60105e-A31-r3-G1000
Contents
1. GIA1 GIA2 PFD1 MFD1 GMU1 FPGA GRS1 FPGA GDC1 FPGA GRS1 MV DB for approved version see DAI MSB D4 045 latest version TR IRRITEER YF TS YA TA TA neon Fa wa OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 18 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR NOTE The database version is displayed on the MFD power up page immediately after system power up and must be acknowledged The remaining system software versions can be verified on the AUX group sub page 5 AUX SYSTEM STATUS 3 If not previously defined the following default settings must be made in the SYSTEM SETUP menu of the G1000 prior to operation refer to Pilot s Guide for procedure if necessary a DIS SPD nm kt sets navigation units to nautical miles and knots b ALT VS ft fom sets altitude units to feet and feet per minute c MAP DATUM WGS 84 sets map datum to WGS 84 see note below d POSITION deg min sets navigation grid units to decimal minutes NOTE In some areas datums other than WGS 84 or NAD 83 may be used If the G1000 is authorized for use by the appropriate Airworthiness Authority the required geodetic datum must be set in the G1000 prior to its use for navigation 4 Operation is prohibited north of 70 N and south of 70 S latitudes In addition operation is prohibited in the following2. AIRCRAFT Garmin G1000 VFR 7 9 POWERPLANT 7 9 4 ENGINE INSTRUMENTS The engine instruments are displayed on the Garmin G1000 MFD Also refer to Section 7 14 3 MULTI FUNCTION DISPLAY MFD Default page Display when pushing Display when pushing Engine the SYSTEM button the FUEL button RPM RPM L 2 Aga 3000 L EE e 2300 o 6 FFLOW GPH 0 9 ELECTRICAL FFLOW GPH 19 9 OIL TEMP VOLTS 12 6 17 Gal 17 52 tt 52 On PRES FUEL CALC oo ml GAL REM 0 8 COOLANT TEMP ENGINE GAL USED 50 0 yo GEARBOX C 35 ENDUR 00 00 A FUEL TEMP MERET bit Al d COOLANT C 60 OIL A FUEL QTY GAL 5 23 TTL TIME IN SVC j 0086 5 HRS OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 47 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR NOTE The figure on previous page is a general demonstration of a typical G1000 MFD to show the different display modes The pictured engine instrument markings may not stringently agree with the current engine limitations of the DA 40 D NOTE The fuel calculations on the FUEL CALC portion do not use the airplane s fuel guantity indicators The values shown are numbers which are calculated from the last fuel guantity update done by the pilot and actual fuel flow data Therefore the endurance and range data is for information only and must not be used for flight planning Designation Pro
3. AIRCRAFT Garmin G1000 VFR 4A 3 11 DESCENT WARNING Do not load a new arrival procedure in the flight plan of the G 1000 if one currently exists without first removing the existing arrival procedure Failing to observe this limitation can cause erroneous course deviation indications loss of GPS navigation information and other display anomalies NOTE If display anomalies are noted after editing the flight plan on the G 1000 perform either a direct to or activate leg operation as appropriate on the flight plan to ensure correct flight plan seguencing and guidance O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 36 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 4A 4 ADVISORY ALERTS ON THE G1000 The G1000 provides the following advisory alerts on the PFD in the alert area 4A 4 1 ADVISORY GENERAL CHARACTERISTICS White color coded text 4A 4 2 GLOW ON GLOW ON Engine glow plug active 4A 4 3 FUEL XFER FUEL XFER Fuel transfer from auxiliary to main tank is in progress 4A 4 4 PFD MFD GIA FAN FAIL PFD FAN FAIL Cooling Fan for the PFD is inoperative MFD FAN FAIL Cooling Fan for the MFD is inoperative GIA FAN FAIL Cooling Fan for the GIA is inoperative The flight may be continued but maintenance action is required after landing OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 37 Ot OAM 40 268 DA 40 D AFM Diam
4. 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 49 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR Alert levels Text Color Audible Tone Warning May reguire Warning chime immediate tone which repeats corrective action without delay until acknowledged by the crew a tion Yellow May require future S ing le warning corrective action chime tone Annunciation White Nana Advisory Message Advisory white None Safe Operation Green Lowest None Annunciation Warning Caution and Advisory Alerts A list of all alerts is given in Section 2 6 WARNING CAUTION AND ADVISORY ALERTS in this Supplement OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 _ or Page 9 A31 50 OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 7 14 GARMIN G1000 INTEGRATED AVIONICS SYSTEM 7 14 1 GENERAL The Gamin G1000 is a fully integrated flight engine communication navigation and surveillance instrumentation system This Integrated Avionics System consists of a Primary Flight Display PFD a Multi Function Display MFD an Audio Panel an Attitude and Heading Reference System AHRS an Air Data Computer ADC andthe sensors and computers to process flight and engine information for display to the pilot The system contains dual GPS receivers dual VOR ILS receivers dual VHF communications transceivers a transponder and an integrated annunciation system to al
5. VFR 3 9 G1000 SYSTEM WARNINGS 3 9 1 RED X A red X through any display field such as COM freguencies NAV freguencies or engine data indicates that display field is not receiving valid data 3 9 2 POSN ERROR The system will flag and no longer provide GPS FOSA ERROR based navigational guidance Revert to the G1000 VOR ILS receivers or an alternate means of navigation other than the G1000 GPS receivers 3 9 3 ATTITUDE FAIL ATTITUDE FAIL The display system is not receiving attitude reference information from the AHRS accompanied by the removal of sky ground presentation and a red X over the attitude area Revert to the standby attitude indicator O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 28 or OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 9 4 AIRSPEED FAIL AIRSPEED FAIL The display system is not receiving airspeed input from the air data computer accompanied by a red X through the airspeed display Revert to the standby airspeed indicator 3 9 5 ALTITUDE FAIL ALTITUDE FAIL The display system is not receiving altitude input from the air data computer accompanied by a red X through the altimeter display Revert to the standby altimeter 3 9 6 VERT SPEED FAIL VERT SPEED FAIL The display system is not receiving vertical speed input from the air data computer accompanied by a red X through the vertical speed display Det
6. 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 32 Ot OAM 40 268 DA 40 D AFM Y Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 10 5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS NOTE Loss of an engine parameter is indicated by a red X through the data field Erroneous information may be identified by indications which do not agree with other system information Erroneous indications may be determined by comparing a display with other displays and other system information 1 Set power based on throttle lever position engine noise and speed 2 Monitor other indications to determine the health of the engine 3 Use known power settings and performance data of the AFM for approximate fuel flow values 4 Use other system information such as annunciator messages GPS fuel quantity and flow to safely complete the flight OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 33 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 10 6 ERRONEOUS OR LOSS OF WARNING CAUTION ANNUNCIATORS NOTE Loss of an annunciator may be indicated when engine or fuel displays show an abnormal or emergency situation and the annunciator is not present An erroneous annunciator may be identified when an annunciator appears which does not agree with other displays or system information 1 lfan annunciator appears treat it as if the condition exists Refer to the pro
7. Engine gearbox temperature is in the upper red range too high gt 120 C ALTN AMPS Engine alternator output is in the upper red range too high gt 90 amps OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 _ or Page 9 A31 11 OAM 40 268 4 Supplement A31 DA 40 D AFM W Diamond Garmin G1000 VFR Warning alerts g Meaning Cause red ALTN FAIL Engine alternator has failed STARTER Engine starter is engaged DOOR OPEN Front and or rear canopy are is not closed and locked AP TRIM FAIL Failure in the automatic trim system of the autopilot if autopilot installed POSN ERROR G1000 will no longer provide GPS based navigational guidance ATTITUDE FAIL The display system is not receiving attitude reference information from the AHRS AIRSPEED FAIL The display system is not receiving airspeed input from the air data computer ALTITUDE FAIL The display system is not receiving altitude input from the air data computer VERT SPEED The display system is not receiving vertical speed input from FAIL the air data computer HDG The display system is not receiving valid heading input from the AHRS WARN RAIM position warning The nav deviation bar is removed OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 12 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR Color and significance of the caution alerts on the G1000 Caution alerts Meaning Cause yell
8. 01 05 E Rev 3 01 Jun 2008 Page 9 A31 41 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 4B 9 6 COOL LVL COOL LVL Engine coolant level is low A COOL LVL caution on the G1000 System is equivalent to a WATER LEVEL caution indicated on the AED 125 as described in the AFM and all its procedures 4B 9 7 PITOT FAIL HT OFF PITOT FAIL Pitot heating system has failed PITOT HT OFF Pitot heating system is OFF A PITOT FAIL caution on the G1000 System is equivalent to a PITOT caution indicated on the annunciator panel as described in the AFM and all its procedures A PITOT OFF caution on the G1000 System informs the pilot that the Pitot heating system is switched off OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 42 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 4B 9 8 INTEG RAIM NOT AVAILABLE INTEG RAIM Receiver Autonomous Integrity Monitor is not RAIM not available available Revert to other navigational method 4B 9 9 AHRS ALIGNING KEEP WINGS LEVEL GEED The AHRS Attitude and Heading Reference System is aligning Keep Wings Level Keep wings level using standby attitude indicator OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 43 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 5 PERFORMANCE No change 6 MASS AND
9. 5 E Rev 3 01 Jun 2008 Page 9 A31 20 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 EMERGENCY PROCEDURES 3 1 3 SELECTING EMERGENCY FREQUENCY In an in flight emergency depressing and holding the Com transfer button on the G1000 for 2 seconds will tune the emergency frequency of 121 500 MHz If the display is available it will also show it in the Active frequency window 3 8 AIRPLANE RELATED G1000 WARNINGS NOTE Airplanes equipped with the Garmin G1000 have no annunciation panel All annunciations are displayed on the G1000 The annunciations differ from those listed in the main part of the AFM 3 8 1 WARNINGS GENERAL CHARACTERISTICS Means that the non observation of the corresponding procedure leads to an immediate or important degradation in flight safety Red color coded warning text Warning chime tone of 1 5 second duration which repeats without delay until acknowledged by the crew OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 21 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 8 2 ENG TEMP ENG TEMP Engine coolant temperature is in the upper red range too high above 105 C Check coolant qty caution COOL LVL if off during climb Reduce power by 10 Increase airspeed by 10 KIAS If the coolant temperature does not reach the green range within 60 seconds redu
10. Attitude and Heading Reference System COM1 COM Radio No 1 FLOOD Flood Light GPS NAV1 Global Positioning System and NAV Receiver No 1 XPDR Transponder LANDING Landing Light PFD Primary Flight Display PITOT Pitot Heating System FLAPS Flap System AP WARN Autopilot Warning MASTER CONTROL Master Control Avionics Relay ESS TIE Bus Interconnection ENG INST Engine Instruments O M 40 224 01 Jun 2008 Page 9 A31 6 Ot OAM 40 268 DA 40 D AFM Y Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR MAIN BUS MAIN TIE XFER PUMP MFD INST LT AV CDU FAN PWR STROBE POSITION TAXI MAP START AV BUS ECU BUS ECU ALT ECU A ECUB AVIONICS BUS GPS NAV2 COM2 AUDIO AP ADF DME WX500 Doc 6 01 05 E Bus Interconnection Fuel Transfer Pump Multi Function Display Instrument Lights Avionic CDU Cooling Fans Power Strobe Lights Anti Collision Lights Position Lights Taxi Light Map Lights Starter Avionic Bus ECU Alternate power relay ECUA ECUB Global Positioning System and NAV Receiver No 2 COM Radio No 2 Audio Panel Marker Beacon Receiver Autopilot System Automatic Direction Finder Distance Measuring Eguipment Stormscope OAM 40 224 01 Jun 2008 or Page 9 A31 7 O M 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 2 LIMITATIONS NOTE There is no change in existing operating limitations of the airplane Following information
11. BALANCE Upon removal or installation of the Garmin G1000 system the change of empty mass and corresponding center of gravity of the airplane must be recorded according to Chapter 6 of the Airplane Flight Manual O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 44 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7 4 INSTRUMENT PANEL 11 2 se Ma 2 Fuel Transfer switch 15 Alternate static valve 10 Rotary buttons for instrument 23 Autopilot control unit if Autopilot lighting and flood light installed 11 Light switches 24 Primary Flight Display PFD 12 Emergency switch 25 Audio amplifier Intercom Marker beacon receiver OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 _ or Page 9 A31 45 OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 13 Circuit breakers 26 Multi Function Display MFD Designations and abbreviations used to identify the circuit breakers are explained in Section 1 5 DEFINITIONS AND ABBREVIATIONS NOTE The figure on previous page shows the typical DA 40 D installation position for the equipment with the G1000 System installed The actual installation may vary due to the approved equipment version OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 46 Ot OAM 40 268 DA 40 D AFM Y Diamond Supplement A31
12. DA 40 D AFM gp Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR SUPPLEMENT A31 TO THE AIRPLANE FLIGHT MANUAL DA 40 D INTEGRATED AVIONICS SYSTEM G1000 GARMIN VFR OPERATION Doc No 6 01 05 E Date of Issue of the Supplement 08 Sep 2006 Design Change Advisory OAM 40 224 or OAM 40 268 Signature DAI Design Organisation Stamp 22 SEP 2006 Date of approval The technical information contained in this document has been approved under the authority of DOA No EASA 21J 052 DIAMOND AIRCRAFT INDUSTRIES GMBH N A OTTO STR 5 A 2700 WIENER NEUSTADT AUSTRIA Page 9 A31 1 DA 40 D AFM O Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 0 1 RECORD OF REVISIONS Rev Reason Chapter Page s Date of Approval Date of No Revision Note Approval _ Te GARMIN 0 9 A31 1 through Service 9 A31 5 approved by Bulletin No 15 Feb 2008 R Kremnitzer 29 May 2008 0708 Rev A 9 A31 33 through for DAI Implemented 9A 31 55 4 01 Jun 2008 Date Inserted ES F OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 _ or Page 9 A31 1 OAM 40 268 approved by H Lackner for DAl Equipment OAM 40 268 Corrections Instrument Markings for all TAE except 125 02 99 cover page engine 18 JULI 2008 corrections DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 0 2 LIST OF EFFECTIVE PAGES Chapter 08 Sep 2006 01 Ju
13. al reguirements are met the following kinds of operation are approved e daytime flights according to Visual Flight Rules VFR e with the appropriate equipment night flights according to Visual Flight Rules VFR Flights into known or forecast icing conditions are prohibited Flights into known thunderstorms are prohibited Minimum operational equipment serviceable The following table lists the minimum serviceable equipment required by JAR 23 Additional minimum equipment for the intended operation may be required by national operating rules and also depends on the route to be flown NOTE Many of the items of minimum equipment listed in the following table are integrated in the G1000 OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 15 Ot OAM 40 268 Supplement A31 Garmin G1000 VFR Y Diamond AIRCRAFT for daytime VFR flights in addition for night VFR flights Flight amp DA 40 D AFM e airspeed indicator on G1000 vertical speed indicator VSI naviga tion instru ments lighting other opera tional mini mum equip ment Doc 6 01 05 E PFD or backup altimeter on G1000 PFD or backup magnetic compass 1 headset used by pilot in command fuel qty oil press oil temp coolant temp coolant level indicator gearbox temp load prop RPM fuel temp left amp right tank stall warning system alternate means for fuel quantity indication see Sect
14. ce power as far as possible and increase airspeed during cruise Reduce power Increase airspeed Check coolant temperature in green range CAUTION If the coolant temperature does not return to the green range perform a precautionary landing on the nearest airfield in accordance with the procedures given in the AFM ifon Reduce power Expect loss of coolant OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 22 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR WARNING A further increase in coolant temperature must be expected Prepare for an emergency landing in accordance with the procedures given in the AFM 3 8 3 OIL TEMP OIL TEMP Engine oil temperature is in the upper red range too high above 140 C Check oil pressure if the oil pressure is low Reduce power Expect loss of oil with engine failure Prepare for an emergency landing in accordance with the procedures given in the AFM if the oil pressure is within the green range Reduce power Increase airspeed OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 23 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 8 4 OIL PRES OIL PRES Engine oil pressure is in the lower red range too low below 1 2 bar NOTE If the RPM indication is less than 1500 RPM with the power lever at IDLE the oil pressu
15. cedures given in the AFM 2 Ifa display indicates an abnormal condition but no annunciator is present use other system information such as engine displays GPS fuel quantity and flow to determine if the condition exists If it cannot be determined that the condition does not exist treat the situation as if the condition exists Refer to the procedures given in the AFM OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 34 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 4A NORMAL OPERATING PROCEDURES NOTE Airplanes eguipped with the Garmin G1000 have no annunciation panel All annunciations are displayed on the G1000 The annunciations differ from those listed in the main part of the AFM 4A 3 4 BEFORE TAXIING WARNING Do not load a new departure procedure in the flight plan of the G 1000 if one currently exists without first removing the existing departure procedure Failing to observe this limitation can cause erroneous course deviation indications loss of GPS navigation information and other display anomalies NOTE If display anomalies are noted after editing the flight plan on the G 1000 perform either a direct to or activate leg operation as appropriate on the flight plan to ensure correct flight plan seguencing and guidance O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 35 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31
16. e automatic entry of reversionary mode is resolved A maximum of one attempt to return to normal mode is approved using the following procedure I If the system returns to normal mode leave the DISPLAY BACKUP button IN and continue as display flashing occurs then return the DISPLAY BACKUP button to the OUT l If the system remains in reversionary mode or abnormal display behavior such position OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 31 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 10 3 AHRS FAILURE NOTE A failure of the Attitude and Heading Reference System AHRS is indicated by a removal of the sky ground presentation and a red X and a yellow AHRS FAILURE shown on the PFD The digital heading presentation will be replaced with a yellow HDG and the compass rose digits will be removed The course pointer will indicate straight up and course may be set using the digital window 1 Use standby attitude indicator emergency compass and Navigation Map 2 Course 7 sus dev ji da j j set using digital window 3 10 4 AIR DATA COMPUTER ADC FAILURE NOTE Complete loss of the Air Data Computer is indicated by a red X and yellow text over the airspeed altimeter vertical speed TAS and OAT displays Some FMS functions such as true airspeed and wind calculations will also be lost 1 Use standby airspeed indicator and altimeter O M 40
17. ermine vertical speed based on the change of altitude information OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 29 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 9 7 HDG The display system is not receiving valid heading input from the AHRS accompanied by a red X through the digital heading display Revert to the emergency compass 3 9 8 WARN IWARN RAIM position warning nav deviation bar removed 1 CDI softkey ER SR aus ees Bae wae switch to VOR LOC OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 30 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 10 G1000 FAILURES 3 10 1 NAVIGATION INFORMATION FAILURE If GARMIN G1000 GPS navigation information is not available or invalid utilize remaining operational navigation eguipment as reguired 3 10 2 PFD OR MFD DISPLAY FAILURE 1 DISPLAY BACKUP button on audio panel PUSH Automatic Entry of Display Revisionary Mode Ifthe PFD and MFD have automatically entered reversionary mode use the following procedure a DISPLAY BACKUP button on audio panel PUSH button will be OUT NOTE After automatic entry of reversionary mode the pilot must press the DISPLAY BACKUP button on the audio panel After the DISPLAY BACKUP button has been pushed the system will remain in reversionary mode even if the problem causing th
18. ert the pilot of certain abnormal conditions A remote avionic box is located behind the aft baggage compartment frame A push to talk PTT button for the COM portion of the G1000 is mounted on the end of each control stick There are connection facilities for up to 4 headsets between the front seats Refer to the Garmin G1000 Cockpit Reference Guide Garmin P N 190 00324 03 Rev A and Pilot s Guide P N 190 00363 01 Rev B for complete descriptions of the G1000 system and operating procedures O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 51 Ot OAM 40 268 DA 40 D AFM Y Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 7 14 2 PRIMARY FLIGHT DISPLAY PFD The Primary Flight Display PFD see figure below typically displays airspeed attitude altitude and heading information in a traditional format Slip information is shown as a trapezoid under the bank pointer One width of the trapezoid is equal to a one ball width slip Rate of turn information is shown on the scale above the compass rose full scale deflection is equal to a standard rate turn The following controls are available on the PFD clockwise from top right Communications frequency volume and squelch knob Communications frequency set knobs Communications frequency transfer button Altimeter setting knob baro set Course knob Map range knob and cursor control FMS control buttons and knob PFD softkey buttons incl
19. ev 3 01 Jun 2008 or Page 9 A31 4 O M 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 0 3 TABLE OF CONTENTS Page i GENERAL ane A De ts D R DDD 9 A31 6 2 OPERATING LIMITATIONS i e ka araa asas ANA ANA AKA 9 A31 8 3 EMERGENCY PROCEDURES 24 ia adan aan da maan 9 A31 21 4A NORMAL OPERATING PROCEDURES i 9 A31 35 4B ABNORMAL OPERATING PROCEDURES 9 A31 38 5 JPERPFORMANCE ts Ek ERENS an tree N oh hove hoe he N dekas 9 A31 44 6 UMASS AND BALANCE lt STERRE DE GE east teed eee eee 9 A31 44 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 9 A31 45 8 AIRPLANE HANDLING CARE AND MAINTENANCE 9 A31 56 OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 or Page 9 A31 5 O M 40 268 Supplement A31 DA 40 D AFM Garmin G1000 VFR Y Diamond AIRCRAFT 1 GENERAL This Supplement supplies the information necessary for the efficient operation of the airplane when the Integrated Avionics System Garmin G1000 is installed The information contained within this Supplement is to be used in conjunction with the complete AFM This Supplement is a permanent part of this AFM and must remain in this AFM at all times when the G1000 is installed 1 5 DEFINITIONS AND ABBREVIATIONS f Designation of the circuit breakers on the instrument panel Doc 6 01 05 E ESSENTIAL BUS HORIZON Artificial Horizon Attitude Gyro ADC Air Data Computer AHRS
20. g chime tone of 1 5 seconds duration 4B 9 2 ECU A FAIL ECU A FAIL Engine ECU A has failed or is being tested during FADEC test procedure before take off check A ECU A FAIL caution on the G1000 System is equivalent to a ECU A caution indicated on the annunciator panel as described in the AFM and all its procedures whereby the ECU A FAIL caution of the G1000 is steady on when appearing OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 40 Ot OAM 40 268 DA 40 D AFM O Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 4B 9 3 ECU B FAIL ECU B FAIL Engine ECU B has failed or is being tested during FADEC test procedure before take off check A ECU B FAlL caution on the G1000 System is equivalent to a ECU B caution indicated on the annunciator panel as described in the AFM and all its procedures whereby the ECU B FAIL caution on the G1000 is steady on when appearing 4B 9 4 L FUEL LOW L FUEL LOW Main tank fuel quantity is low A L FUEL LOW caution on the G1000 System is equivalent to a LOW FUEL caution indicated on the annunciator panel as described in the AFM and all its procedures 4B 9 5 LOW VOLTAGE CAUTION LOW VOLTS VOLTS LOW Bus voltage is too low less than 12 6 volts A VOLTS LOW caution on the G1000 System is equivalent to a LOW VOLTS caution indicated on the annunciator panel as described in the AFM and all its procedures OAM 40 224 Doc 6
21. he last 2 2 minutes of received audio Lights above the selections indicate what selections are active Pressing the red DISPLAY BACKUP button on the audio panel causes both the PFD and MFD to display a composite mode 7 14 5 ATTITUDE AND HEADING REFERENCE SYSTEM AHRS The Attitude and Heading Reference System AHRS uses GPS rate sensors air data and magnetic variation to determine pitch and roll attitude sideslip and heading Operation is possible in a degraded mode if the system loses any of these inputs Status messages alert the crew of the loss of any of these inputs The AHRS will align while the airplane is in motion but will align guicker if the wings are kept level during the alignment process 7 14 6 AIR DATA COMPUTER ADC The Air Data Computer ADC provides airspeed altitude vertical speed and air temperature to the display system In addition to the primary displays this information is used by the FMS and TIS systems O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 55 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 8 AIRPLANE HANDLING CARE AND MAINTENANCE 8 5 CLEANING AND CARE 8 5 5 INTERIOR SURFACES All instruments can be cleaned using a soft dry cloth plastic surfaces should be wiped clean using a damp cloth without any cleaning agents CAUTION The PFD and MFD displays use a lens coated with a special anti reflective coating that is ve
22. ion 7 9 safety belts for each occupied seat Airplane Flight Manual Rev 3 01 Jun 2008 attitude gyro artificial horizon on G1000 PFD or backup turn amp bank indicator directional yro VHF radio OM with speaker and microphone VOR receiver transponder XPDR mode A and mode C GPS receiver ammeter voltmeter position lights strobe lights anti collision lights landing light instrument lighting flood light flashlight Pitot heating system alternate static valve O M 40 224 _ or Page 9 A31 16 OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 2 16 8 GARMIN G1000 AVIONICS SYSTEM 1 The Garmin G1000 Cockpit Reference Guide P N 190 00324 03 Rev A or later appropriate revision must be immediately available to the flight Crew 2 The G1000 must utilize the software Garmin P N 010 00370 11 or later approved software in accordance with the mandatory service bulletin DAI MSB D4 045 latest version O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 17 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR Software Approved Version 010 00370 Manifest 006 B0093 006 B01 72 006 B0190 006 B0193 006 B0203 006 B0223 006 B0224 006 B0319 006 B0328 006 B0329 006 C0048 006 C0049 006 C0055 006 D0159 006 D0202 006 B0261 006 B0081 006 B0083 006 B0082
23. is exclusively to reflect the indications on the Garmin G1000 24 POWER PLANT LIMITATIONS 9 Oil temperature TAE 125 02 99 TAE 125 01 M M 40 256 carried out TAE 125 02 99 TAE 125 01 M M 40 256 carried out O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 8 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 2 5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the tables below fthe TAE 125 01 engine is installed Indi Red Yellow Green Yellow Red cation arc bar arc bar arc bar arc bar arc bar lower caution normal caution upper prohibited range operating range prohibited range range range up to 2400 2400 to 2500 above RPM RPM 2500 RPM Oil below 1 2102 3 bar 23to5 2bar 5 2 to 6 5 bar above pressure 1 2 bar 6 5 bar i below above 32 to 50 C 50 to 130 C 130 to 140 C 140 C Coolant below above temp 32 to 60 C 60to 101 C 101 to 105 C 105 C vee aar N up to 115 C 115 to 120 C a ed IE Fuel gty below 0 45 0 45 to 14 US gal US gal O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 9 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR fthe TAE 125 02 99 engine is installed M M 40 256 is carried out Red Yellow Green Yellow Red arc bar arc bar arc bar arc bar arc bar lower caution normal caution upper
24. n 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 9 A31 6 01 Jun 2008 9 A31 7 01 Jun 2008 9 A31 8 01 Jun 2008 9 A31 9 01 Jun 2008 9 A31 10 01 Jun 2008 9 A31 11 01 Jun 2008 9 A31 12 01 Jun 2008 9 A31 13 01 Jun 2008 9 A31 14 01 Jun 2008 9 A31 15 01 Jun 2008 9 A31 16 01 Jun 2008 2 9 A31 17 01 Jun 2008 9 A31 18 01 Jun 2008 9 A31 19 01 Jun 2008 9 A31 20 01 Jun 2008 OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 2 vol Page 9 A31 2 OAM 40 268 DA 40 D AFM Chapter 4A 4B 5 6 Y Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 01 Jun 2008 9 A31 35 01 Jun 2008 9 A31 36 01 Jun 2008 9 A31 37 01 Jun 2008 9 A31 38 01 Jun 2008 9 A31 39 01 Jun 2008 9 A31 40 01 Jun 2008 9 A31 41 01 Jun 2008 9 A31 42 01 Jun 2008 9 31A 43 01 Jun 2008 9 A31 44 01 Jun 2008 OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 or Page 9 A31 3 O M 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR Chapter 9 A31 45 01 Jun 2008 9 A31 46 01 Jun 2008 9 A31 47 01 Jun 2008 9 A31 48 01 Jun 2008 9 A31 49 01 Jun 2008 7 9 A31 50 01 Jun 2008 9 A31 51 01 Jun 2008 9 A31 52 01 Jun 2008 9 A31 53 01 Jun 2008 9 A31 54 01 Jun 2008 9 A31 55 01 Jun 2008 8 9 A31 56 01 Jun 2008 OAM 40 224 Doc 6 01 05 E R
25. ng source of electrical power for about 30 minutes 1 Circuit breakers check if all are O K proceed with step 2 2 ESSENTIAL BUS ON 3 Electrical equipment switch OFF all equipment which is not needed 4 Land on the nearest suitable airfield WARNING The ECU which is absolutely necessary for engine operation needs electrical power It is recommended to switch off all electrical consumers and to land as soon as possible Be prepared for an engine failure and an emergency landing For a severe electrical failure a ECU Backup System is installed OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 26 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 8 9 STARTER STARTER Engine starter is engaged A STARTER warning on the G1000 System is equivalent to a START warning indicated on the annunciator panel as described in the AFM and all its procedures whereby the STARTER warning of the G1000 is steady on when appearing 3 8 10 DOOR OPEN DOOR OPEN t rear canopy door are is not closed and A DOOR OPEN warning on the G1000 System is equivalent to a DOOR warning indicated on the annunciator panel as described in the AFM and in all its procedures O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 27 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000
26. ond Supplement A31 AIRCRAFT Garmin G1000 VFR 4B ABNORMAL OPERATING PROCEDURES 4B 8 ENGINE INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE ON THE G1000 4B 8 1 HIGH RPM Proceed according to 4B 2 1 RPM in the main part of the AFM 4B 8 2 HIGH OR LOW COOLANT TEMPERATURE Proceed according to 4B 2 2 COOLANT TEMPERATURE CT in the main part of the AFM 4B 8 3 HIGH OR LOW OIL TEMPERATURE Proceed according to 4B 2 3 OIL TEMPERATURE OT in the main part of the AFM 4B 8 4 HIGH OR LOW OIL PRESSURE Proceed according to 4B 2 4 OIL PRESSURE OP in the main part of the AFM OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 38 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 4B 8 5 HIGH GEARBOX TEMPERATURE Proceed according to 4B 2 5 GEARBOX TEMPERATURE GT in the main part of the AFM 4B 8 6 HIGH OR LOW FUEL TEMPERATURE Proceed according to 4B 2 6 FUEL TEMPERATURE FUEL TEMP in the main part of the AFM 4B 8 7 HIGH OR LOW VOLTAGE Proceed according to 4B 4 2 VOLT in the main part of the AFM OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 39 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 4B 9 CAUTION ALERTS ON THE G1000 The G1000 provides the following CAUTION alerts on the PFD in the ALERT area 4B 9 1 CAUTIONS GENERAL CHARACTERISTICS yellow color coded text Single warnin
27. ors are shown on the airspeed and altimeter displays as a magenta line predicting 6 seconds at the current rate The turn rate indicator also functions as a trend indicator on the compass scale The PFD can be displayed in a composite format for emergency use by pressing the DISPLAY BACKUP button on the audio panel In the composite mode the full crew alerting function remains but no map functions are available 7 14 3 MULTI FUNCTION DISPLAY MFD The Multi Function Display MFD typically displays engine data maps terrain traffic and topography displays and flight planning and progress information The display unit is identical to the PFD and contains the same controls as previously listed Engine instruments are displayed on the MFD Discrete engine sensor information is processed by the Garmin Engine Airframe GEA sub system When an engine sensor indicates a value outside the normal operating range the legend will turn yellow for caution range and turn red and flash for warning range Also refer to Section 7 9 4 ENGINE INSTRUMENTS OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 54 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 7 14 4 AUDIO PANEL The audio panel contains traditional transmitter and receiver selectors as well as an integral intercom and marker beacon system The marker beacon lights appear on the PFD In addition a clearance recorder records t
28. ow CAUTION One of the Cautions below is being indicated Engine ECU A has failed or ECU A FAIL is tested during FADEC test procedure during before take off check Engine ECU B has failed ECU B FAIL 9 Is tested during FADEC test procedure during before take off check L FUEL LOW Main tank fuel guantity is low VOLTS LOW Engine bus voltage is too low lt 12 6 volts COOL LVL Engine coolant level is low PITOT FAIL Pitot heat has failed PITOT HT OFF Pitot heat is OFF INTEG RAIM not RAIM Receiver Autonomous Integrity Monitor is not available available AHRS ALIGN The AHRS Attitude and Heading Reference System is Keep Wings aligning Level O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 13 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR Color and significance of the advisory alerts on the G1000 advisory alerts Meaning Cause white GLOW ON Engine glow plug active FUEL XFER Fuel transfer from auxiliary to main tank is in progress PFD FAN FAIL Cooling fan for the PFD is inoperative MFD FAN FAIL Cooling fan for the PFD is inoperative GIA FAN FAIL Cooling fan for the GlAs is inoperative O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 14 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 2 13 KINDS OF OPERATION Provided that national operation
29. peller RPM GEARBOX Gearbox temperature O M 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 _ or Page 9 A31 48 OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 7 10 ELECTRICAL SYSTEM 7 10 3 WARNING CAUTION AND ADVISORY MESSAGES Crew Alerting System CAS The G1000 Crew Alerting System CAS is designed to provide visual and aural alerts to the flight crew Alerts are divided into three levels as follows WARNING CAUTION ADVISORY Crew alerts will appear in the Alerts Window on the PFD In this window Warnings will appear at the top followed by Cautions and Advisories respectively Within the criticality levels messages will appear from newest top to oldest bottom At the low right corner of the display there is a MSG Message soft key The MSG key provides two functions in the CAS 1 Pressing the MSG key acknowledges a new master warning caution advisory indication 2 An additional MSG key press with no master alert indication active will open a pop up Auxiliary Flight Display AFD page that contains information for all active alerts This structure allows the crew to scroll through all system alerts if the Alerts Window overflows This approach displays the most critical alerts close to the pilot s primary field of view at all times with the option of allowing lower criticality alerts to overflow and be accessible from the pop up AFD page window OAM 40 224 Doc
30. prohibited range operating range prohibited range range range above below above pressure 1 2 bar 1 2 to 2 3 bar 2 3 to 5 8 bar 5 8 to 6 5 bar 6 5 bar Oil below above temp 30 C 30 to 50 C 50 to 130 C 130 to 140 C 140 C Coolant 30 to 60 C 60to 101 C 101 to 105 C temp above Kai up to 115 C 115 to 120 C 120 C Poem Ke Ara Fuel gty below 1 to 14 US gal 1 US gal OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 _ or Page 9 A31 10 OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 2 6 WARNING CAUTION AND STATUS LIGHTS NOTE Airplanes eguipped with the Garmin G1000 have no annunciation panel All annunciations are displayed on the G1000 The annunciations differ from those listed in the main part of the AFM The following tables show the color and significance of the warning caution and advisory alerts lights on the G1000 Color and significance of the warning alerts on the G1000 Warning alerts i Meaning Cause red WARNING One of the Warnings listed below is being indicated Engine coolant temperature is in the upper red range too high gt 105 C Engine oil temperature is in the upper red range OIL TEMP too high gt 140 C Engine oil pressure is in the lower red range OIL PRES too low lt 1 2 bar ENG TEMP L R FUEL TEMP Fuel temperature is in the upper red range too high gt 75 C GBOX TEMP
31. re must drop into the red range to cause the OIL PRES warning to illuminate Reduce power Expect loss of oil with engine failure Prepare for an emergency landing in accordance with the procedures given in the AFM 3 8 5 GBOX TEMP Engine gearbox temperature is in the upper red range Oe HEM too high above 120 C Reduce power Increase airspeed 3 8 6 L R FUEL TEMP Fuel temperature is in the upper red range too high L R FUEL TEMP above 75 C Reduce power Increase airspeed OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 24 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 8 7 ALTN AMPS Engine alternator output is in the upper red range too ACTV AMPS high above 90 amps This warning is indicated when the consumption of electrical power is too high Possible reasons are A fault in wiring or equipment 1 Electrical equipment switch OFF as necessary and possible to reduce electric load if the problem does not clear itself 2 Land on the nearest suitable airfield OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 25 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 3 8 8 ALTN FAIL ALTN FAIL Engine alternator has failed An alternator failure is indicated by a warning light ALTN FAIL on the G1000 System The batteries are the last remaini
32. ry sensitive to skin oils waxes and abrasive cleaners CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI REFLECTIVE COATING It is very important to clean the lens using a clean lint free cloth and an eyeglass lens cleaner that is specified as safe for anti reflective coatings OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 56 Ot OAM 40 268
33. two regions a north of 65 N between 75 W and 120 W longitude and b south of 55 S between 120 E and 165 E longitude OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 19 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR 5 The fuel guantity fuel reguired and fuel remaining functions on the Fuel Page displayed when pushing the FUEL button as shown in Section 7 9 4 of the FMS are supplemental information only and must be verified by the flight crew 6 The pilot s altimeter is the primary altitude reference during all operations using advisory vertical navigation VNAV information 7 Navigation must not be predicated upon the use of the Terrain or Obstacle data displayed by the G1000 NOTE The terrain display is intended to serve as a situational awareness tool only lt may not provide either the accuracy or fidelity or both on which to solely base decisions and plan maneuvers to avoid terrain ir obstacles 8 The Terrain Obstacle Airport databases have an area of coverage as detailed below 1 The Terrain Database has an area of coverage from North 75 Latitude to South 60 Latitude in all longitudes 2 The Airport Terrain Database has an area of coverage that includes the United States Canada Mexico Latin America and South America 3 The Obstacle Database has an area of coverage that includes the United States O M 40 224 Doc 6 01 0
34. uding master warning caution acknowledgment Altitude reference set knob Heading bug control Navigation frequency transfer button Navigation freguency set knobs Navigation frequency volume and Identifier knob OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 52 Ot OAM 40 268 W Di mon Supplement A31 as d 10nd Garmin G1000 VFR nav1110 90 115 90 BUMI wer KIXD T RK 259 136 975 118 888 com Nave 117 88 top fi COM2 1200 STBY 2 IDENT TMR REF NRST ALERTS The PFD displays the crew alerting annunciator system When a warning or caution message is received a warning or caution annunciator will flash on the PFD accompanied by an aural tone A warning is accompanied by a repeating tone and a caution is accompanied by a single tone Acknowledging the alert will cancel the flashing and provide a text description of the message Refer to the procedures given in the AFM and to Section 7 10 3 WARNING CAUTION AND ADVISORY MESSAGES of this supplement OAM 40 224 Doc 6 01 05 E Rev 3 01 Jun 2008 Page 9 A31 53 Ot OAM 40 268 DA 40 D AFM Diamond Supplement A31 AIRCRAFT Garmin G1000 VFR Advisory messages related to G1000 system status are shown in white and are accompanied by a white flashing ADVISORY alert Refer to the G1000 Pilot s Guide and Cockpit Reference Guide for descriptions of the messages and recommended actions if applicable Trend vect
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