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Garmin Software Version 0321.22 FAA Approved Airplane Flight Manual Supplement

1. Check no messages illuminated he Fel tank SIC CIOL tscncos cash esscahs eves stabs E e R fullest tank 8 Engine mstruments cscs coleutace ieee cei iene in green sector 9 Circuit breakers innesi hale eae a eee ee Sb Seis es AEn pressed in 10 Fuel pressure iconii eva isha Check no messages illuminated T1 Electric fuel pump iae ss ested reat nee aar RAE Er EE eE E EE ERETTA ON 12 Mixture control lever c cccccesscessecsssceescecssseeseeeeseeeees 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 a a E E check T O 14 A D i a EEE E E E E T E Ashlee check T O 15 Flight contol iniiao ninin ieee free movement correct sense 16 Throttle iniisa a ied E a eS 2000 RPM DA 40 1800 RPM DA 40 F I7 Magneto Checks setn epena odeio iene a TE ESEE Ei save 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 10 Rev 8 Diamond DA 40 DA 40F 4A 10 18 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000
2. FUEL QTY GAL will turn red and flash continuously in inverse video 190 00492 10 Rev 8 Diamond DA 40 DA 40F 7 6 Part Information GPN 190 00492 10 Description AFMS G1000 Integ Avionics Sys w GFC700 AFCS Diamond DA40 F 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 10 Rev 8 ECO 099458 Creation Date 17 May 2013 12 50 PM CST
3. DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F STARTING ENGINE DA 40 F only a Cold engine 1 Strobe light ACL sa8 passin asse a a a E a aie cane not ON 2s Mixture sisi essa doe arav lon ania E E KE AS fully RICH 3 Electrical tuel Pump nenn Mitac banks ON note pump noise functional check of pump A Throttle c c 8c oii Aisi ie ties travel forward from IDLE De PHM seek aes arb Ria deg ana 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 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
4. Never try to start the engine by hand STARTING ENGINE DA 40 only a Cold engine 1 Strobe light ACL urerrnn i nei ei o iE E E E Eee o RSE Siri ON 2 Electrical fuel pumpir neinni as ON note pump noise functional check of pump Be Whrottl vs enea a eee ae es 3 cm 1 2 in forward from IDLE measured from rear of slot 4 Mixture control lever cceccececcccceesesseeeeeeeee RICH for 3 5 sec then LEAN 5 Throttle s 4i6ccnciavnig aii iain liecides dieds 1 cm 0 4 in forward from IDLE 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 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
5. Refer to the Main Bus and Avionics Bus areas of the circuit breaker panel for a quick reference to equipment on those busses 190 00492 10 Rev 8 Diamond DA 40 DA 40F 3 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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 Pito the atin aes i cehew SescesleebrevecR tiled athereoe e e E E AEA ON 35 Cabin Neato reat seen ices ee aise eee E Bee es Be A ON 4 Air distribution lever cccccccccsccssccssccssecsseeseecesecesescesecesecesscsseeseenes A UP De RPM EE E ES increase in order to prevent ice build up on the propeller blades 6 Alternate Air DA 40 only sssesssesenseesesssseeessseseessessrsreseesesseseessesees OPEN 6a Carburetor Heat DA 40 F only 0 e cee eecececeececeeeeeeeeeeeeereeseensees HOT 7 Emergency Window S cccsccsssesescessceseeeeceaeeeseceecaeeeneeeneees open if required 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 ata Bs kot a a E E a Ea advise if an emergency is expected CAUTION When the pitot heating fails yellow PITOT FAIL annunciation and the alternate static valve is i
6. 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 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 10 Rev 8 Diamond DA 40 DA 40F 3 14 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 4A 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 and GFC 700 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 iieiaeie flight planning complete b Airplane document cceecceecesceeeeeeeeeeceeeeseesneenee complete and up to date Y MQMIUION KE Yee E coeds SE E E A pulled out d Front canopy amp rear doof seseessseessseeseeesesreesrsreerssrrrreserrreresee clean undamaged
7. e All electrical equipment f Circuit breakers ceeeeeeee set in if one has been pulled check reason g Engine control levers ceeceeeeeee check condition freedom of movement Full travel of throttle Full Travel of RPM DA 40 only Full Travel of mixture lever h Throttle 2s ecselec specced Sascecstecdestes Riese codec ola RE hava neeendave ce eben can eaet oc es IDLE D Mixture control lever sdn ceecccas cod cicadev at cet cates eee inci vdacek T LEAN jJ RPM lever DA 40 only eeeeceecceeseeecceeeceseceneceeecaeeeneeeneeneeeseenneees HIGH RPM k Carburetor Heat DA 40 F only eee ceeceeeseeceeeeecsaeceeneecnaeceeeeeenaeeeees COLD HN BAT battery Switch rennin er er EE E REE S ON m Fuel Quantity 0 0 cece ceecesecesecececeeeceeeeseeeeeeeseeeeeeeeeeseeneees check fuel qty on EIS check with fuel qty measuring device 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 th
8. 8 Diamond DA 40 DA 40F 3 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 X over the attitude area AIRSPEED FAIL Display system is not receiving
9. 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 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 substantially identical to the PFD and contains the same controls as previously listed Additionally the GFC 700 autopilot mode controls are located on the MFD These controls are described later in this section 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 Heading Reference System AHRS uses GPS rate sensors air data and magnetic variation to determine pitch a
10. Cruise Descent 200 feet Maneuvering 115 feet Approach 130 feet 3 2 3 ENGINE PROBLEMS IN FLIGHT h High Fuel Flow DA 40 only Fuel flow in red sector 1 Fuel pressure 0 cee eeeceeeeeeseeeeee 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 should 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 190 00492 10 Rev 8 Diamond DA 40 DA 40F 3 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F g High Fuel Flow DA 40 F only I Fuel Quantity nesenie ee esee si seara ii ra Check and Monitor 2 Power Stn tinere E EE E ERA ES 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 T Emergency SW iChain ciehtewsteteereen dhaesheaseeee ON if installed CAUTION Switching OFF the master switch ALT BAT will lead to total loss of all electronic and electric equipment inc
11. GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F If smoke or fumes decrease 9 Land at the nearest suitable airport as soon as possible If smoke or fumes persist 10 ALT alternator SWitch enssins e ON LA SESS BUS switch saaan ce RAR ec te oa iS ted Meas noes eds a Ra AEN OFF 12 BATT and ESS TIE circuit breakers 0 eccceccccccesseesccseceseesssssesseesseesees 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 13 Use standby instruments for attitude airspeed and altitude 14 Refer to Section 3 7 2 b of this Supplement Alternator Failure 15 Land at the nearest suitable airport as soon as possible 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 COM 1 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
12. GPS SBAS NAVIGATION SYSTEM GIA 63W INSTALLED The Garmin G1000 GPS SBAS receivers GIA 63W incorporating SW version 3 0 or later 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 versi
13. INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F RPM lever DA 40 only 0 e eee eee eeeeeeeeeee eens pull back until a drop of max 500 RPM is reached HIGH RPM Cycle 3 times 18a Carburetor Heat DA 40 F only eee eeeeceeeeeneeceeeeeeneeceeeeeneees check function 18b Throttle DA 40 F only eee eeeeeeeeeeneeeeee 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 TO TRO Le ER E AT set 1000 RPM 20 Carburetor Heat DA 40 F only ssesseeseessesssesssesrserrsrrssresressrrssees check COLD 21 Alternate Air DA 40 only s seseessessesseesssrserssesessrserssesersesseeee check CLOSED 22 Flight Plah ii ie E E ROE a entered 23 Altimeter seting ersin i e e reie anny Hanae rary checked set G1000 and standby altimeter 24 Altitude preselector nieres eae r e S REE set P E OSE E sees de EE EE E E E set and checked 26 Transponder snosi a scccsscuenvees S schdusdesvadts aE feokvees ds eeheusdacunsss e e apre eii code set 27 Standby attitude gyro occ ees ssecseeeecneeeeceseeeeesecseeseeeeeeeeaees erect and no flag 28 Parkins Drakes s isc pissse saves ea a eaae feeds rar E eE Raa aetas release 29 Fanding Mehter eeen er easet sir Eee ea Ea EE ek ON as re
14. 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 South 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 form 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 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F The ADF aural identifier must be monitored any time
15. and Track 1 Navigation Source SELECT VOR LOC or GPS using CDI button on PFD 2 Course Bearing Pointer SET using course knob VOR or OBS mode only 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller eee ceeeecsseceeneeeseeeenee SELECT NAV on mode controller 5 Green or White VOR or GPS annunciation ceeeeeeeeeneeeee NOTE on PFD 6 Vertical Mode and Reference cesses SELECT on mode controller NOTE If the Course Deviation Indicator CDTI is greater than one dot from center the autopilot will arm the NAV mode and indicate VOR or GPS in white on the PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the autopilot will enter the capture mode when the NAV button is pressed and annunciate VOR or GPS in green on the PFD 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 14 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F APPROACH VOR 1 Navigation Source eee SELECT VOR using CDI button on PFD 2 Course Bearing Pointer eee eeeeecseeeeceeeeeeeeeeeeeeene SET using course knob 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller cceescceesseceesereeeeees SELECT APR on mode controller 5 Green or Whi
16. 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 LOCY GS receivers to fly approaches not approved for or GPS requires 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 11 RNP operations are not authorized except as noted in the Operational Approvals section GFC 700 LIMITATIONS 1 The GFC 700 AFCS preflight test must be successfully completed prior to use of the autopilot flight director or manual electric trim Use of the autopilot or manual electric trim system is prohibited if the preflight test is not satisfactorily completed 2 A pilot with the seat belt fastened must occupy the left pilot s seat during all autopilot operations 3 The autopilot must be off during takeoff and landing 4 Autopilot
17. 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 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 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 190 00492 10 Rev 8 Diamond DA 40 DA 40F 1 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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 G1000
18. biect eeteerevind a ea T eaat PULL Ss AP DISCS witch nnii n e s os aisha as deseo bee Sot RELEASE WARNING FOLLOWING AN AUTOPILOT AUTOTRIM OR MANUAL ELECTRIC TRIM SYSTEM MALFUNCTION DO NOT ENGAGE THE AUTOPILOT OR OPERATE THE MANUAL ELECTRIC TRIM UNTIL THE CAUSE OF THE MALFUNCTION HAS BEEN CORRECTED 190 00492 10 Rev 8 Diamond DA 40 DA 40F 3 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F For lt AIL AIL gt Indication 1 Rudder Trim penenie VERIFY slip skid indicator is centered NOTE Observe the maximum fuel imbalance limitation If annunciation remains 2 Control Stick oo cccceceessessecsecesesseesees GRASP FIRMLY with both hands CAUTION Be prepared for sustained control forces in the direction of the annunciation arrow For example an arrow pointing to the right indicates that sustained right wing down control stick force will be required upon autopilot disconnect JAP DISC Switch oo cscpsisieiaess estat eid a a OE EE EEPE Bites DEPRESS 4 Autopilot aeeoe ieee nesk RE ENGAGE if lateral trim re established FLASHING YELLOW MODE ANNUNCIATION NOTE Abnormal mode transitions those not initiated by the pilot or by normal sequencing of the autopilot will be annunciated by flashing the disengaged mode in yellow on the PFD Upon loss of a selected mode the system will revert to the default mode fo
19. 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 alternate 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 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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
20. maximum engagement speed 165 KIAS Autopilot minimum engagement speed 70 KIAS Electric Trim maximum operating speed 178 KIAS 5 The autopilot must be disengaged below 200 feet AGL during approach operations and below 800 feet AGL during all other operations 190 00492 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 6 ILS approaches using the GFC 700 autopilot flight director are limited to Category I approaches only 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 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
21. oil pressure is normal and steady 6 Tenton SwitCh 24 0 essesoccthtentetesren ghaestestescon ies neten siete E START 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F When engine starts 7 Mixture control lever c cccecccecceeseeesceeeceeeeeeeeeseenneenneeaee rapidly move to RICH 8 Oil Pressure iy 25 be ele a cele E green arc within 15 sec 9 Electrical fuel pump sveria eh e e E nein toed abet ease 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 swit haee ae ee ee EEE EEEE A ON l Ammetta eee e e e e e aeree E a EES ETE e Check 12 Fuel pressure nieee e Check no messages illuminated 13 Annunciator section Of PFD cccccceceesseceesceesseceeeceeseeceeeeeseecsteeeesaeenes Check b Warm engine 1 Strobe ight A CL soi renar n E E E EEE EE E ON 2 Electrical fuel PUMP eiea neen e ON note pump noise functional check of pump 3a Throttle n a sk kiios 3 cm 1 2 in forward from IDLE measured from rear of slot 4 Mixture control lever oo ccccceecseceeeseeeeeeneees 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 D
22. 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 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
23. they will be annunciated with a flashing annunciation of the new mode for ten seconds in green If a mode becomes unavailable for whatever reason the mode will flash for ten seconds in yellow and be replaced by the new mode in green 190 00492 10 Rev 8 Diamond DA 40 DA 40F 7 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F The GFC 700 autopilot contains an electric pitch trim system which is used by the autopilot for automatic pitch trim during autopilot operation and by the pilot for manual electric pitch trim when the autopilot is not engaged The manual electric pitch trim system is operated by a split switch on the left control stick The GFC 700 autopilot and manual electric trim MET will not operate until the system has satisfactorily completed a preflight test The preflight test begins automatically with initial power application to the autopilot AVIONIC MASTER Switch is set to the ON position The following conditions will cause the autopilot to automatically disconnect e Electrical power failure e Internal autopilot system failure e AHRS malfunction e Loss of Air Data Computer information The GFC 700 may be manually disconnected by any of the following means e Depressing the red AP DISC button on either control stick e Moving the left outboard side of the manual electric trim switch on the left co
24. 1 SECTION 4B ABNORMAL PROCEDUREG cssssssssssssrsessessrsesseres 4B 1 SECTION 5 PERFORMANCE cscsssssssssssssessessesessersesessessesessessesesessesees 5 1 SECTION 6 WEIGHT AND BALANCE ccccsssssssesssssssessesessersesessevseeees 6 1 SECTION 7 SYSTEM DESCRIPTIONS csssssssssssssessssessesssserseseesessesees 7 1 190 00492 10 Rev 8 Diamond DA 40 DA 40F Vv This page is intentionally blank 190 00492 10 Rev 8 Diamond DA 40 DA 40F vi FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 in accordance with TSO C145a Class 3 The primary function of the PFD is to provide attitude heading air data navigation and alerting inform
25. 35 Note 4 aoe 0 25 25 55 56 95 96 97 gt 97 Fuel flow Gal hr 1 20 gt 20 ae 0 241 241 25 251 30 30 1 32 gt 32 Volts Amperage _ 2 75 _ e Amps Fuel quantity US gal Standard 0 gt 0 3 gt 3 17 Tanks Fuel quantity US gal gt 3 16 Long Range 7 Ae I 5 54 i j Tanks 190 00492 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 annunciations 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 Oper
26. CE Refer to the Aircraft Flight Manual and see current weight and balance data 190 00492 10 Rev 8 Diamond DA 40 DA 40F 6 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 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 followi
27. D AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 ma 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 10 Rev 8 Diamond DA 40 DA 40F 4B 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F PFD MFD AND GIA OVERHEAT a b ma c 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 fa
28. EMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F AUTOPILOT DISCONNECT Red AP flashing on PFD 1 AP DISC Switch c e c cceciseceteceesesseceecnteeesosetdnetoeneeee DEPRESS AND RELEASE to cancel disconnect tone 2 Pith Tim aeae a sees ents setae RETRIM if necessary using the trim wheel NOTE The autopilot disconnect may be accompanied by a red boxed PTCH pitch or ROLL on the PFD indicating the axis which has failed The autopilot cannot be re engaged with either of these annunciations present AUTOPILOT OVERSPEED RECOVERY Yellow MAXSPD on PFD 1 Throttle ssnnennrn n aaa R R REDUCE When overspeed condition is corrected 2 Autopilote nenk erea RESELECT VERTICAL MODE if necessary NOTE Overspeed recovery mode provides a pitch up command to decelerate the airplane at or below the maximum autopilot operating speed 165 KIAS Overspeed recovery is not active in altitude hold ALT or glideslope GS modes LOSS OF NAVIGATION INFORMATION Yellow VOR VAPP GPS or LOC flashing on PFD NOTE If a navigation signal is lost while the autopilot is tracking it the autopilot will roll the aircraft wings level and default to roll mode ROL L AUtOpilObiss lt 2 sist Steet teed Sh S SELECT HDG on mode controller 2 Nav SOUC 2 ia alte heel ee Ri Be SELECT A VALID NAV SOURCE 3 AUfOpil Otene ni SELECT NAV or APR on mode controller If on an instrument appro
29. Garmin Ltd Or its subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA Document No 190 00492 10 FAA APPROVED FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GFC 700 AUTOMATIC FLIGHT CONTROL 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 and GFC 700 automatic flight control system are 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 ali previously approved G1000 GFC700 Airplane Flight Manual Supplements for DA 40 and DA 40 F including those required by STC SA01254WI D and STC SA01389WI ae Robert Murray ODA STC Unit Administrator Garmin International ODA 240087 CE Date Ht 2o1 2 190 00492 10 Rev 8 Diamond DA 40 DA 40F i This page is intentionally blank 190 00492 10 Rev 8 Diamond DA 40 DA 40F ii Garmin Ltd Or its subsidiaries c o Garmin Internati
30. INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 11 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 is not available or invalid and the TAWS option is installed TAWS will not be available A white TA
31. LOC 1 Altitud Pres lect cuss sovcscsiensisvvceesssoonnstiseceescosccestoevesoeees SET to desired altitude 2 Mode Controller ccccccecccccceceesessseeeeeeees SELECT FLC on mode controller 3 Airspeed Reference ADJUST using NOSE UP and NOSE DN buttons 4 White ALT altitude preselect armed esceeseeeceeseeeeeeeeeee NOTE on PFD 5 Green ALT icena ieia VERIFY UPON ALTITUDE CAPTURE NOTE If the airspeed reference cannot be maintained without deviating away from the selected altitude the system will maintain level flight until the power or reference is changed to allow climbing or descending towards the selected altitude The FLC mode is limited to airspeeds between 70 KIAS and 165 KIAS Use engine power to maintain appropriate vertical speed If the CWS switch is used while in FLC mode the airspeed reference will change to the airspeed existing when the CWS switch is released Altitude Hold ALT To capture a selected altitude 1 Altimeter Setting 0 0 0 0 eeeeeeeeereees ADJUST TO APPROPRIATE VALUE 2 Altitude Preselect cccccccccceseesseeeseeesseeseees SET TO DESIRED ALTITUDE 3 Vertical Mode and Reference cccceecceeseeeeee SELECT on mode controller 4 White ALT altitude preselect armed ecceecceeeeereeeeeeees NOTE on PFD 5 Green ALT orice raceri VERIFY UPON ALTITUDE CAPTURE 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 13 FAA APPROVED AIRPLANE FLIGHT MAN
32. MALFUNCTION HAS BEEN DETERMINED AND CORRECTED Normal autopilot disconnects are annunciated with a yellow flashing AP on the PFD accompanied by a two second autopilot disconnect tone Normal disconnects are those initiated by the pilot with the AP DISC switch the MET switch the AP button on the MFD mode controller or the GA button Abnormal disconnects will be accompanied by a red flashing AP on the PFD accompanied by a continuous autopilot disconnect tone The disconnect tone 190 00492 10 Rev 8 Diamond DA 40 DA 40F 7 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F and flashing alert may be cancelled by pressing the AP DISC switch or the left side of the MET switch Refer to the Garmin G1000 Pilot s Guide for the Diamond DA 40 for a complete description of the GFC 700 system and operating procedures 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 reads 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
33. MIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F T Autopulotis sis ciieveresasptetiet ses etal Ea E A a RES RE ENGAGE if desired NOTE If the missed approach procedure requires tracking the localizer outbound from the airport use NAV mode to prevent inadvertent coupling to glideslope AFTER TAKEOFF TAWS NORMAL PROCEDURES If 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 Pil
34. N THE AIRPLANE TO STABILIZED FLIGHT PRIOR TO RE ENGAGING THE AUTOPILOT NOTE The NOSE UP and NOSE DN buttons on the mode controller on the MFD are referenced to aircraft movement The NOSE UP button will increase the reference pitch attitude increase the reference vertical speed and decrease the reference airspeed Likewise the NOSE DN button will decrease the reference pitch attitude decrease the reference vertical speed and increase the reference airspeed 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 12 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F CLIMB CRUISE and DESCENT Vertical Speed VS 1 Altitude Preselect 0cccccccecssccecessceceessseeceesseeesssseeees SET to desired altitude 2 Mode Controller c cccccccsesssecececesssseceeees SELECT VS on mode controller 3 Vertical Speed Reference ADJUST using NOSE UP and NOSE DN buttons 4 White ALT altitude preselect armed ecceesseeseeeeeeeeeeees NOTE on PFD 5 Green ALT rinner enie iis VERIFY UPON ALTITUDE CAPTURE NOTE The vertical speed mode is limited to 1 500 ft min climb and 3 000 ft minute descent Use engine power to maintain appropriate aircraft speed If the CWS switch is used while in VS mode the VS reference will change to the vertical speed existing when the CWS switch is released Flight Level Change F
35. OC and glideslope GS e Back Course BC tracking e Go Around GA pitch roll guidance e Glidepath coupling GP GIA 63W equipped aircraft only e Vertical Navigation VPTH optional feature The system consists of autopilot controls on the Multi Function Display MFD servos with autopilot processing logic Flight Director processing logic in the GIAs a left control stick mounted elevator trim switch a control stick mounted trim interrupt and autopilot disconnect switch on both sides a left control stick mounted CWS Control Wheel Steering switch a throttle mounted GA Go Around switch and PFD MFD mounted altitude preselect heading and course knobs Flight Director commands and autopilot modes are displayed on the PFD Full AFCS functionality is only available with the both displays operating and will disconnect under certain reversionary conditions Upon initial system power up the system undergoes a preflight test At the end of the test the autopilot disconnect tone sounds and the PFT and AFCS annunciations are removed Successful completion of the preflight test is required for the autopilot and manual electric trim to engage Annunciation of the flight director and autopilot modes is shown in the lower status field of the PFD In general green indicates active modes and white indicates armed modes When a mode is directly selected by the pilot no flashing of the mode will occur When automatic mode changes occur
36. UAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F NOTE In ALT mode the autopilot will maintain the reference altitude shown in the autopilot window of the PFD regardless of the altitude in the altitude preselect window or the altimeter s barometric pressure setting If the altimeter setting is changed the autopilot will climb or descend to maintain the reference altitude Altitude Hold ALT To maintain a desired altitude 1 Altimeter Setting eee eeeeeeeeee ADJUST TO APPROPRIATE VALUE 2 Reaching desired altitude eee eee SELECT ALT on mode controller DS Green AE T a E E E aT ASe nha VERIFY on PFD Vertical Path VPTH If equipped with optional GDU 1044 1 Navigation Source SELECT GPS using CDI button on PFD 2 MFD flight plan page ceeceeseeseeeeeeeeeteeeeeeees Enter Desired Vertical Profile 3 Altitude Preselect 0 0 0 cc ceeecseseceecneeereeeeeees SET TO DESIRED ALTITUDE 4 Mode Controller eeeceeeeesseceeneeeseeeenees SELECT VNV on mode controller 5 White VPTH Vertical Path armed ccceccscccsssessseceseeeeeees NOTE on PFD 6 Green VPTH osos VERIFY UPON VERTICAL PATH CAPTURE NOTE If VNV is pressed and VPTH is armed prior to 5 minutes time to top of descent VPTH will flash in white at 1 minute prior to top of descent The pilot must acknowledge the flashing by pressing VPTH again Navigation Capture
37. WS 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 approach course guidance may still be available with 1 nautical mile CDI sensitivity 190 00492 10 Rev
38. ach at the time the navigation signal is lost 4 Missed Approach Procedure s sseseseeeecseeeereeesrereresesee EXECUTE as applicable 190 00492 10 Rev 8 Diamond DA 40 DA 40F 3 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F AUTOPILOT OUT OF TRIM Yellow 4AIL AIL gt TELE or JELE on PFD For TELE or VELE Indication WARNING DO NOT ATTEMPT TO OVERPOWER THE AUTOPILOT IN THE EVENT OF A PITCH MISTRIM THE AUTOPILOT SERVOS WILL OPPOSE PILOT INPUT AND WILL CAUSE PITCH TRIM TO RUN OPPOSITE THE DIRECTION OF PILOT INPUT THIS WILL LEAD TO A SIGNIFICANT OUT OF TRIM CONDITION RESULTING IN LARGE CONTROL STICK FORCE WHEN DISENGAGING THE AUTOPILOT CAUTION Be prepared for significant sustained control forces in the direction of the annunciation arrow For example an arrow pointing down indicates nose down control stick force will be required upon autopilot disconnect NOTE Momentary illumination 5 sec or less of the TELE or JELE indication during configuration or large airspeed changes is normal If the annunciation remains 1 AP DISC Switch DEPRESS AND HOLD while grasping control stick firmly 2 Aircraft Attitude MAINTAIN REGAIN AIRCRAFT CONTROL use standby attitude indicator if necessary 3 Pitch TAM aeara eie RETRIM if necessary using the trim wheel 4 AFES Circ it Breaker usssatse ssieteh esse
39. 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 10 Rev 8 Diamond DA 40 DA 40F 3 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F GFC 700 EMERGENCY PROCEDURES Some emergency situations require immediate memorized corrective action These numbered steps are printed in boxes within the emergency procedures and should be accomplished without the aid of the checklist AUTOPILOT OR ELECTRIC TRIM MALFUNCTION FAILURE NOTE An autopilot or electric trim malfunction may be recognized by an unexpected deviation from the desired flight path abnormal flight control or trim wheel movement or flight director commands
40. al equipment s s cived ain EE R On as required 3 Plapsvec tae eecd cease earth ES n ANT UP T O LDG T O indicator and visual check 4 Flight instruments and avionics ccecceeceerees set test function as required set both altimeters 5 Flood ight asina k neni nea Ana et ON test function as required 6 gt Ammetef e siao o n e e iE check if required increase RPM 7 Fueltank selector cccceecceeseeseeseeeeeeeeeeees change tanks confirm that engine also runs on other tank at least 1 minute at 1500 RPM 8 Pitot heating sista E e E eee hey ON test function Spd SNA R E RE a NE KE RA no yellow PITOT FAIL annunciation 9 Pitot heating s eesneine a a E a O S OFF if not required E EA E A E iaees yellow PITOT OFF annunciation 10 Strobe lights ACLS cecesseesceeseeeseeereeeeeeeeeeseeeeeeeees check ON test function E sche eceaaunveCeae Teicha cs E E A E E Reactass as required 11 Position lights landing and taxi lights ON test function as required 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 12 Ide RPM enoun o N E check 600 to 800 RPM The GFC 700 AFCS system automatically conducts a preflight self test upon initial power application The preflight test is indicated by a white boxed PFT on the PFD Upon su
41. ation of the starter without the key in the start position or failure of the starter STARE RENED motor to disengage from the engine after starting Front canopy and or rear door not DON completely closed and locked 190 00492 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Caution annunciations Yellow Annunciation Cause PITOT OFF Pitt heat is not switched on PITOT FAIL Fault in the pitot heating system Fuel quantity in the left tank is less than 3 EPUEDEOW US gal 1 US gal Fuel quantity in the right tank is less than 3 MEUBEL TYAN US gal 1 US gal LOW VOLTS On board voltage below 24 volts PFD FAN FAIL PFD Cooling Fan has failed See Abnormal Procedures section 4B MFD 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 temperature limit Display brightness is PED ONERMEAR automatically reduced to 50 of maximum See Abnormal Procedures section 4B MFD is approaching its operating MFD OVERHEAT temperature limit Display brightness is automatically reduced to 50 of maximum See Abnormal Procedures section 4B GIA1 OVERHEAT GIA 1 is approaching its operating tem
42. ation to the pilot The PFD may also be used for flight planning 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 10 Rev 8 Diamond DA 40 DA 40F 1 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 info
43. ccessful completion of the preflight test the PFT is removed the red AFCS annunciation is removed and the autopilot disconnect tone sounds 13 Primary Flight Display PFD NO AUTOPILOT ANNUNCIATIONS 14 Autopilot Disconnect Tone ceeecsseseceseceeeseceeeeceesecsaeeecsaecaeeeeeneeaes NOTE 15 Autopilots nsi tunics nain i nesei CHECK Pilot s AP DISC button a Press AP to engage autopilot b Press Pilot s AP DISC button Verify autopilot disconnects c Press FD to remove flight director as desired d Set trim to T O 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F BEFORE TAKE OFF 1 Position airplane into wind if possible 2 Parking brakes siacnciasinlonnnucins duaiiod E anand mame set 3 Safety HamMesses merini erae aise ovis R R A hee ees on and fastened 4 Reat doo s 4 5 atic de anki din cit aie aii check closed and locked So Pronticanopy ea i heehee he ohh a a e S 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
44. 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 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 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 Information 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 inst
45. duced Yellow band 53 KIAS 58 KIAS 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 178 KIAS and greater 178 KIAS is the maximum speed for all operations The airspeed indicator is marked in IAS values 190 00492 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 bar arc or or bar Yellow or bar bar arc or bar Lower Normal Upper prohibited Caution operating Caution prohibite Indication range range range range d range Manifold Pressure In He 13 30 Note 2 500 gt 2700 BEM 2700 T Note 3 Oil Temp oF 149 230 231 245 gt 245 Cylinder 476 Head Temp z 150 475 i gt 500 op 500 Fuel Press PSI DA 40 0 14 14 35 gt
46. e fuel quantity measuring device There are 3 US gal of ungauged 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 eccesesseesseesceesceeseeereeeeeeeeeeseeneensees check 0 BAT battery S Witch narenn clot levuuceedeesedesietuctedsauna RRES OFF P Check for loose items siiani ornen ne ei a n complete q Flight controls and trim eeeseeesseeeesssesersseseessrsreesssesees free to move and correct T Bat gate snar a Ra n Qin oe OA Qe 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 nspectlon 2201 seca viele Meio ip o erie i Complete 2 Rudder pedals niinn eaa a a REEE Adjusted and locked EE S 01A SSA AESA E E E ENEE E E E EE EN Instructed 4 Safety Harness S oken ceesecseeseesecseeeeceeseecssecasesecsesereeaeeees All on and fastened Di ReatidOOr sca co ce istie tase ities Bates cp nE aisles EEEE E Closed and locked 6 Door lock if installed cece cceceeseeesseeeeeeeesseeeeee Unblocked key removed Ta Front Canopy serenana a a Position 1 or 2 cooling gap 8 Canopy lock if installed oe eee eeeeeecneeeeeneeeeeeee Unblocked key removed Os Parking Drakenei nano a hes falda aE a REO E N Set 10 Flight controls Freedom of movement and proper direction 11 Trim wheels fientecsonicuieie prina s
47. ea eer E r a N R T O 12 Friction device throttle quadrant cccesccesececeeseeeseeeeeeeeeeeeeeeeeeteenaes Adjusted 133 Phar ttl EREE EE fs sagssaatesd sauebst esas shten stbbaesysasteospabssdessesaeaeeabobisteits IDLE 14 Mixture control lever cccceccecsseesceesceseceeeceeceseceaeceaecaeecaeeeseeeaeenaeeneeennees LEAN 15 RPM lever DA 40 only eeeeeceeeeeseeseceseeeeeseceeesecneesecsaeeereeeaeeees HIGH RPM 16 Carburetor heat DA 40 F only cee eee ceeccecsseceeeeeceeceeeeeceeeeeneecsaeeeenees COLD 17 Alternate air DA 40 only 00 ceeceeeeesceeeceeeceseceneceecaeecaeeeseeeeeeneeenees CLOSED 18 Alternate Static Valve cece cecccccccssscccecssececesseeeensseeeeenes CLOSED if installed 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 19 Avionics master SWitCh cccccccccesessssssccceecessscsseccceceesseessseseeceessessesesesseesees OFF 20 Essential Bus SWitch a e r e ea a A e e Nease 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 switch rniran r E aR a E ON 22 AIEI E AO E EE E EEE EEEE on fullest tank WARNING Never move the propeller by hand while the ignition is switched on as it may result in serious personal injury
48. er than APR mode GPS LNAV 1 Navigation Source SELECT GPS using CDI button on PFD 2 Approdc hiv 3 ss28 iste ed Goat E R LOAD in FMS and ACTIVATE 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller SELECT APR on mode controller 5 Green or White GPS annunciation ccceeecsscssececeesessseeseseees NOTE on PFD 6 Vertical Mode and Reference 0 cccceceeeeeeees SELECT on mode controller 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 15 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 7 Airspeed eeeeeeee MAINTAIN 80 KIAS OR GREATER Recommended GPS LPV LNAV VNAV LNAV V If equipped with optional GIA 63W GIA units 1 Navigation SOurcCe eee eeeeeeneeeee SELECT GPS using CDI button on PFD 2 Approaches icsse Sadsh nesesite eevee LOAD in FMS and ACTIVATE 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller cccccccescecseseeeeeeseeeeeenees SELECT APR on mode controller 5 Green or White GPS annunciation cccccesceessecsseceeeeesseeeees NOTE on PFD 6 Green or White GP annunciation ccccccesceescecsteeeeeeeesteeeees NOTE on PFD 7 Airspeed MAINTAIN 80 KIAS OR GREATER Recommended Localizer Back Course BC 1 Navigation Source cesses SELECT LOC using CDI butt
49. et ssseseeeeeseseeesreseereesrsrserrrereresrsesreerersesesee LEAN fully aft e I U n0 E EEE E E sours 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 S Tsmitionswitch s 1 sis ahaisnavras nich bien Ares bavee as Mata haees START 6 Throttle sieneen and pull back towards IDLE when engine starts When engine starts 7 Mixture control lever cecccecceeceeeceseceseceeeeseeeneeeeeensees rapidly move to RICH 8 Oil pressure sys csscen a EE Ea ede Dien nies 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 altertiator S Witehira a ok ari wet i ET Reese ON 10 Atim ter arn icesaieietees A kid ieee a EEE Rie E EEK Check Ti Fuel pressure crenn ee a Check no messages illuminated 12 Annunciator section of PFD ccccccccecsseceeeceesseceeeceeseeceeeeeseeceeeeeesaeenes Check 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT
50. 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 3 Starte ene a e r aii ktlaeainiias a E a Eea engage When engine starts Gs OUspressure si ids reiia ar a a enia aans green arc within 15 sec Te Throttle rerio erosota treere Sete eoe bessie eE EEEE iai set 1000 RPM 8 Electrical fuel pump x iseer ee raae ee pe a E e eats 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 Master sV OA AL a OE wees a i ON LO Ammetei eienn a a a haves a eae Check 11 Annunciator section Of PFD sseseeeeeesseseeseesseeseeressssrsereesessssereeeessrerrereesee Check 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F c Engine will not start after priming flooded engine 1 Strobe light ACL Jennaa i aa eee ON 2 Electrical fuel pumps i sa vistsu seein Anu aii EEEE E EREE e A et OFF Bi MIXTE e aeieea
51. ft 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 Additional 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 10 Rev 8 Diamond DA 40 DA 40F 1 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 0321 23 P N 190 00324 1 1 Revision B or later appropriate revision 2 AHRS Areas of operation Flight operations with the G1000
52. ils or is unusable select Display Reversionary Mode using the red DISPLAY BACKUP button on the audio panel Pull the PFD circuit breaker If the PFD fails or the PFD circuit breaker is pulled the autopilot will not operate MED 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 If the MFD fails or the MFD circuit breaker is pulled the autopilot mode controls on the MFD will not operate Disengage the autopilot using the AP DISC button on the control stick PFD OVERHEAT caution AND MED 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 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4B 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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 affec
53. ined 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 MFD 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 10 Rev 8 Diamond DA 40 DA 40F 1 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F ELECTRONIC FLIGHT BAG The G1000 Integrated Avionics System as installed in this aircra
54. luding 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 2 M ster switeh ALT BAT i cses cscdich Sit A Has Ria hee As EEE E OFF 3 Cabin heats snniscdenis dette ok alee a amalntn Rake OFF A Emergency witdow S tii cs ssisesstssecechsbastpseeseievssspsasvdtsdstesibassomiasbestpshepereges OPEN 5 Use standby instruments for airspeed altitude and attitude reference if necessary 6 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 T BAT Battery SwitChs c icccsiccccssesceieecaastecscdecsdepcavcneviescaise ei era e i ON 8 So A s1 OEA T ETA EAT E S E ON NOTE This removes power from the main and avionics busses and does not allow alternator operation See the table at the end of this section for the equipment which is still available 190 00492 10 Rev 8 Diamond DA 40 DA 40F 3 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH
55. nd 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 10 Rev 8 Diamond DA 40 DA 40F 7 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F GFC 700 The GFC 700 Automatic Flight Control System AFCS is a 2 axis autopilot and flight director system which provides the pilot with the following features e Altitude Preselect and Altitude Hold ALT e Flight Level Change with Airspeed Hold FLC e Vertical Speed Hold VS e Navigation tracking for VOR NAV and GPS GPS e Heading Hold HDG e Approach mode coupling to VOR VAPP or localizer L
56. ng 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 190 00492 10 Rev 8 Diamond DA 40 DA 40F 7 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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
57. nstalled 9 Allternate static val V neno renna EE EEES OPEN 10 Emergency window s cesccesscesseeeeesecseceeecaeecaeeeseeeeeeeeeeeseeerenerensees close 190 00492 10 Rev 8 Diamond DA 40 DA 40F 3 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 Circuit breakers 4 4etaks cee na atk Bates scerin Sitar adecehee Check in 2 ALT alternator switch 00 cece cccccescecsseceeececsseceseecseseeeeecseeesee OFF then ON If alternator does not come back on line message extinguishes and ammeter indication greater than zero PY Switch off any non essential electrical loads 5 Land within 30 minutes If PFD attitude information is lost prior to landing ESS BUS switch a ra ena Sutin sean Nid atest ON 6 HORIZON EMERGENCY Switch eeceeeceeceeeseeseeeessecaeeeeereeeaeeees ON CAUTION The following items are available on the Essential Bus e 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 e Landing light Refer to the ESSENTIAL BUS area of the circuit breaker panel for a quick reference to equipment on tho
58. ntrol stick e Pushing the AP button on the autopilot mode controller when the autopilot is engaged e Depressing the GA button on the left side of the throttle e Pulling the AFCS circuit breaker e Turning off the AVIONIC MASTER switch e Turning off the airplane Master ALT BAT switch In addition the CWS control wheel steering switch on the pilot s control stick will disconnect the autopilot servos from the airplane flight controls as long as the CWS switch is depressed Power to the GFC 700 autopilot and electric trim system is supplied through the AVIONIC MASTER switch and the AFCS circuit breaker The AVIONIC MASTER switch can be used as an additional means to disable the autopilot and electric trim system The red AP DISC switch on the either control stick will interrupt power to the manual electric trim for as long as the switch is depressed 190 00492 10 Rev 8 Diamond DA 40 DA 40F 7 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Loss of instruments or components of the G1000 system will affect the GFC 700 AFCS as follows e Loss of the AHRS will cause the autopilot to disconnect The autopilot and flight director will be inoperative Manual electric trim will be available e Loss of the heading function of the AHRS will result in loss of the HDG mode If in HDG mode at the time heading is lost the auto
59. o 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 Isnitiomswitch ienie nonnii er R E E eee START When engine starts 6 Mixture control levet sssessseeesseeesesreeseseeersserreereseeereseeees rapidly move to RICH Te Oil Pres UTE a eera eaaa eea eaaa r aa Sa essa ao aaas 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 pumpir nireset i Ee EN E ER a OFF 9 ALT lt rnator ks wite hiin aee EAE AE ON 10 Amimeter 4235504 els aa tea A E ESE rE AREE Check 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 11 Fuel pressure ices scsseccicssssssssescetectestassbeasctasseestens Check no messages illuminated 12 Annunciator section Of PFD 0 eccceseesecssecseeeeeeeeeeeeceeeceseeeeeeeseenaeeaeenee Check b Engine will not start after injection flooded engine Warm engine T Strobe light AGEren nie R E EE SE ON Electrical fulel PUMP cci nan ieina n ON note pump noise Functional check of pump 3 Mixture control lev
60. on on PFD 2 Course Bearing Pointer SET to ILS front course using course knob 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller eseereeeeee SELECT NAV on mode controller 5 Green or White BC annunciation 0 ee eeeeseeseeeeeteereeeeeeeee NOTE on PFD NOTE The course pointer must be at least 105 from the current magnetic heading before BC will be annunciated in the lateral mode field Until that point LOC will be annunciated Selecting NAV mode for back course approaches inhibits the glideslope from coupling 6 Vertical Mode and Reference cecccceceeeeeeees SELECT on mode controller 7 Airspeed eeeeeeeee MAINTAIN 80 KIAS OR GREATER Recommended GO AROUND 1 Control Stick 2 2 Sie aici neea accu Birch cin dees GRASP FIRMLY 2 GA DUON nerien stato neea a aa PUSH Verify GA GA on PFD in lateral and vertical mode fields autopilot will disconnect but flight director will still be available 3 Balked Tanding ses hte niere erae E estes eaa ee EXECUTE 4 Missed Approach Procedure sseeeeseeeeeeeeeeeee EXECUTE as applicable 5 Altitude Preselectniniosieineseriiri iia rN SET to appropriate altitude At an appropriate safe altitude 6 Autopilot Mode Controller SELECT appropriate lateral and vertical modes on mode controller 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 16 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GAR
61. on with GA35 PN 013 00235 00 antennas selected Both GPS SBAS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation LRN sensor This does not constitute an operational approval 190 00492 10 Rev 8 Diamond DA 40 DA 40F 1 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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 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 determ
62. onal 1200 E 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GFC 700 AUTOMATIC FLIGHT CONTROL SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F LOG OF REVISIONS Revision Page Number Number s Description Approved Approval Murray Add Software Levels 9 6 2007 Murray Add Software Levels 2 28 2008 Murray adsain evel 41472008 Murray Update Software Levels Robert poe fan Add Software Levels 9 11 2009 Murray Revised by Garmin ODA Correct minor typographical errors and 7 All administrative Robert 9 91 2010 Murray corrections to fuel quantity indication range markings Incorporate revisions for E All system software level SER i abe iSe i age 190 00492 10 Rev 8 Diamond DA 40 DA 40F lil This page is intentionally blank 190 00492 10 Rev 8 Diamond DA 40 DA 40F iv FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GFC 700 AUTOMATIC FLIGHT CONTROL SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Table of Contents SECTION 1 GENERAL cccssssssssessesessessssessesessersesessersesessessesessersesessersesess 1 1 SECTION 2 LIMITATIONS cccssssssssessssessessssersesessessesessersesessersesessersevess 2 1 SECTION 3 EMERGENCY PROCEDUREG cssssssssssessesessersesessersevees 3 1 SECTION 4A NORMAL PROCEDURES ccccssssssssssessessesessessrsessesees 4A
63. ot s Guide 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 17 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 24V Possible reasons are A fault in the power supply RPM is too low i Low voltage caution on the ground I Enpine speed aaeeio e n Te EE re E E E EES 1200 RPM 2 Hlectrical equipment sa niei tini eea en ae EE E EE E EE S OFF 3 Ammeter and voltmeter sere ae en iiri EEEE E E check If the caution message does not extinguish and the ammeter gauge legend flashes and the ammeter gauge reads zero discontinue the flight ii Low voltage caution during flight 1 Electrical equipment 0 cee ceeeecseeeecneeeeceseeeeesecneeeeeneeeeens OFF if not needed 2 Ammeter and voltmeter 0 0 eee cece ceseceeeceeecaeeeseeeeeeeeeeeeeeeeeseesseesaeenees check If the caution message does not go out and the ammeter legend flashes and the 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 10 Rev 8 Diamond DA 40 DA 40F 4B 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATE
64. p era ra E Gos inion haa eo nen a Esk LEAN fully aft dir TUTORS arians a EES E ES O E N ESE 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 Je ota E a ee eee engage When engine starts 6 Throttle sieci irnn pull back towards IDLE when engine fires T OW press Ter nonna ae e aa iaei 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 H 01KO N 1 EE R EE EAEE ET set 1000 RPM 9 ALT alternator switch oo cc cccccccssscesscecsseceeceecsseseseecsseeesseeceeeeeseecsseeeeneess ON LOS AMMO ter AOAO EEEE Meas heeds hae aes Check 11 Annunciator section Of PFD c cc ccceccesccccceceessessecseeeceesssssesseeesesseeees Check 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F BEFORE TAXIING 1 Avionics master SWITCH ceceecesecesecscecseeeseeseecseeeseceeceeeeeeesecnseeeseeeaeeaeeaes ON 2 Electric
65. perature limit See Abnormal Procedures section 4B of the AFMS GIA2 OVERHEAT GIA 2 is approaching its operating temperature limit See Abnormal Procedures section 4B of this AFMS 190 00492 10 Rev 8 FAA Approved Diamond DA 40 DA 40F 2 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 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 MFD 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 Long Range Tanks 8 US gal approx 30 3 liters 190 00492 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000
66. pilot will revert to basic roll mode ROL e Loss of the MFD will not cause the autopilot to disconnect and will remain engaged with limited functionality but the autopilot cannot be re engaged once disconnected e Loss of the PFD will cause the autopilot to disconnect The autopilot and flight director will be inoperative Manual electric trim will be available e Loss of air data computer information will cause the autopilot to disconnect The autopilot will be inoperative The flight director will be available except for air data modes ALT VS FLC Manual electric trim is available e Loss of GIA 1 will cause the autopilot to disconnect The autopilot flight director and manual electric trim will be inoperative Loss of GIA 2 will also prevent autopilot and manual electric trim operation but flight director will be available e Loss of the standby airspeed indicator standby attitude indicator standby altimeter or standby compass will have no effect on the autopilot e Loss of both GPS systems will cause the autopilot and flight director to operate in NAV modes LOC BC VOR VAPP with reduced accuracy Course intercept and station crossing performance may be improved by executing intercepts and station crossings in HDG mode then reselecting NAV mode WARNING FOLLOWING AN AUTOPILOT OR ELECTRIC TRIM MALFUNCTION DO NOT RE ENGAGE THE AUTOPILOT OR MANUAL ELECTRIC TRIM OR RESET THE AFCS CIRCUIT BREAKER UNTIL THE CAUSE OF THE
67. quired 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 11 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F AFTER TAKEOFF GFC 700 NORMAL PROCEDURES WARNING IT IS THE RESPONSIBILITY OF THE PILOT IN COMMAND TO MONITOR THE AUTOPILOT WHEN IT IS ENGAGED THE PILOT SHOULD BE PREPARED TO IMMEDIATELY DISCONNECT THE AUTOPILOT AND TO TAKE PROMPT CORRECTIVE ACTION IN THE EVENT OF UNEXPECTED OR UNUSUAL AUTOPILOT BEHAVIOR DO NOT ATTEMPT TO MANUALLY FLY THE AIRPLANE WITH THE AUTOPILOT ENGAGED THE AUTOPILOT SERVOS WILL OPPOSE PILOT INPUT AND WILL TRIM OPPOSITE THE DIRECTION OF PILOT INPUT PITCH AXIS ONLY THIS COULD LEAD TO A SIGNIFICANT OUT OF TRIM CONDITION DISCONNECT THE AUTOPILOT IF MANUAL CONTROL IS DESIRED THE PILOT IN COMMAND MUST USE PROPER AUTOPILOT MODES AND PROPER ENGINE POWER SETTINGS TO ENSURE THAT AIRCRAFT SPEED IS MAINTAINED BETWEEN 70 KIAS AND 165 KIAS IT WILL BE NECESSARY TO CHANGE ENGINE POWER TO MAINTAIN THE DESIRED RATE OF DESCENT WHEN OPERATING AT 165 KIAS OBSERVE THE MINIMUM AUTOPILOT OPERATING SPEED OF 70 KIAS OPERATION IN PITCH PIT VERTICAL SPEED VS OR ALTITUDE HOLD ALT MODES BELOW THIS SPEED CAN RESULT IN AN AIRPLANE STALL IF INDICATIONS OF AN AIRPLANE STALL ARE PRESENT INCLUDING STALL WARNING HORN LOSS OF CONTROL EFFECTIVENESS OR AIRFRAME BUFFET DISCONNECT THE AUTOPILOT AND MANUALLY RETUR
68. r the affected axis either ROL or PIT After 10 seconds the new mode PIT or ROL will be annunciated in green Loss of selected vertical mode FLC VS ALT GS VPTH GP 1 Autopilot mode controls SELECT ANOTHER VERTICAL MODE If on an instrument approach Qi Autopilot ainiin nnr aaea DISCONNECT and continue manually or execute missed approach Loss of selected lateral mode HDG NAV GPS LOC VAPP BC 1 Autopilot mode controls 4 SELECT ANOTHER LATERAL MODE If on an instrument approach 2 Autopilot seinnu DISCONNECT and continue manually or execute missed approach 190 00492 10 Rev 8 Diamond DA 40 DA 40F 3 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F FAILURE OF THE PREFLIGHT TEST Red boxed PFT on PFD 1 AFCS Circuit Breaker cccccssssssccecssesssesscceesessessrsescevsevsesssanseee PULL WARNING DO NOT ATTEMPT TO ENGAGE THE AUTOPILOT OR OPERATE THE MANUAL ELECTRIC TRIM UNTIL THE CAUSE OF THE MALFUNCTION HAS BEEN CORRECTED NOTE When the AFCS circuit breaker is pulled the PFT FAIL annunciation will be removed and the autopilot and manual electric trim will be unavailable Do not reset the circuit breaker unless the airplane is on the ground MAXIMUM ALTITUDE LOSS DUE TO AUTOPILOT FLIGHT DIRECTOR OR AHRS MALFUNCTIONS MANEUVER ALTITUDE LOSS Climb
69. rmation in accordance with TSO C129a class Al 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 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
70. ruments 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 90 190 00492 10 Rev 8 Diamond DA 40 DA 40F FAA Approved 2 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 Low speed awareness re
71. ry 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 10 Rev 8 Diamond DA 40 DA 40F 3 12 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 3 8 2 AHRS FAILURE NOTE A failure of the Attitude and Heading 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 1 Use Standby Attitude Indicator magnetic compass and Navigation Map De COUSC essss est sess epee ra Red tise oe stectan ass Set using digital window 3 8 3 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 display
72. s Some FMS functions such as true airspeed and wind calculations will also be lost 1 Use Standby Airspeed Indicator and Altimeter 2 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 flow 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 10 Rev 8 Diamond DA 40 DA 40F 3 13 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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
73. se 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 10 Rev 8 Diamond DA 40 DA 40F 3 11 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT 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 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 reversiona
74. te VAPP annunciation cccccceeseeesseceeeeeesseeee NOTE on PFD 6 Vertical Mode and Reference ccceeeseereees SELECT on mode controller 7 Airspeed eeeeeeeee MAINTAIN 80 KIAS OR GREATER Recommended NOTE If the Course Deviation Indicator CDTI is greater than one dot from center the autopilot will arm the VAPP mode and indicate VAPP in white on the PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the autopilot will enter the capture mode when the APR button is pressed and annunciate VAPP in green on the PFD ILS LOC 1 Navigation Source eee eeeeeeseeeee SELECT LOC using CDI button on PFD 2 Course Bearing Pointer csc eeeeeeeceeeseceeeeeeeeeneeees SET using course knob 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller cee eeeeeeeeeeeneeceeeeeeneeees SELECT APR on mode controller 5 Green or White LOC and GS annunciations cee eeeeeeeeeee NOTE on PFD 6 Airspeed eee MAINTAIN 80 KIAS OR GREATER Recommended NOTE When the selected navigation source is a valid ILS glideslope coupling is automatically armed when tracking the localizer The glideslope cannot be captured until the localizer is captured The autopilot can capture the glideslope from above or below the glideslope If GS coupling is not desired it may be disabled by selecting NAV mode rath
75. ted 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 If the PFD fails or the PFD circuit breaker is pulled the autopilot will not operate If the MFD fails or the MFD circuit breaker is pulled the autopilot mode controls on the MFD will not operate Disengage the autopilot using the AP DISC button on the control stick 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 10 Rev 8 Diamond DA 40 DA 40F 4B 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 5 PERFORMANCE No change Refer to the Aircraft Flight Manual 190 00492 10 Rev 8 Diamond DA 40 DA 40F 5 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION 6 WEIGHT AND BALAN
76. 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 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
77. 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 Starlets enres Eronia eeoa Eep i SEE EEEa EE DEERE Taes PEKS ESRDE Eno ERS Eai engage 190 00492 10 Rev 8 Diamond DA 40 DA 40F 4A 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GARMIN GFC 700 AUTOPILOT DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F When engine starts Te OI PIeSSULe snper sl eeno eect i iene ees green arc within 15 sec Gu Ott Sc sai se E ds vasiens donee vs daessh EOE ys aed ote Bese sea set 1000 RPM 9 Electrical fuel pumpsen niieoe a a e a es 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 10 ALT alternator SWitCh r a ae ra eE E E ETE A ON Ti Ammeteis akg fod scahds scS55s decay tas be Sesais dv E a eves as dessa dase es aks Boece tases Check 12 Annunciator section Of PFD ccc ccecccsscccececeessssssesceessessessesseesseeseeees Check b Warm engine 1 Strob light ACL sus pata ani Ay EA E E oni aquanenlohd ON 2 Mirre e erin a sheen e a E S E R E TSn fully RICH 3 Electrical fuel pump e i ne a ON note pump noise functional check of pump AS Throttle is i hihi E E atta ss travel
78. which cause unexpected or contradictory information on the other cockpit displays It may be accompanied by the aural autopilot disconnect tone a red AFCS red AP or yellow AP indication on the PFD or a yellow CHECK ATTITUDE on the PFD The autopilot and AHRS monitors normally detect failures and automatically disconnect the autopilot Failure of the electric pitch trim indicated by a red boxed PTRM indication on the PFD may not cause the autopilot to disconnect Be alert to possible autopilot out of trim conditions see AUTOPILOT OUT OF TRIM procedure below and expect residual control forces upon disconnect The autopilot will not re engage after disconnect with failed pitch trim If AUTOPILOT OUT OF TRIM NJELE indication is present expect substantial elevator forces on autopilot disconnect 1 AP DISC Switch DEPRESS AND HOLD while grasping control stick firmly 2 Aircraft Attitude MAINTAIN REGAIN AIRCRAFT CONTROL use standby attitude indicator if necessary 3 Pitch TAn snie eau itee RETRIM if necessary using the trim wheel AAP Circuit Breaker ciraos niae e edict het EE a aSa PULL SAP DISC SWIED eso iae aaae a E Eeri Eii Ea RELEASE WARNING FOLLOWING AN AUTOPILOT AUTOTRIM OR MANUAL ELECTRIC TRIM SYSTEM MALFUNCTION DO NOT ENGAGE THE AUTOPILOT OR OPERATE THE MANUAL ELECTRIC TRIM UNTIL THE CAUSE OF THE MALFUNCTION HAS BEEN CORRECTED 190 00492 10 Rev 8 Diamond DA 40 DA 40F 3 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPL

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