Garmin Software Version 0321.19 FAA Approved Airplane Flight Manual Supplement
Contents
1. 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 2 3 AIRSPEED MARKINGS Marking IAS Significance Red band 20 KIAS 53 KIAS Low speed awareness stall is imminent Yeow baud SIRAS SEKAS LON Speed avatcness lt _ temuced airspeed margin to stall White band 58 KIAS 91 KIAS Operating range with flaps fully extended Green band 58 KIAS 129 KIAS Normal operating range Yellow band 129 KIAS 178 KIAS Caution range smooth air only Red band VS KTAS a e E AIS Me eeg for all operations The airspeed indicator is marked in IAS values 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 2 5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the table below NOTE When an indication lies in the upper or lower prohibited range the legend for that display will change to the color of the prohibited range and will flash Red arc or Yellow Green arc Red arc or bar arc or or bar Yellow bar bar arc or bar Lower Normal Upper prohibited Caution operating Caution prohibited Indication range2. IN FLIGHT 1 Monitor for MFD OVERHEAT caution message c GIA FAN FAIL caution ON GROUND 1 Do not takeoff in night or in instrument meteorological conditions IN FLIGHT 1 Minimize all COM transmissions to reduce temperature 2 Monitor for GIA 1 and GIA 2 OVERHEAT caution messages 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4B 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F PFD MFD AND GIA OVERHEAT a PFD OVERHEAT caution NOTE The PFD is approaching its operating temperature limit Display brightness is automatically reduced to 50 of maximum 1 Cross check PFD attitude heading altimeter and airspeed with standby instruments 2 If PFD primary flight instruments do not agree with standby flight instruments or the PFD fails or is unusable select Display Reversionary Mode using the red DISPLAY BACKUP button on the audio panel Pull the PFD circuit breaker b MFD OVERHEAT caution NOTE The MFD is approaching its operating temperature limit Display brightness is automatically reduced to 50 of maximum 1 Select Display Reversionary Mode using the red DISPLAY BACKUP button on the audio panel 2 Cross check MFD engine instruments and primary flight instruments with the PFD If the MFD does not agree with the PFD or the MFD fails or is unusable pull the MFD circuit breaker c PFD OVERHEAT caut
3. 0 0 cceeccceseeeeceeeceeeceneceeecaeecneeeneeneeees OPEN 6a Carburetor Heat DA 40 F only 0 0 e ec eeceeceeeceeeeeeeeeeeeeeeeeeeeeneeeneees HOT 7 Emergency Window S ccscccssesesceesceeecesecenecesecneeeeeeneeeneees open if required 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F CAUTION Ice build up increases the stalling speed If required for safety reasons engine speeds up to 2700 RPM are permissible without time limit 8 ATC sincaniatinaiis nica cans aiccindva advise if an emergency is expected CAUTION When the pitot heating fails yellow PITOT FAIL annunciation and the alternate static valve is installed 9 Alternate static Valv ccccccccccccsessssssccseccessssssssssevsecssssssesseseesseenes OPEN 10 Emergency window s cs cesccsssceseceseceseceecaeeeneeeaeeeseeseeneeeeereeeensees close 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 3 7 2 FAILURES IN THE ELECTRICAL SYSTEM b Alternator failure An alternator failure is indicated by a red ALTERNATOR message and an ammeter indication of 0 Amps 1 Circdit breakers vicctess ace iin ieee ne Se aE Sie Check in 2 ALT alternator switch 0 0 cceccescceseeeescecsseceseeee
4. OFF CAUTION When the essential bus is switched ON the battery will not be charged unless the essential tie relay bypass OAM 40 126 is installed 21 BAT battery O IE D a aves e s eE ER E ON 22 FUE tank SCICCTOL nees orehe arene or e e EEr n on fullest tank WARNING Never move the propeller by hand while the ignition is switched on as it may result in serious personal injury Never try to start the engine by hand 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F STARTING ENGINE DA 40 only a Cold engine Ti Strobe ight ACD aa sons lade eshes ya ra a e ESEE EEEE ON 2 Electrical fuel PUMP seri einen pena eie ON note pump noise oleae EEA A EE A E EES functional check of pump Bs Thrott ienen e e i 3 cm 1 2 in forward from IDLE EEEE EE E EEE EE measured from rear of slot 4 Mixture control lever oosseoeonseseeesssee00eee RICH for 3 5 sec then LEAN 5 Throttle 1 cm 0 4 in forward from ou ceeceeeceeseceseeeeececeseeeeeeeesseeeees IDLE r a r A measured from rear of slot WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 at
5. heck beeen nck esis S Eaa EEEa pressed in 10 Fuel pressure iiss regres Check no messages illuminated TI Electric fuel pumpieri eK e E rite E ER T ON 12 Mixture control lever ccccccesccesseceseceeseeceeeeeeseeeeee RICH below 5000 ft NOTE At a density altitude of 5000 ft or above or at high ambient temperatures a fully rich mixture can cause rough running of the engine or a loss of performance The mixture should be set for smooth running engine 13 Flaps krenen anre ie a E R E SSS check T O T4 Trin oo hitches e a cede Sia Saeed check T O 15 Flight controls 0 cee cessecseesecneseeceeeeeceeeeeeeees free movement correct sense T6 Throttle 3 2522 oneta aE da ey 2000 RPM DA 40 aaa ahah AEE ra e EEEE AE e AEE E E a 1800 RPM DA 40 F 17 Magneto check iina aE L BOTH R BOTH Max RPM drop 175 RPM Max difference 50 RPM CAUTION The lack of an RPM drop suggests a faulty ground or incorrect ignition timing In case of doubt the magneto check can be repeated with a leaner mixture in order to confirm a problem Even when running on only one magneto the engine should not run unduly roughly 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 11 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 18 RPM lever DA 40 only 00 eeeeeees pull back until a drop of max 500 RPM is reached HIGH RPM Cycle 3 times 18a Car
6. is not available or invalid and the TAWS option is installed TAWS will not be available A white TAWS N A or red TAWS FAIL annunciator will be displayed on the PFD left of selected altitude or on the MFD TAWS page lower right hand corner If the GPS NAV LOST annunciation is displayed the system will flag and no longer provide GPS based navigational guidance The crew should revert to the G1000 VOR ILS receivers or an alternate means of navigation other than the G1000 GPS receivers If the LOI Loss of Integrity annunciation is displayed in the enroute oceanic or terminal phase of flight continue to navigate using the GPS equipment or revert to an alternate means of navigation other than the G1000 GPS receiver appropriate to the route and phase of flight When continuing to use GPS navigation position must be verified every 15 minutes using the G1000 VOR ILS receiver or another IFR approved navigation system If the ABORT APR or GPS NAV LOST annunciation is displayed while on an approach segment the pilot shall initiate the missed approach Aircraft equipped with GIA 63W WAAS GPS receivers only If the APR DWNGRADE annunciation is displayed the pilot shall use LNAV minima Aircraft equipped with GIA 63 non WAAS GPS receivers only If the RAIM UNAVAIL annunciation is displayed while on an approach segment the approach will become inactive and the pilot shall initiate the missed approach Missed
7. 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 e Communications frequency volume and squelch knob e Communications frequency set knobs e Communications frequency transfer button e Altimeter setting knob baro set e Course knob e Map range knob and cursor control e FMS control buttons and knob e PFD softkey buttons including master warning caution acknowledgement e Altitude reference set knob e Heading bug control e Navigation frequency transfer button e Navigation frequency set knobs e Navigation frequency volume and Identifier knob 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 Emergency or Abnormal Procedures Sections of the AFM or this Supplement for the appropriate procedure to follow for each message 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 190 00492 11 Rev 8 Diamond DA 4
8. rapidly move to RICH 8 Ol Pressure irr n e O green arc within 15 sec WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 9 ALT alternator SWitCh sencese iniiis snr e tii i A T a ON 10 AMmeter ioiei serari ensa eseese Da EDE OE ESSEE EOE ER RSE E SEERE eE EOS Check 11 Fuel pressure sisivc scsstessussssessseneiderystescttttsstesss Check no messages illuminated 12 Annunciator section Of PFD seseesseeesssreeessesersresrsessesreseesessreeessrseesee Check 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F STARTING ENGINE DA 40 F only a Cold engine pt Strobel Shit ACIS ea ee Rea EE AERE RAES aR ON MAUI 5 eset era eran ated aaa pene a Eeee EE a SSE fully RICH Electrical fuel pump seeeseeeeesesesesesresrsrerrererrsrsrsrerrerse ON note pump noise EA E EE AEE E AT functional check of pump Throttle reoni e E AER travel forward from IDLE PHMC ech aiieneiatia urna aon nnimouuaaer 1 4 seconds electric pump WARNING Use the primer system to prepare the engine for a starting attempt Do not use the throttle to pump fuel through the carburetor to the engine for priming since this may lead to carburetor fire The primer system delivers fuel to the cylinders directly CAUTION The priming system is
9. seconds after starting SWITCH OFF THE ENGINE and investigate problem 10 ALT alternator switch c ccc cccccccssccesecessceceseceesceseceessecseeeeeseeseeeeeaeens ON Ti Ammeter minnn e a E Ea E EE E E E aS Check 12 Annunciator section Of PFD ccc cc cccecessessccseessssscsecseeesessessesseseees Check b Warm engine I Strobe light ACL oreta iaia e ah ee aig Moni ap ON 2e Mixture i322 ade aig le Ala ai Eade ee fully RICH 3 Electrical fuel pump eee eeesseceeceseeeeeseeeeeseeneeees ON note pump noise EES E AEE E E E E AE functional check of pump A Throttle im aE travel forward from IDLE WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts Ss Starter sine tid ood Ravi ial E sed Sie es engage When engine starts 6 Oil pressures in o5 ik Maite he ee ieee era green arc within 15 sec dy Throttle ne ee Ge A set 1000 RPM 8 Electrical fuel pump sce css eaa a N a EE Ea OFF WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF THE ENGINE and investigate problem 9 ALT alternator SWitCh sinceri ann
10. that VOR LOC GS navigation data is selected and presented on the CDI of the pilot flying i e proper CDI source selection NOTE Not all published approaches are in the AVIATION database The flight crew must ensure that the planned approach is in the database 9 Use of the G1000 VOR ILS receiver to fly approaches not approved for GPS requires VOR ILS navigation data to be present on the display 10 When conducting missed approach procedures autopilot coupled operation is prohibited until the pilot has established a course and rate of climb that ensures all altitude and path requirements of the procedure will be met RNP operations are not authorized except as noted in the Operational Approvals section TERRAIN AWARNESS AND WARNING SYSTEM TAWS SYSTEM LIMITATIONS NOTE The terrain display is intended to serve as a situational awareness tool only It may not provide either the accuracy or fidelity or both on which to solely base decisions and plan maneuvers to avoid terrain or obstacles 1 Navigation must not be predicated upon the use of the TAWS Terrain or Obstacle data displayed by the G1000 2 Pilots are authorized to deviate from their ATC clearance to the extent necessary to comply with terrain obstacle warnings from TAWS 3 The Terrain and Obstacle databases have an area of coverage as detailed below 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 3 FAA APPROVED AIRPLANE FLIG
11. used as an airport moving map display AMMD SafeTaxi and Chartview are to be used by the flight crew to orient themselves on the airport surface to improve situational awareness during ground operations Do not move the aircraft until the AHRS has aligned and displays valid attitude information on the PFD after the G1000 system has been turned on G1000 GPS NAVIGATION SYSTEM LIMITATIONS 1 GPS SBAS based IFR enroute oceanic and terminal navigation is prohibited unless the pilot verifies and uses a valid compatible and current Aviation database or verifies each waypoint for accuracy by reference to current approved data GPS or GPS and RNAV GPS instrument approaches using the G1000 System are prohibited unless the pilot verifies and uses the current Aviation database GPS based instrument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the Aviation database Instrument approaches utilizing the GPS receiver must be conducted in the approach mode LNAV LNAV V L VNAV or LPV and GPS W AAS integrity monitoring must be available at the Final Approach Fix If there is not sufficient GPS WAAS integrity at any time after crossing the Final Approach Fix a Loss Of Integrity LOI will be annunciated on the HSI and the approach mode will be aborted Only applicable to GIA 63W equipped aircraft When operating under instrument flight rules requiring an alternat
12. 0 DA 40F 7 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Guide and Cockpit Reference Guide for descriptions of the messages and recommended actions if applicable Trend vectors 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 red DISPLAY BACKUP button at the bottom of the audio panel Manual display backup mode is engaged when the button on the audio panel is OUT In the composite mode the full crew alerting function remains 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 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 the last 2 1 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 The Attitude and Hea
13. A NORMAL PROCEDURES NOTE Readability of the PFD and MFD displays may be degraded when wearing polarized sunglasses DETAILED OPERATING PROCEDURES Normal operating procedures for the G1000 are described in the Garmin G1000 Cockpit Reference Guide and the Garmin G1000 Pilot s Guide PRE FLIGHT INSPECTION I Cabin check a MET NAV Mass amp CG osiers flight planning complete b Airplane document eecceeeeeeeeeceeeeeteeeseenneeeee complete and up to date c Dgmition key coc seccbecsescees a e e a E ESER S pulled out d Front canopy amp rear doof ssesssseesseeesseesesererssrrrrssesrresesrees clean undamaged e All electrical equipment esesssessseeieseesstserrtererserrtrrersrsesrrrreresssrsrsrereerse OFF f Circuit breakers eee set in if one has been pulled check reason g Engine control levers c e check condition freedom of movement peice te Bl aN cea i atthe celts Ne anda ste Nae og I E E EAO Full travel of throttle EEE bes ee E A T Full Travel of RPM DA 40 only EA E EE E S A E E E A Full Travel of mixture lever Wo Throttle imena nia E e eal eee IDLE i Mixture control lever ooseoesenssesessseeeeseoseereesssreessrrsessersenreessereesseensn LEAN J RPM lever DA 40 only ainoina a HIGH RPM k Carburetor Heat DA 40 F only eeeeeeeceencecsseceeneeceseeeneecseeenees COLD D BATF battery Swie iraner ena te tot sit ec ckaceteb vous A R G dots ON M Fuel Quantity serccenieci
14. F 4A 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F b Warm engine 1 Strobe light ACL nanais ioeie nierit Side eea ieee Seeks ON 2 Electrical fuel PUMP 0 eee eect ceeceeeeeceeeeeeeeeneeeeens ON note pump noise functional check of pump 32 Whrottle A ieee ea a atte ee 3 cm 1 2 in forward from IDLE measured from rear of slot 4 Mixture control lever ceececseseceesteeee RICH for 1 3 sec then LEAN WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts Sim Memitiom switch sss casts tesavesscicchestedechass castastdad taskseeranteltvdescanets edetecssess START When engine starts 6 Mixture control lever ecceseseeseeeeeceeeeneeeseeeeeeesees rapidly move to RICH Te Ql POSS ULES in a a E green arc within 15 sec WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 8 Electrical fuel pump nimara iina n aa ia OFF 9 ALT alternator switch c cee ccecccssccessceeeecessceeseeseeeeesseceeeee
15. FD AUX GPS STATUS page to determine the state of the GPS receivers Enroute and Terminal including RNP5 BRNAV and PRNAV RNP 1 In accordance with JAA TGL 10 Rev 1 ACJ 20X4 AC 90 96A and AC 90 100A provided the FMS is receiving usable navigation information from one or more GPS SBAS receivers The G1000 Integrated Avionics system as installed in this aircraft is eligible for B RNAV in accordance with AMJ20X2 The G1000 Integrated Avionics system as installed in this aircraft is eligible for PRNAV in accordance with PRNAV requirements JAA Administrative amp Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No 10 Airworthiness and Operational Approval for Precession RNAV Operations in Designated European Airspace 7 1 Required Functions Navigation information is referenced to WGS 84 reference system and should only be used where the Aeronautical Information Publication including electronic data and aeronautical charts conform to WGS 84 or equivalent 190 00492 11 Rev 8 Diamond DA 40 DA 40F 1 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F ELECTRONIC FLIGHT BAG The G1000 Integrated Avionics System as installed in this aircraft has been approved as a Hardware Class 3 Software Type B Electronic Flight Bag EFB in accordance with AC 120 76B when using current FliteChart or ChartView data Addit
16. Garmin Ltd Or its subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA Document No 190 00492 11 FAA APPROVED FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Reg No S N This Supplement must be attached to the FAA Approved Airplane Flight Manual when the Garmin G1000 Integrated Avionics System is installed in accordance with STC SA01444WI D The information contained herein supplements the information of the basic Airplane Flight Manual For Limitations Procedures and Performance information not contained in this Supplement consult the basic Airplane Flight Manual Note This Airplane Flight Manual Supplement follows the format and content of the Airplane Flight Manual for the Diamond DA 40 for consistency and ease of use Note This Airplane Flight Manual Supplement supersedes all previously approved G1000 Airplane Flight Manual Supplements for DA 40 and DA 40 F including those required by STC SAOQ1254WI D ZL Robert Murra ODA STC Unit Administrator Garmin International ODA 240087 CE Date gt oe 190 00492 11 Rev 8 Diamond DA 40 DA 40F i This page is intentionally blank 190 00492 11 Rev 8 Diamond DA 40 DA 40F ii Garmin Ltd Or its subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONIC
17. HT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F a The Terrain Database has an area of coverage from North 90 Latitude to South 90 Latitude in all longitudes b The Obstacle Database coverage area includes the United States and Europe NOTE The area of coverage may be modified as additional terrain data sources become available 4 When replacing or updating the TAWS terrain and obstacle database cards the following procedure must be conducted e The G1000 system must be turned off e After database card replacement apply power to the G1000 system to perform a TAWS system test A successful TAWS system test will result in the aural TAWS SYSTEM TEST OK message being played and removal of the TAWS TEST annunciator from the PFD and MFD displays Note the cockpit speaker must be ON or a headset worn to hear the TAWS aural message e Turn the G1000 system off 5 To avoid unwanted alerts TAWS must be inhibited when landing at an airport that is not included in the airport database 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F TRAFFIC AVOIDANCE SYSTEM LIMITATIONS Use of the MAP TRAFFIC MAP to maneuver the airplane for traffic avoidance without outside visual reference is prohibited The Traffic Informa
18. HT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F The equipment available on Essential Bus only operating on battery only and the Essential Bus switch selected is Air Data Computer airspeed altitude vertical speed OAT TAS Attitude and Heading Reference System attitude heading PFD in composite mode Pitot Heat Flaps COM1 GPS NAV 1 Transponder Landing light Instrument flood lights Engine instruments Starter Refer to the Essential Bus area of the circuit breaker panel for a quick reference to equipment on the Essential Bus Equipment available on the Main and Avionics Busses only Com 2 GPS Nav 2 MFD Electric fuel pump Instrument lights Strobe lights Position lights Taxi light Refer to the Main Bus and Avionics Bus areas of the circuit breaker panel for a quick reference to equipment on those busses 3 7 1 ICING Unintentional flight into icing conditions 1 Leave the icing area by changing altitude or turning back in order to reach zones with a higher ambient temperature 2 lt Pitotheating nonesa oea ee E E EAR EEEREN EE SR ON 3 C bir heat wns acca nia iin reat a ainte eea E aa eai EESE ESEA maha ON 4 Air distribution lever cccccccccsccesccssccssecssecssecssecscescssecesscesecsseeseenee A UP De A AA E E E E increase in order to prevent ice build up on the propeller blades 6 Alternate Air DA 40 only 2
19. Long Range Tanks 8 US gal approx 30 3 liters 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 2 15 Limitation Placard Below the MFD next to the fuel quantity indication Standard Tanks Fuel qty Indication max 17 US gal Max difference LH RH tank 10 US gal For use of max tank capacity see AFM Long Range Tanks Fuel qty Indication max 24 US gal Refer to AFM to use entire tank capacity Max difference LH RH tank 8 US gal 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 11 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 3 EMERGENCY PROCEDURES GENERAL 1 If Garmin G1000 GPS navigation information is not available or invalid utilize remaining operational navigation equipment as required If the G1000 system reverts to Dead Reckoning mode indicated by DR displayed on the HSI the moving map will continue to be displayed Aircraft position will be based upon the last valid GPS position and estimated by Dead Reckoning methods Changes in winds aloft can affect the estimated position substantially Dead Reckoning is only available for 20 minutes in Oceanic and Enroute modes Terminal and Approach modes do not support DR If Garmin G1000 GPS navigation information
20. Manual 190 00492 11 Rev 8 Diamond DA 40 DA 40F 5 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 6 WEIGHT AND BALANCE Refer to the Aircraft Flight Manual and see current weight and balance data 190 00492 11 Rev 8 Diamond DA 40 DA 40F 6 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 7 SYSTEM DESCRIPTIONS G1000 SYSTEM The Garmin G1000 Integrated Avionics System consists of a Primary Flight Display PFD a Multi Function Display MFD an Audio Panel and Attitude and Heading Reference System AHRS an Air Data Computer ADC and the 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 an Automatic Direction Finder ADF receiver Distance Measuring Equipment DME and an integrated annunciation system to alert the pilot of certain abnormal conditions The GPS receivers will either be non WAAS capable if GIA 63 units are installed or WAAS capable if GIA 63W units are installed The Primary Flight Display PFD 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
21. Optional TAWS system is installed TAWS CAUTION When a TAWS CAUTION occurs take positive corrective action until the alert ceases Stop descending or initiate either a climb or a turn or both as necessary based on analysis of all available instruments and information TAWS WARNING If a TAWS WARNING occurs immediately initiate and continue a climb that will provide maximum terrain clearance or any similar approved vertical terrain escape maneuver until all alerts cease Only vertical maneuvers are recommended unless either operating in visual meteorological conditions VMC or the pilot determines based on all available information that turning in addition to the escape maneuver is the safest course of action or both TAWS INHIBIT The TAWS Forward Looking Terrain Avoidance FLTA and Premature Descent Alerts PDA functions may be inhibited to stop alerting for acceptable flight conditions such as below glideslope maneuvers For detailed operating instructions regarding the G1000 TAWS Option refer to the Garmin DA 40 DA 40F Pilot s Guide 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 13 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 4B ABNORMAL PROCEDURES 4B 3 FAILURES IN THE ELECTRICAL SYSTEM a Low voltage caution LOW VOLTS This caution is indicated when the normal on board bus voltage 28V drops below 24
22. S SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F LOG OF REVISIONS Revision Page FAA Date of Number Number s Description Approved Approval 1 All Initial Release Robert 7 26 2007 Murray All Add Software Levels 9 6 2007 Murray All Add Software Levels 2 28 2008 Murray All Add Software Levels Robert 4 4 2008 Murray Update Software Levels Robert EJ All Add Software Levels Robert 9 11 2009 Murray 7 Revised by Garmin ODA Correct minor typographical errors and administrative 9 21 2010 9 21 2010 corrections to fuel quantity indication range markings Incorporate revisions for system software level See Page 1 See Page 1 0321 23 190 00492 11 Rev 8 Diamond DA 40 DA 40F iii This page is intentionally blank 190 00492 11 Rev 8 Diamond DA 40 DA 40F iv FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Table of Contents SECTION 1 GENERAL cccssssssssessesessersssessesessersesessersesessessesessersesecsersesees 1 1 SECTION 2 LIMITATIONS cscsssssssssssssssssssssessessssersesessersesessersesessersesees 2 1 SECTION 3 EMERGENCY PROCEDUREG cssssssssssessssesserseseesersevees 3 1 SECTION 4A NORMAL PROCEDURES cccccssssssssssessessrsessessrsesserees 4A 1 SECTION 4B ABNORMAL PROCEDUREG cscssssssssessrsessessrsesserees 4B 1 SECTION 5 PERFORMANCE ccsssssssssss
23. The primary function of the MFD is to provide engine information mapping terrain information and flight planning The audio panel is used for selection of radios for transmitting and listening intercom functions and marker beacon functions The primary function of the VHF Communication portion of the G1000 is to enable external radio communication The primary function of the VOR ILS Receiver portion of the equipment is to receive and demodulate VOR Localizer and Glide Slope signals The primary function of the GPS portion of the system is to acquire signals from the GPS system satellites and WAAS satellites if so equipped recover orbital data make range and Doppler measurements and process this information in real time to obtain the user s position velocity and time If the optional TAWS function is installed in the G1000 the pilot will receive appropriate aural warnings and cautions for terrain and obstacles The pilot should refer to the DA 40 DA 40F Pilot s Guide for the terrain warning and caution messages and system information 190 00492 11 Rev 8 Diamond DA 40 DA 40F 1 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Operational Approvals G1000 GPS NAVIGATION SYSTEM GIA 63 INSTALLED GIA 63 units are standard and provide position information in accordance with TSO C129a class Al The Garmin G1000 system has been demonstrated cap
24. V Possible reasons are A fault in the power supply RPM is too low i Low voltage caution on the ground 1 Engine speed a a cies acccihavea nish tives ear aca nua 1200 RPM 2 Electrical equipment e ienen a a a e aie eee OFF 3 Ammeter and voltmeter nisinsin asini anait check If the caution message does not extinguish and the ammeter legend flashes and ammeter gauge reads zero discontinue the flight ii Low voltage caution during flight 1 Electrical equipment saisin ainni naea OFF if not needed 2 Ammeter and Voltmeter i srme irinen e i E EEE check If the caution message does not go out and the ammeter legend flashes and ammeter gauge reads zero follow procedure 3 7 2 b Alternator Failure in this Supplement Gii Low voltage caution during landing Follow i after landing 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4B 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F AVIONICS COOLING FAN FAILURES NOTE These caution messages are indicated when a cooling fan has failed The avionics may overheat especially in hot temperatures a PFD FAN FAIL caution ON GROUND 1 Do not takeoff in night or in instrument meteorological conditions IN FLIGHT 1 Monitor for PFD OVERHEAT caution message b MFD FAN FAIL caution ON GROUND 1 Do not takeoff in night or in instrument meteorological conditions wm
25. X over the attitude area AIRSPEED FAIL Display system is not receiving airspeed input from the air data computer accompanied by a red X through the airspeed display ALTITUDE FAIL Display system is not receiving altitude input from the air data computer accompanied by a red X through the altimeter display VERT SPEED FAIL Display system is not receiving vertical speed input from the air data computer accompanied by a red X through the vertical speed display HDG Display system is not receiving valid heading input from the AHRS accompanied by a red X through the digital heading display Red X A red X through any display field such as COM frequencies NAV frequencies or engine data indicates that display field is not receiving valid data LOI GPS integrity is insufficient for the current phase of flight 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 3 2 3 ENGINE PROBLEMS IN FLIGHT h High Fuel Flow DA 40 only Fuel flow in red sector 1 Fuel pressure oricine check for red FUEL PRESS LO message e If fuel pressure is low FUEL PRESS LO message there is possibly a leak between the injection system and the injectors Land at the nearest available airport e If there is no FUEL PRESS LO message there is no leak the likely cause is a defective fuel flow indication which sh
26. a A e a ATER S Emergency window s Use standby instruments for airspeed altitude and attitude reference if necessary Land at the nearest suitable airport as soon as possible If electronic or avionics equipment is required for continued flight the following procedure may be used to isolate the source of the smoke or fumes BAT battery S Witch nnne a E A E detente ON ESS BUS SWO inam a S a a a AA o e ON NOTE This removes power from the main and avionics busses but does not allow alternator operation See the table at the end of this section for the equipment which is still available If smoke or fumes decrease 9 Land at the nearest suitable airport as soon as possible If smoke or fumes persist 10 11 12 13 Refer to Section 3 7 2 b of this Supplement Alternator Failure 15 ALT alternator switch ccc ccesceessccesecessseceseceesseseeeecsaecseeeeesaecseeeeeaeens ON ESS BUS Switch cass cece oa epea r ns acest eran EE Baste EEE ENE OFF BATT and ESS TIE circuit breakers ee eeeseeseeeeeseceeeeeeeeeeeeeeeeeeens PULL This removes power from the essential bus and restores power to the main and avionics busses See the table at the end of this section for the equipment which will still be available Use standby instruments for attitude airspeed and altitude Land at the nearest suitable airport as soon as possible 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 4 FAA APPROVED AIRPLANE FLIG
27. able of and has been shown to meet the accuracy requirements for the following operations provided it is receiving usable navigation data The G1000 Integrated Avionics system as installed in this aircraft complies with AC 20 138A for navigation within the U S National Airspace System using GPS for IFR en route terminal area and non precision approach operations including those approaches titled GPS or GPS and RNAV GPS approaches The G1000 Integrated Avionics system as installed in this aircraft has been found to comply with the requirements for GPS as a Primary Means of Navigation for oceanic and remote navigation RNP 10 per FAA AC 20 138A and FAA Order 8400 12A Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval North Atlantic NAT Minimum Navigational Performance Specifications MNPS Airspace per AC 91 49 and AC 120 33 Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval NOTE Each GIA 63 computes an independent navigation solution based on its GPS sensor The G1000 will use the GPS sensor with the highest signal quality and will automatically revert to the other sensor if the active sensor fails or if the secondary sensor i
28. als except for routes requiring only one Long Range Navigation LRN sensor This does not constitute an operational approval The G1000 WFDE predication program works in combination with the Garmin AT Inc Route Planning Software version 1 2 or later approved version The route planning and WFDE prediction program can be 190 00492 11 Rev 8 Diamond DA 40 DA 40F 1 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F downloaded from Garmin G1000 website on the Internet For information on using the WFDE Prediction Program refer to Garmin WAAS FDE Prediction Program part number 190 00643 01 WFDE Prediction Program Instructions North Atlantic NAT Minimum Navigational Performance Specifications MNPS Airspace per AC 91 49 and AC 120 33 Both GPS SBAS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval NOTE Each GIA 63W computes an independent navigation solution based on its GPS sensor The G1000 will use the GPS sensor with the highest signal quality and will automatically revert to the other sensor if the active sensor fails or if the secondary sensor is determined to be more accurate An AHRS 1 GPS message displayed in the ALERTS window means that one of the GPS receivers has failed Refer to the M
29. and floodlight This battery is switched on with the HORIZON EMERGENCY Switch It provides power for 1 hour and 30 minutes when the floodlight is switched on 3 8 AVIONICS EMERGENCIES 3 8 1 PFD OR MFD DISPLAY FAILURE a DISPLAY BACKUP button on audio panel PUSH button shall be OUT 3 8 1 1 AUTOMATIC ENTRY OF DISPLAY REVERSIONARY MODE If the PFD and MFD have automatically entered reversionary mode use the following procedure a DISPLAY BACKUP button on audio panel PUSH button shall be OUT NOTE After automatic entry of reversionary mode it is required to press the DISPLAY BACKUP button on the audio panel With the DISPLAY BACKUP button pushed if the problem causing the automatic entry of reversionary mode is resolved the system will remain in reversionary mode A maximum of one attempt to return to normal mode may be made using the following procedure b DISPLAY BACKUP button on audio panel PUSH button shall be IN e If the system returns to normal mode leave the DISPLAY BACKUP button in and continue e If the system remains in reversionary mode or abnormal display behavior such as display flashing occurs then return the DISPLAY BACKUP button to the OUT position 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 3 8 2 AHRS FAILURE NOTE A failure of the Attitude and Headi
30. approach course guidance may still be available with 1 nautical mile CDI sensitivity 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 9 In an in flight emergency depressing and holding the COM transfer button 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 10 If the white TAWS N A status annunciator is displayed on the PFD or MFD TAWS page the system will no longer provide TAWS alerting or display relative terrain elevations The crew must maintain compliance with procedures that ensure minimum terrain separation 11 If the red TAWS FAIL status annunciator is displayed on the PFD or MFD TAWS page the system will no longer provide TAWS alerting or display relative terrain elevations The crew must maintain compliance with procedures that ensure minimum terrain separation 12 The following warnings and cautions appear in various locations on the PFD or MFD Annunciation Cause AHRS Aligning Keep Attitude and Heading Reference System is aligning Wings Level Keep wings level using standby attitude indicator ATTITUDE FAIL Display system is not receiving attitude reference information from the AHRS accompanied by the removal of sky ground presentation and a red
31. assengers renere a E a E R rreeeiate Instructed 4 Safety Harnesses nieno a eene Ea aiken ieaS All on and fastened S Reat doors nisi 6 2506 Gi8 aa Le See i ee Closed and locked 6 Door lock if installed ec ceeeeseceteeeeseeeeee Unblocked key removed Tic FROMU CANOPY A Position 1 or 2 cooling gap 8 Canopy lock if installed oo eee eeeeeeereeeeeees Unblocked key removed 9 Parking brake coros ti bien en oneness Set 10 Flight controls eee Freedom of movement and proper direction TI Tim wheel rnnr nti th ieee ee a ts eee ee T O 12 Friction device throttle quadrant cccecceesceesceesceeeceeeeeseeeeenseeaee Adjusted 13 RAPOtH G2 oes erencseb ia eee ar A a re tube r E A A tubes IDLE 14 Mixture control lever oo eee ceesecseeeeessceecesececesecneeseeneeeeesaecesnecaeeseens LEAN 15 RPM lever DA 40 only oo eee eeceeeeceseeeceecneeeecaeeeesaesaeeseeneeaes HIGH RPM 16 Carburetor heat DA 40 F only eee eeee ce eeeccesncecseeceeeeeceeeeeeeeceeeeeeneees COLD 17 Alternate air DA 40 only ceeceecseesceesceeeceeeceseceaeceneceeenseenseeneeeas CLOSED 18 Alternate Static Valve uo ecccccccccssececessceceessseecesaees CLOSED if installed 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 19 Avionics master switch parsoni aea E AEE Ea OFF 20 Essential Bus switch vrari cre i A ey
32. ater approved version and GA35 PN 013 00235 00 antennas are approved under TSO C145a TSO C146a equipment Class 3 and installed in accordance with AC 20 138A The Garmin G1000 system has been demonstrated capable of and has been shown to meet the accuracy requirements for the following operations provided it is receiving usable navigation data The G1000 Integrated Avionics system as installed in this aircraft complies with AC 20 138A for navigation using GPS and WAAS within the coverage of a Space Based Augmentation System complying with ICAO Annex 10 for IFR en route terminal area and non precision approach operations including those approaches titled GPS or GPS and RNAV GPS approaches The G1000 Integrated Avionics system installed in this aircraft is approved for approach procedures with vertical guidance including LPV LNAV VNAV and LNAV V within the U S National Airspace System The G1000 Integrated Avionics system as installed in this aircraft has been found to comply with the requirements for GPS as a Primary Means of Navigation for oceanic and remote navigation RNP 10 per FAA AC 20 138A and FAA Order 8400 12A when used in conjunction with Garmin WAAS Fault Detection Exclusion WFDE Prediction Program part number 006 A0154 01 or later approved version with GA35 PN 013 00235 00 antennas selected Both GPS SBAS receivers are required to be operating and receiving usable sign
33. buretor Heat DA 40 F only cee eeeceereeeseceeneeenaeeeeees check function 18b Throttle DA 40 F only MAX PWR minimum 2200 RPM NOTE DA 40 F only The result of the ground check at full throttle depends on a number of environmental factors e g temperature ambient air pressure and in particular head or tailwind components Headwind will cause a higher RPM than tailwind 19 Throttle iarsan sistas keratin dite aici E EE E E set 1000 RPM 20 Carburetor Heat DA 40 F only sesseseseeseeesesesrsesssessresrseesee check COLD 21 Alternate Air DA 40 only ssssessssseressssssssrserssessssrsesses check CLOSED 22 Flight a e a P E S E cess entered 237 Altimeter seting kssr ean r e atid ete rete checked set G1000 and standby altimeter 24 Altitude preselector nseseesseserseesessesetssesetetsseeeessreerssesersteseeeesseeeessesees set 252 Radi0s ena arn REE O A RER set and checked 26 Tra spondet s e rnoet eripias aaee REE e KEE EE a E aie code set 21 Standby attitude Cyro oe ee ceeeeceeeseceseeeeeseceeeeeeereeeeaees erect and no flag 28 gt Parking brakes innn Aes tire tiene eeebeewe the eee release 29 MManding We ht t22 ties sscics aetieuses sets catedisbs aeaa TE a EE ON as required 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 12 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F AFTER TAKEOFF TAWS NORMAL PROCEDURES If
34. ce nenesa e check fuel qty on EIS a E RAR check with fuel qty measuring device 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F NOTE FOR STANDARD TANKS when the fuel quantity indicator reads 17 US gal the correct fuel quantity must be determined with the fuel quantity measuring device If this measurement is not carried out the fuel quantity available for flight planning is 17 US gal FOR LONG RANGE TANKS when the fuel indicator reads 16 US gal the correct fuel quantity must be determined with the fuel quantity measuring device There are 3 US gal of un gauged fuel from 16 to 19 US gal If this measurement is not carried out the fuel quantity available for flight planning is 16 US gal n Position lights strobe light ACLS ececseesseeseeeseeeeceeseeteeeeeeseenneeaes check o BAT battery switch 20 0 0 cee cecceeceesseesceesceeeceeeceseceseeesecnaeceaecaeecaeeeneenneees OFF P Check for loose items iiini ni e i e E complete q Flight controls and trim eeseseesseeeeseesessesersersereeee free to move and correct f Baggage nine o a bee tons T AE stowed and secure NOTE Refer to DA 40 and DA 40 F AFMs to complete the Walk around check visual inspection BEFORE STARTING ENGINE 1 Preflight inspection isene n a a i a a Complete 20 Rudder pedals insonne as Adjusted and locked 3 P
35. ding 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 aircraft is in motion but will align more quickly if the wings are kept level during the alignment process 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 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 190 00492 11 Rev 8 Diamond DA 40 DA 40F 7 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 7 10 FUEL SYSTEM Fuel Quantity Indication Each fuel tank has a capacity probe that ascertains fuel quantity in that tank Standard Tank configurations have two fuel probes one in each wing Long Range Tank configurations have four fuel probes two in each wing an outboard tank and an inboard tank When the fuel quantity indicator r
36. e airport the required alternate airport must not be flight planned based on an RNAV GPS LP LPV or LNAV VNAV approach The alternate airport must be flight planned using an LNAV approach or available ground based approach aid Only applicable to GIA 63 non WAAS equipped aircraft The aircraft must have operational approved navigation equipment other than GPS appropriate to the operation Only applicable to GIA 63 non WAAS equipped aircraft When operating under instrument flight rules requiring an alternate airport the required alternate airport must have an approved instrument approach procedure other than GPS that is anticipated to be operational and available at the estimated time of arrival and which the aircraft is equipped to fly 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F IFR non precision approach approval using the GPS SBAS sensor is limited to published approaches within the U S National Airspace System Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority Use of the Garmin G1000 GPS SBAS receivers to accomplish ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for or GPS is not authorized Use of the G1000 VOR LOC GS receivers to fly approaches not approved for or GPS requires
37. eads zero only unusable fuel remains in the tank Usable capacity of each tank for the Standard Tank configuration is 20 US gal 76 liters Usable capacity of an outboard and inboard tank for the Long Range Tank configuration is 24 US gal 91 liters Fuel quantity Fuel quantity indicating for the Standard Tank configuration functions as described in the DA 40 AFM Also refer to the G1000 Pilot s Guide for the Diamond DA 40 for additional information about the functionality of the G1000 s fuel quantity gauge For the Long Range Tank configuration dual pointers on a linear scale a top pointer for the left fuel quantity and a bottom pointer for the right fuel quantity indicate fuel quantity The fuel quantity gauge is marked in five gallon increments starting at zero to 25 US gal The break in the green band between 16 and 19 US gal shows the un gauged portion of the fuel tanks usable fuel When a fuel tank is completely full the quantity pointer will indicate 24 US gallons As fuel is consumed from the tank the pointer will move to the left Once there is no more measurable fuel in the outboard tank the pointer migrates over a 30 second period to the 16 US gal position The pointer will remain at 16 US gallons while the un gauged fuel quantity is consumed Once the quantity of fuel remaining in the inboard tank is less than 16 gallons the pointer will begin moving left towards zero When either pointer enters the amber portion of
38. eeeeesaeeees OFF then ON If alternator does not come back on line message extinguishes and ammeter indication greater than zero 3 ESS BUS switchin anita paniadi ni Alii aidan aiden ON 4 Switch off any non essential electrical loads 5 Land within 30 minutes If PFD attitude information is lost prior to landing 6 HORIZON EMERGENCY Switch eecseeeceeeeeceseeeeeeceseceeeseeneeeeens ON CAUTION The following items are available on the Essential Bus PFD in composite backup format NAV COM 1 GPS 1 Attitude and Heading Reference System AHRS Air Data Computer Pitot heat Engine instruments Transponder Flood light Landing light Refer to the ESSENTIAL BUS area of the circuit breaker panel for a quick reference to equipment on those busses These items of equipment can be supplied with power by the battery for at least 30 minutes During this 30 minute period the airplane must be landed at a suitable airport Economical use of electrical equipment in particular of pitot heat and switching off equipment that is not needed extends the time during which the other equipment remains available 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F For cases in which the battery capacity is not sufficient to reach a suitable airport an emergency battery is installed to power the standby attitude gyro
39. esaeceeeeeeaeens ON LO Ammetet eiea aar aah Aa E a R Check 11 Fuel pressure ices isis cece sosussesd ateri Check no messages illuminated 12 Annunciator section Of PFD 00 c cc ceceecceesseesceesceeeceseceseeeeeeeeseenaeeneenes Check 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F c Engine will not start after injection flooded engine Warm engine 1 Strobe light ACL aisis ii Ao raian tas Sieh oer ees ON 2 Electrical fuel pump eee eee cseeeeceeeeeeeeeeeeeseeneeees ON note pump noise sigedydbh chit us ebaskabesic shes vevatnentsdstuaeaeasthew S Functional check of pump 3s Mixture control leyers rine eeir eisai eiee LEAN fully aft A BA DTE O A A lE aA ESE EE E E OS at mid position WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts 5 e Teniton switch v 35 ches aia Seis A Aiea oad START 6 Throttle siseses euis pull back towards IDLE when engine starts When engine starts 7 Mixture control lever eccceceseeseceecseeeneeeseeeeeeeeees
40. h latitude at all longitudes c North of 65 North latitude between longitude 75 W and 120 W Northern Canada d North of 70 North latitude between longitude 70 W and 128 W Northern Canada e North of 70 North latitude between longitude 85 E and 114 E Northern Russia f South of 55 South latitude between longitude 120 E and 165 E Region south of Australia and New Zealand NOTE The Garmin G1000 system is not designed for use as a polar navigator and operation outside the approved operating area is prohibited The GRS 77 AHRS internally monitors the magnetic field and will display a GEO LIMITS system message when the magnetic field becomes unsuitable for AHRS operation When the AHRS can no longer reliably compute heading heading information will be removed from the HSI 3 The fuel quantity fuel required and fuel remaining functions of the FMS are supplemental information only and must be verified by the flight crew 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F The ADF aural identifier must be monitored any time the ADF is used as the primary source of navigation Do not use SafeTaxi or Chartview functions as the basis for ground maneuvering SafeTaxi and Chartview functions do not comply with the requirements of AC 20 159 and are not qualified to be
41. i lights ON test function as required 12 CAUTION When taxiing at close range to other aircraft or during night flight in clouds fog or haze the strobe lights should be switched OFF The position lights must always be switched ON during night flight Idle RPM 2205s anc stl ak tite Ghat eas check 600 to 800 RPM 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F BEFORE TAKE OFF 1 Position airplane into wind if possible 2 Parking brake eeina ne cassaccheavcalan ancien E r R s avaiaess set 3 Safety harne ss g a a E ora E aaa Aae pe aE EAEE Ein on and fastened Ay Reat COOL eser eee aoe e oi E Eea check closed and locked D5 E KoI 11E 0 10 eA AAR OOE EAS EEEE E S E closed and locked CAUTION When operating the canopy pilots operators must ensure that there are no obstructions between the canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward pressure on the canopy may be required to ease the handle operation 6 Door warning light DOOR OPEN Check no messages illuminated T Fuel tank selector scc cs c ssissstvstssessvessecsepiscdessesssccssnsosstensteasscesdevvess fullest tank 8 Engine instruments esoe e eeter erit srete an EE Eaa in green sector 9 Circuit breakers ss icine
42. ion AND MFD OVERHEAT caution NOTE The PFD and MFD are both approaching operating temperature limits The brightness of both displays is automatically reduced to 50 of maximum 1 Refer to standby attitude heading altimeter and airspeed instruments to maintain aircraft control 2 If either the PFD or MFD fails or is unusable pull the circuit breaker of the affected device and select Display Reversionary Mode using the red DISPLAY BACKUP button on the audio panel 3 Land as soon as practical at a suitable airport 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4B 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F d GIA1 OVERHEAT caution OR GIA2 OVERHEAT caution NOTE Either GIA 1 or GIA 2 is approaching its operating temperature limit 1 Minimize all COM transmissions to reduce temperature e GIA1 OVERHEAT caution AND GIA2 OVERHEAT caution NOTE Both GIA 1 and GIA 2 are approaching their operating temperature limits COM 1 COM 2 NAV 1 NAV 2 GPS 1 and GPS 2 may fail 1 Minimize all COM transmissions to reduce temperature 2 Land as soon as practical at a suitable airport 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4B 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 5 PERFORMANCE No change Refer to the Aircraft Flight
43. ional operational approvals may be required For operations under part 91 it is suggested that a secondary or back up source of aeronautical information necessary for the flight be available to the pilot in the aircraft The secondary or backup information may be either traditional paper based material or displayed electronically If the source of aeronautical information is in electronic format operators must determine non interference with the G1000 system and existing aircraft systems for all flight phases 190 00492 11 Rev 8 Diamond DA 40 DA 40F 1 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 2 LIMITATIONS 2 1 INTRODUCTION GENERAL LIMITATIONS 1 The Garmin G1000 Cockpit Reference Guide CRG must be immediately available to the flight crew The required CRG is referenced to the System Software Version number The System Software Version number is displayed at the top right side of the MFD Power up page System Software Garmin G1000 Cockpit Reference Guide CRG Version revision P N 190 00324 11 Revision B or later appropriate revision 0321 23 2 AHRS Areas of operation Flight operations with the G1000 Integrated Avionics installed are prohibited in the following areas due to unsuitability of the magnetic fields near the Earth s poles a North of 72 North latitude at all longitudes b South of 70 Sout
44. low values 4 Use other system information such as annunciator messages ENGINE SYSTEM page and AUX TRIP PLANNING page to safely complete the flight 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 3 8 5 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 If an annunciator appears treat it as if the condition exists Refer to the AFM Emergency or Abnormal procedures or the procedures contained in this AFMS 2 If a display indicates an abnormal condition but no annunciator is present use other system information such as engine displays ENGINE SYSTEM page GAL REM and FFLOW GPH displays 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 AFM Emergency or Abnormal procedures or the procedures contained in this AFMS 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 4
45. n air R ON 10 Ammeter cccccccccceeeeseseseseseseseseseseesesssesesesesesesssssesssesseeseeeseseseeeeees Check 11 Annunciator section Of PFD esseseeeeeeseeseeeseseseserreseessreressserrereeeessrsrrees Check 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F c Engine will not start after priming flooded engine NS 5 Strobe light ACD oseink a a E a ESE at ON Electrical file pUmPiscirane nei r E R R aE OFF IA EO nET E A EEE A teseasters LEAN fully aft Tiroteo a a a S OA RS MAX PWR WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts Startel vets nice Gates esee weaves o eE EEEE ciate E Ra engage When engine starts Oy Throttle siepi pull back towards IDLE when engine fires Te OU press re s n e n eae eh a E green arc within 15 sec WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF THE ENGINE and investigate problem Se Ehrottle ccs a E ET set 1000 RPM 9 ALT al
46. ng Reference System AHRS is indicated by 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 Use Standby Attitude Indicator magnetic compass and Navigation Map COULSE i ss55 Shes seese hbysais Sos essncss yoda eadeabstbaaens pbseatase gece Set using digital window 3 8 3 AIR DATA COMPUTER ADC FAILURE Ne 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 Use Standby Airspeed Indicator and Altimeter Land as soon as practical at a suitable airport 3 8 4 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 that 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 from the AFM for approximate fuel f
47. ng its operating MED OVERHEAT temperature limit Display brightness is automatically reduced to 50 of maximum See Abnormal Procedures section 4B GIA1 OVERHEAT GIA2 OVERHEAT GIA 1 is approaching its operating temperature limit See Abnormal Procedures section 4B of the AFMS GIA 2 is approaching its operating temperature limit See Abnormal Procedures section 4B of this AFMS 190 00492 11 Rev 8 FAA APPROVED Diamond DA 40 DA 40F 2 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 2 13 KINDS OF OPERATION Minimum operational equipment serviceable Number VFR VFR Equipment installed Day Night IFR Primary Flight Display 1 1 1 1 Multi Function Display 1 1 1 1 Audio panel 1 1 1 1 Air data computer 1 1 1 1 Attitude and Heading Reference 1 0 1 1 System Static dischargers 7 0 0 7 GPS 2 0 1 2 PFD Cooling Fan 1 0 1 1 MED Cooling Fan 1 0 1 1 GIA Cooling Fan 1 0 1 1 2 14 FUEL Fuel Quantity Total fuel quantity Standard Tanks 2 x 20 6 US gal approx 156 liters Long Range Tanks 2 x 25 5 US gal approx 193 liters Unusable fuel 2x 0 5 US gal approx 3 8 liters Max Indicated Fuel Quantity Standard Tanks 17 US gal per tank Long Range Tanks 24 0 US gal per tank Max permissible difference between right and left tank Standard Tanks 10 US gal approx 38 liters
48. not intended for operation in flight WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts CAUTION The use of an external pre heater and external power source is recommended whenever possible in particular at ambient temperatures below 0 C 32 F to reduce wear and abuse to the engine and electrical system Pre heat will thaw the oil trapped in the oil cooler which can be congealed in extremely cold temperatures After a warm up period of approximately 2 to 5 minutes depending on the ambient temperature at 1500 RPM the engine is ready for takeoff if it accelerates smoothly and the oil pressure is normal and steady Starte aii n E E A SS engage 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F When engine starts Tey OUP SSU E reneisse enee Er E green arc within 15 sec 8 ThrottlE na aen eeens onse aseko e aer eose De E eE EE ES set 1000 RPM 9 Electrical fuel pump iniaiaiai aa at OFF WARNING If the oil pressure has not moved into the green arc within 15
49. nunciations Red Annunciation Cause OIL PRES LO Oil pressure is less than 25 psi FUEL PRES LO DA40 Only Fuel pressure is less than 14 psi FUEL PRES HI DA40 Only Fuel pressure is greater than 35 psi ALTERNATOR Alternator failure Operation of the starter without the key in the start position or failure of the starter STEEP motor to disengage from the engine after starting Front canopy and or rear door not DOOR CEEN completely closed and locked 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Caution annunciations Yellow Annunciation Cause PITOT OFF Pitot heat is not switched on PITOT FAIL Fault in the pitot heating system Fuel quantity in the left tank is less than 3 LOREM US gal 1 US gal Fuel quantity in the right tank is less than 3 cinema US gal 1 US gal LOW VOLTS On board voltage below 24 volts PED FAN FAIL PFD Cooling Fan has failed See Abnormal Procedures section 4B MED FAN FAIL MFD Cooling Fan has failed See Abnormal Procedures section 4B GIA FAN FAIL GIA Cooling Fan has failed See Abnormal Procedures section 4B PFD is approaching its operating PFD OVERHEAT temperature limit Display brightness is automatically reduced to 50 of maximum See Abnormal Procedures section 4B MFD is approachi
50. ould thus be ignored the airplane should be serviced Fuel flow data should be taken from the engine performance table in Chapter 5 of the AFM g High Fuel Flow DA 40 F only 1s Fuel Quantity sspctsie eiasetsies Shassveteisetieyitisss Check and Monitor 2 Power Sette tis sates andesite E E Check Land as soon as practical Consider the reduced range and endurance due to possible loss of fuel NOTE Have the airplane inspected before next flight 3 3 3 SMOKE AND FIRE IN FLIGHT b Electrical fire with smoke in flight I Emergency Switchinis 2 oisiitindanikiieeninittecanaian ON if installed CAUTION Switching OFF the master switch ALT BAT will lead to total loss of all electronic and electric equipment including the AHRS and attitude display However by switching the HORIZON EMERGENCY switch ON the emergency battery will supply power to the standby attitude gyro artificial horizon and the flood light In case of extreme smoke development the front canopy may be unlatched during flight This allows it to partially open in order to improve ventilation The canopy will remain open in this position Flight characteristics will not be affected significantly 190 00492 11 Rev 8 Diamond DA 40 DA 40F 3 3 SA al m FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Master switch AL TBA T t e a e a E OFF Cabin heaton ra a ce
51. range range range range Manifold Pressure in Hig 13 30 Note 2 500 gt 2700 EEM 5 2700 Note 3 Oil Temp oF 149 230 231 245 gt 245 Cylinder Head 476 Temp 150 475 a gt 500 oF 500 Fuel Press PSI DA 40 0 14 14 35 gt 35 Note 4 Salis 0 25 25 55 56 95 96 97 gt 97 Fuel flow Gal hr 1 20 gt 20 oe 0 24 1 24 1 25 251 30 30 1 32 gt 32 Volts Amperage _ 2 75 Amps Fuel quantity US gal Standard 0 gt 0 3 gt 3 17 Tanks Fuel quantity US gal gt 3 16 Long Range 9 pene gt 19 24 k Tanks 190 00492 11 Rev 8 Diamond DA 40 DA 40F FAA APPROVED 2 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Note 2 Not applicable to DA 40 F Manifold Pressure gauge is not installed in the DA 40 F Note 3 To prevent nuisance alerts during normal takeoffs the legend RPM and digits will not turn red or flash until the RPM exceeds 2780 Note 4 Fuel Pressure Gauge is optional for DA 40 aircraft 2 6 WARNING CAUTION AND STATUS MESSAGES The following tables show the color and significance of the warning caution and advisory messages which may appear on the G1000 displays NOTE The G1000 Cockpit Reference Guide and the G1000 Pilot s Guide contain detailed descriptions of the annunciator system and all warnings cautions and advisories Warning an
52. s determined to be more accurate An AHRS 1 GPS message means that one of the GPS receivers has failed Refer to the MFD AUX GPS STATUS page to determine the state of the GPS receivers e Enroute and Terminal including RNP5 BRNAV and PRNAV RNP 1 In accordance with JAA TGL 10 Rev 1 ACJ 20X4 AC 90 96A and AC 90 100A provided the FMS is receiving usable navigation information from one or more GPS SBAS receivers The G1000 Integrated Avionics system as installed in this aircraft is eligible for B RNAV in accordance with AMJ20X2 190 00492 11 Rev 8 Diamond DA 40 DA 40F 1 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F The G1000 Integrated Avionics system as installed in this aircraft is eligible for PRNAV in accordance with PRNAV requirements JAA Administrative amp Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No 10 Airworthiness and Operational Approval for Precession RNAV Operations in Designated European Airspace 7 1 Required Functions Navigation information is referenced to WGS 84 reference system and should only be used where the Aeronautical Information Publication including electronic data and aeronautical charts conform to WGS 84 or equivalent G1000 GPS SBAS NAVIGATION SYSTEM GIA 63W INSTALLED The Garmin G1000 GPS SBAS receivers GIA 63W incorporating SW version 3 0 or l
53. ssessessesessersssessersesessersesessesseeees 5 1 SECTION 6 WEIGHT AND BALANCE ccccsssssssesssssssessesessesseseesersesees 6 1 SECTION 7 SYSTEM DESCRIPTIONS csssssssssssssessssessessssersesessersesees 7 1 190 00492 11 Rev 8 Diamond DA 40 DA 40F v This page is intentionally blank 190 00492 11 Rev 8 Diamond DA 40 DA 40F vi FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 1 GENERAL G1000 The G1000 Integrated Avionics System is a fully integrated flight engine communication navigation and surveillance instrumentation system The system consists of a Primary Flight Display PFD Multi Function Display MFD audio panel Air Data Computer ADC Attitude and Heading Reference System AHRS engine sensors and processing unit GEA and dual integrated avionics units GIA each containing VHF communications VHF navigation and GPS Global Positioning System GIA 63 units are standard and provide non WAAS GPS position information in accordance with TSO C129a class Al Optional GIA 63W units provide WAAS augmented GPS position If the optional GIA63W units incorporate GPS software level 3 0 or later the GPS system meets the requirements of TSO C145a The primary function of the PFD is to provide attitude heading air data navigation and alerting information to the pilot The PFD may also be used for flight planning
54. tempts to start the engine let the starter cool for 30 minutes before further start attempts CAUTION The use of an external pre heater and external power source is recommended whenever possible in particular at ambient temperatures below 0 C 32 F to reduce wear and abuse to the engine and electrical system Pre heat will thaw the oil trapped in the oil cooler which can be congealed in extremely cold temperatures After a warm up period of approximately 2 to 5 minutes depending on the ambient temperature at 1500 RPM the engine is ready for takeoff if it accelerates smoothly and the oil pressure is normal and steady 6 Agnition Switch chcnsiecnn N E E e hia START When engine starts 7 Mixture control lever ceceecesceseeeeceeeeeeeeeeeeeeeeees rapidly move to RICH 8 Oil pressure ssa sein ig ncieniaedein a green arc within 15 sec 9 Electrical fuel pump nnen sapen enn se senussshest ssbassoesosdeassosspniasadseuabevease OFF WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 10 ALT alternator switch c ce cccececcescecesseececeeseececesceceeaeeecsesaeeeeneeeeeneaaes ON As AMME isc oR eee ae ae SR ASA Check 12 Fuel pressure issississ cssssesikescesciesaeseazepseeeact Check no messages illuminated 13 Amnunciator section Of PFD 0 cece eeceesecseeeeesecseesecnecaeeseenerseesaeseeeas Check 190 00492 11 Rev 8 Diamond DA 40 DA 40
55. ternator SWitCh ccc ccescscsecesseesssecesscessseseceessecseseessaeceeseeesaeens ON TO SAMIMCtet foe 5ss shee isn eae oe este ee ES Check 11 Annunciator section Of PFD c ccc icceccsceccccceesessssscsseesessessesseseees Check 190 00492 11 Rev 8 Diamond DA 40 DA 40F 4A 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F BEFORE TAXIING 1 Avionics master SWiteh sisie moisis oes deant harira aeeoe ioui e iia hEn hauek ON 2 Electrical equipment sseseseeesesseeesesrsessesesrerrersrserrerrererrsesesree On as required e PAA ET o EEA T R UP T O LDG T O RO E EEE E E E AEE indicator and visual check 4 Flight instruments and avionics 00 set test function as required set both altimeters 5 Flood lightness onn aaa ON test function as required 6 AmmMeEter sciri esiis check if required increase RPM 7 Fueltank selector se neseeeseseeeseesereeeseee change tanks confirm that engine EE E EE E E EEE EEEE E also runs on other tank at least 1 SRR ALA RRS E E A AEEA EE T minute at 1500 RPM 8 Pitot heating neiaie nri ari a ON test function no yellow PITOT FAIL annunciation 9 a Pitot heating e ar tise E a EEE ataoa OFF if not required yellow PITOT OFF annunciation 10 Strobe lights ACLs esssseeesseseesseseresrssesssreesresees check ON test function as required 11 Position lights landing and tax
56. the scale the pointer and the gauge title FUEL QTY GAL will turn amber When either pointer enters the red portion of the gauge the pointer will turn red and the gauge title FUEL QTY GAL will turn red and flash continuously in inverse video 190 00492 11 Rev 8 Diamond DA 40 DA 40F 7 3 Part Information GPN 190 00492 11 Description AFMS G1000 Integ Avionics Sys Diamond DA40 40F No AP Part Type Manuals Printed Literature Lifecycle Phase Experimental Rev 8 ECO 099458 ltem Attribution Document Review Required ARR Item Notes Preferred Rating ESD Sensitive Moisture Sensitive Limited Shelf Life Magnetic Sensitive Item Attribution 1 of 1 Item 190 00492 11 Rev 8 ECO 099458 Creation Date 17 May 2013 12 50 PM CST
57. tion System TIS is intended as an aid for the pilot to visually locate traffic It is the responsibility of the pilot to see and manually maneuver the airplane to avoid other traffic SYNTHETIC VISION LIMITATIONS Use of the Synthetic Vision system display elements alone for aircraft control without reference to the G1000 primary flight instruments or the aircraft standby instruments is prohibited Use of the Synthetic Vision system alone for navigation or obstacle or terrain avoidance is prohibited Use of the SVS traffic display alone to avoid other aircraft is prohibited DATA LINK WEATHER XM AND GFDS WEATHER LIMITATIONS Datalink weather information displayed by the G1000 system is limited to supplemental use only XM and GFDS weather data is not a source of official weather information Use of the NEXRAD and LTNG Lightning data on the MAP NAVIGATION MAP and or MAP WEATHER DATA LINK XM or GFDS page for hazardous weather e g thunderstorm penetration is prohibited NEXRAD and LTNG information on the MAP NAVIGATION or MAP WEATHER DATA LINK XM or GFDS page is intended only as an aid to enhance situational awareness of hazardous weather not penetration It is the pilot s responsibility to avoid hazardous weather using official weather data sources and the airplane s in flight weather radar if installed VERTICAL NAVIGATION VNAV LIMITATIONS Use of VNAV is prohibited with course changes greater than 90
Download Pdf Manuals
Related Search