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Garmin Software Version 0321.19 FAA Approved Airplane Flight Manual Supplement

1. Red arc or Yellow Green arc Red arc or bar arc or or bar Yellow bar bar arc or bar Lower Normal Upper prohibited Caution operating Caution prohibited Indication range range range range range Manifold Pressure inv H 13 30 Note 2 500 gt 2700 Bee 2700 Note 3 Oil Temp op 149 230 231 245 gt 245 Cylinder Head 476 Temp 150 475 z gt 500 op 500 Fuel Press PSI DA 40 0 14 14 35 gt 35 Note 4 ao 0 25 25 55 56 95 96 97 gt 97 Fuel flow Gal hr 1 20 gt 20 ee Q 24 1 24 1 25 25 1 30 30 1 32 gt 32 Volts Amperage zs i 2 75 2 os Amps Fuel quantity US gal Standard i an k Tanks Fuel quantity US gal 0 7 lt 0 16 i _ Long Range 19 24 Tanks 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 22 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Note 2 Not applicable to DA 40 F Manifold Pressure gauge is not installed in the DA 40 F Note 3 To prevent nuisance alerts during normal takeoffs the legend RPM and digits will not turn red or flash until the RPM exceeds 2780 Note 4 Fuel Pressure Gauge is optional for DA 40 aircraft 2 6 WARNING CAUTION AND STATUS MESSAGES The following tables show the color and significance of the warning caution and advisory messages which may appear on the G1000 displa
2. 1 Altitude Preselect 0cccccccccccccecssccceessececessseeeesseeeeesee SET to desired altitude 2 Mode Controller cccccecccccceceesssseeeeeeeees SELECT FLC on mode controller 3 Airspeed Reference ADJUST using NOSE UP and NOSE DN buttons 4 White ALT altitude preselect armed csceeseesseeseereeeeeees NOTE on PFD J Green AL Ersin e e ia r 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 000 0 ec eeeeeeeereees ADJUST TO APPROPRIATE VALUE 2 Altitude Preselect ccccccccesceeseeesseeesteeeeees SET TO DESIRED ALTITUDE 3 Vertical Mode and Reference cccceecseesseeeee SELECT on mode controller 4 White ALT altitude preselect armed ceccesceeseeeteeeeetees NOTE on PFD 5 Green AL Dyma a VERIFY UPON ALTITUDE CAPTURE 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 53 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPP
3. 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 5 Diamond DA 40 DA 40F Page 60 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM 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 LOC 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 log
4. ENGINE and investigate problem 9 ALT alternator switch ernier aniei eni i E R a ON LOM a Saaie iE A E A hit ade rata Check 11 Fuel pressure sic c 5sssts sess sssssveesieetvstvecteusetstsseseees Check no messages illuminated 12 Annunciator section Of PFD cccccecccesseceesceesseceeeceeseeseeeecsseeseeeecsseeeses Check 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 45 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F STARTING ENGINE DA 40 F only a Cold engine 1 Strobelight ACI enen oa re ER EEE VEIER ON Qi ME s e aa spiel seed eer ha sie eee ata fully RICH 3 Electrical fuel pump eee eeeceeeeeceeceseeeeesecseeeeneeeeeeeees ON note pump noise functional check of pump A Throttle oiscite ceca tein ieee ee travel forward from IDLE Sea PAME e a a aa E EE AEE s 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 moto
5. 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 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 p
6. 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 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 and roll attitude sideslip and heading Operation is possible in a degraded mode if the system loses any of these inputs Status messages alert the crew of the loss of any of these inputs The AHRS will align while the aircraft is in motion but will align more quickly if the wings are kept level during the alignment process The
7. 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 5 Diamond DA 40 DA 40F Page 27 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM 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 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 ex
8. eilines tii bap saan debe increase in order to prevent ice build up on the propeller blades 6 Alternate Air DA 40 only 2 0 0 0 cece ceseceeeceeeceeeceeecaeeeaeeeseeneeeenens OPEN 6a Carburetor Heat DA 40 F only 2000 00 ceececeeeeesceeeceeeeeeeeeeeeeeeeeseenees HOT 7 Emergency Window S cscccssesercessceseeeseceaeenseceeeseeeneeeneees 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 ATO ra a E E e ESS advise if an emergency is expected CAUTION When the pitot heating fails yellow PITOT FAIL annunciation and the alternate static valve is installed 9 Allternate static valve srein ien ia E ER REE OPEN 10 Emmerset y VOV a e ae ee a Ee ET Ee ETRE ESE close 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 35 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 3 7 2 FAILURES IN THE ELECTRICAL SYSTEM b Alternator failure An alternator failure is indicated by a red ALTERNATOR message and an ammeter indication of 0 Amps 1 Crei breakers 5 3 a A RE Check in 2 ALT alternator switche ensenis a a iii OFF then ON If alternator does not come back on line message extinguishes and ammeter indication greater than zero T Switch off any non essential electrical loads 5 Land within 30 minutes If PFD attitude i
9. engine let the starter cool for 30 minutes before further start attempts CAUTION The use of an external pre heater and external power source is recommended whenever possible in particular at ambient temperatures below 0 C 32 F to reduce wear and abuse to the engine and electrical system Pre heat will thaw the oil trapped in the oil cooler which can be congealed in extremely cold temperatures After a warm up period of approximately 2 to 5 minutes depending on the ambient temperature at 1500 RPM the engine is ready for takeoff if it accelerates smoothly and the oil pressure is normal and steady When engine starts 6 Mixture control lever sistini eea aisa rapidly move to RICH Ly OIP rESS UTE nianie eae EEE E e e AEE E iS green arc within 15 sec 8 Electrical fuel pump sven ein cited oeahiet tenet e are ea EAS OFF WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 9 ALT alternator Switch sieniin eisi iN E E R ON LO ATM trie ssse AE EE Check 1I F el pressure srine Check no messages illuminated 12 Annunciator section of PFD cccccesecsseceesceesseceeecessseeeeeecsseeeeeeecsseeeees Check 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 43 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F b Warm engine I Strobe light ACE
10. 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 GPSs has failed Refer to the MFD AUX GPS STATUS page to determine the state of the GPSs 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 is aircraft is eligible for B RNAV in accordance with AMJ20X2 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 8 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F The G1000 Integrated Avionics system as installed in this aircraft is eligible for PRNAV in accordance with PRNAV requirements JAA Administrative amp Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No 10 Airworthiness and Operational Approval for Precession RNAV Operations in Designated European Airspace 7 1 Required Functions Navigation information is referenced to WGS 84 reference system and should only be used where the Aeronautical Information Publication including electronic data and aeronautical charts conform to WGS 84 or equivalent 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 9 of 65 FAA A
11. 0 GPS SBAS receivers GIA 63W incorporating SW version 2 40 do not comply with US 14 CFR Part 91 SFAR 97 requirements for TSO C145a TSO C146a equipment See Limitations Section for requirements to the use GPS for navigation The Garmin G1000 system with GPS SW 2 40 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 g3 approach operations including those approaches titled GPS or 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 11 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F GPS and RNAV GPS approaches when used in conjunction with Garmin Prediction Program 006 A0154 01 with the 013 00235 00 antenna selection to confirm the availability of RAIM for the intended en route terminal and approach flight in addition to any NOTAMs issued for the approach 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 Nation
12. 0 INTEGRATED AVIONICS SYSTEM 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 control 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 sti
13. 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 19 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F CHARTVIEW LIMITATIONS If the optional ChartView function is installed with GDU software version 8 02 and ChartView database cycle 0709 and prior the following limitation applies At airport locations outside the United States within 1 5 either side of zero degrees latitude or longitude the aircraft symbol will be either missing or incorrectly positioned on terminal charts to include airport diagrams and approach procedures Disregard the presentation of position information on all terminal charts for airports within 1 5 either side of zero degrees latitude or longitude The list of affected airports below is subject to change by Jeppesen This list is accurate as of 30 MARCH 2007 All airports within 1 5 either side of zero degrees latitude or longitude will be affected Equatorial Region zero degrees latitude ANYN FOGR FOOG FZEA FZGN HKKI HUEN SBMD SBMQ SBUA SECO SEGS SEII SELT SEMT SENL SEQU SEST SESV SETR SKAC VRMG WIPT WIOO Prime Meridian Region zero degrees longitude DAOO DAOV DAUA DAUT DGAA DGLE EGCN EGDM EGGW EGHI EGKA EGKB EGKK EGLC EGLF EGLK EGLL EGNJ EGNV EGNX EGPB EGPM EGSC EGSS EGTC EGTF EGTK EGUB EGUL EGVN EGVO EGWU EGXC EGXE EGXU EGXW EGYD GAGO LE
14. 10 per FAA AC 20 138A FAA Order 8400 12A and FAA Order 8700 1 when used in conjunction with Garmin WAAS Fault Detection Exclusion WFDE Prediction Program part number 006 A0154 01 or later approved version with GA35 PN 013 00235 00 antennas selected Both GPS SBAS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation LRN sensor This does not constitute an operational approval The G1000 WFDE predication program works in combination with the Garmin AT Inc Route Planning Software version 1 2 or later approved version The route planning and WFDE prediction program can be 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 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 10 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F NOTE Each GIA 63W computes an independent navigation solution based on
15. 2 Annunciator section Of PFD ccc cceeecesceccccceessssscsseccssssessssvesssessesees Check b Warm engine l Strobe light ACL ci 3 tiie kid a EE ini EA RE E EE SEELE EEEIEE Ea ON 2 MRU e aar eetarea se eee E E ste OE E Atte AeA fully RICH 3 Electrical fuel DUMpiitorocneneinretese tnn e ON note pump noise functional check of pump A Throttle renne a he tein travel forward from IDLE WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts De SD UATLER s sosscses senses Lo tes dk ES EEE rest apeties eatin pied doped piace engage When engine starts 6 OU Pressures sciine ddiniiiew suisse E EE an green arc within 15 sec Te Phrotest a ethic ing tated E eesti R set 1000 RPM 8 Electrical fuel pump aine aeaeaei an eea a a REE AOE ei 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 switch ALT iraient eriari oik a E e h ON LOS AMMO tT yira a e Ee Ea Check 11 Annunciator section Of PFD sseseeeeeesseseesessseeseeressssrsereesserrerreseesrrereeseesee Check 1
16. 90 00492 10 Rev 5 Diamond DA 40 DA 40F Page 47 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F c Engine will not start after priming flooded engine T Strobelight ACL secsesicts eee asset ace ieee to E EEA casa sche E EAEEREN ON 2 Electrical fuel PUMP irese oepa eeose ranir hte neat eee OFF Bis AA bDi i o EEE E S EEE LEAN fully aft T FOON E rae EEE E A E EE 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 OES a E NP E EERS engage When engine starts 6 Throttle sic cccncenvei deeds pull back towards IDLE when engine fires Tar OIl PLESSUTE ipase nae bese sttai eee balla ae 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 2 Throttlenits4 tet iee tere was Ue Beer oe nee set 1000 RPM 9 ALT alternator s wite hisani are ER ESE ON VO Ammeters arsaa a a neh a a e a aa ee Check 11 Annunciator section of PFD 0e0sseseessesssereeseessse
17. AILURE a DISPLAY BACKUP button on audio panel PUSH button shall be OUT 3 8 1 1 AUTOMATIC ENTRY OF DISPLAY REVERSIONARY MODE If the PFD and MFD have automatically entered reversionary mode use the following procedure a DISPLAY BACKUP button on audio panel PUSH button shall be OUT NOTE After automatic entry of reversionary mode it is required to press the DISPLAY BACKUP button on the audio panel With the DISPLAY BACKUP button pushed if the problem causing the automatic entry of reversionary mode is resolved the system will remain in reversionary mode A maximum of one attempt to return to normal mode may be made using the following procedure b DISPLAY BACKUP button on audio panel PUSH button shall be IN e If the system returns to normal mode leave the DISPLAY BACKUP button in and continue e If the system remains in reversionary mode or abnormal display behavior such as display flashing occurs then return the DISPLAY BACKUP button the OUT position 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 37 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 3 8 2 AHRS FAILURE NOTE A failure of the Attitude and 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 HD
18. AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F FAILURE OF THE PREFLIGHT TEST Red boxed PFT on PFD 1 AFCS Circuit Breaker ccssssscccocsssessnsscccecevvsnsnseccessevvessnanecees 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 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 0 0 eeeceeeeeeeeeeeee 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 5 Diamond DA 40 DA 40
19. AL LELC LEVC LEZG LFBC LFBD LFBG LFBH LFBM LFBN LFBP LFBT LFBZ LFCY LFDN LFJR LFOD LFOH LFOT LFOU LFOV LFRG LFRI LFRK LFRM LFRN 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 20 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 2 3 AIRSPEED MARKINGS Marking TAS Significance Red band 20 KIAS 53 KIAS Low speed awareness stall is imminent yelow baid SP KIA 5E KIAS E Speed awareness ieduced 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 5 Diamond DA 40 DA 40F FAA Approved Page 21 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 2 5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the table below NOTE When an indication lies in the upper or lower prohibited range the legend for that display will change to the color of the prohibited range and will flash
20. AMOND MODEL DA 40 F NOTE FOR STANDARD TANKS when the fuel quantity indicator reads 17 US gal the correct fuel quantity must be determined with the fuel quantity measuring device If this measurement is not carried out the fuel quantity available for flight planning is 17 US gal FOR LONG RANGE TANKS when the fuel indicator reads 16 US gal the correct fuel quantity must be determined with the fuel quantity measuring device There are 3 US gal of 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 cecceceesseeseeceesceeseeeeeeeeceeeeeseenseenaes check 0 BAT battery SWitch 20 0 rosee n er E a eE EE E OFF P Check for loose items cin e e en ea a r a ooa S Ena EEE KEENE aea complete q Flight controls and trim seseesseeeeseeeessreessrserssesereessee free to move and correct r Bagpare neaei ae E E E E E a stowed and secure NOTE Refer to DA 40 and DA 40 F AFMs to complete the Walk around check visual inspection BEFORE STARTING ENGINE T Preflight inspections ccs8 peti a e EE aaa Ea Complete 20 Rudder pedals sos sn aas AE REKET Adjusted and locked By Passengers rennara a E E Een ee Instructed 4 Safety Harnesses ie etenee aeee aS os hon ea a All on and fastened S Reat do0rs nisin hatha ee aie is i Closed and locked 6 Door lock if installed cece ceeceeeeecsseceseeeesseeeeee Unblock
21. AUTOPILOT OVERSPEED RECOVERY Yellow MAXSPD on PFD 1 THOS aRar sae dette ee dee ee retin AA ee ee heen REDUCE When overspeed condition is corrected 2 Autopilot essaia ni 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 TAutopilotsi tciecie iy aie eee ae SELECT HDG on mode controller 2 NAV SOUT E pipinin SELECT A VALID NAV SOURCE 3 AUPS SELECT NAV or APR on mode controller If on an instrument approach at the time the navigation signal is lost 4 Missed Approach Procedure s sseseseeeeeseeeereeeerererereeee EXECUTE as applicable 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 29 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F AUTOPILOT OUT OF TRIM Yellow AIL AIL 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 OP
22. AUtOpllot vesessessneti seve ssesroenettetathereem AK E ER 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 Pilot s Guide 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 57 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEM
23. DESCRIPTIONS Not FAA Approved 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 following controls are available on the PFD clockwise from top right e Communications frequency volume and squelch knob e Communications frequency set knobs e Communications frequency transfer button e Altimeter setting knob baro set e Course knob e Map range knob and cursor control e FMS co
24. EMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 3 8 5 ERRONEOUS OR LOSS OF WARNING CAUTION ANNUNCIATORS NOTE Loss of an annunciator may be indicated when engine or fuel displays show an abnormal or emergency situation and the annunciator is not present An erroneous annunciator may be identified when an annunciator appears which does not agree with other displays or system information 1 If an annunciator appears treat it as if the condition exists Refer to the AFM Emergency or Abnormal procedures or the procedures contained in this AFMS 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 5 Diamond DA 40 DA 40F Page 39 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION IVA NORMAL PROCEDURES Not FAA Approved 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 de
25. ENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION IVB ABNORMAL PROCEDURES Not FAA Approved 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 on the ground 1 Engine speeda nsa n bates ee A h E aston dees 1200 RPM 2 Electrical equipment sceninis ia Re aidainlg aioli at OFF 3 Ammeter and voltmeter anisini sns aa iai Ennii check If the caution message does not extinguish and the ammeter legend flashes and reads zero discontinue the flight Gii Low voltage caution during flight I Electrical equipment isnan n i a i OFF if not needed 2 Ammeter and Voltmeter nen nieut iieiea wee e eE E EEN EE check If the caution message does not go out and the ammeter legend flashes and reads zero follow procedure 3 7 2 b Alternator Failure in this Supplement Gii Low voltage caution during landing Follow i after landing SECTION V PERFORMANCE Not FAA Approved No change SECTION VI WEIGHT AND BALANCE Not FAA Approved See current weight and balance data 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 58 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION VII SYSTEM
26. F Page 32 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F g High Fuel Flow DA 40 F only T Fuel Quantity e ra a a Eai iak Check and Monitor 2 Power Seting rreren ena ered dees knee 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 1 Emergency switch orei ee ain ea eet ON if installed CAUTION Switching OFF the master switch ALT BAT will lead to total loss of all electronic and electric equipment including the AHRS and attitude display However by switching the HORIZON EMERGENCY switch ON the emergency battery will supply power to the standby attitude gyro artificial horizon and the flood light In case of extreme smoke development the front canopy may be unlatched during flight This allows it to partially open in order to improve ventilation The canopy will remain open in this position Flight characteristics will not be affected significantly 2 Master switch ALT BAT soccccscedscedccccesccvsedesesciecnncesecdcocactventvetnedobtivevarevecies OFF 3 Cabin heat tic ssc hess ansalsa A AEE E Sa OFF 4 sEmersency widow S siscsistesthasteapisti tind wscvessesennt SEENA ee OPEN 5 Use standby instruments for airspeed altitude an
27. G 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 2 MCOURSE gis E E E E E EEE 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 displays 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 5 Diamond DA 40 DA 40F Page 38 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPL
28. 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 Only the Limitations Section of this supplement is FAA APPROVED Robert Murray Lead DAS Administrator Garmin International DAS 240087 CE Date d 18 Z8 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page of 65 This page is intentionally blank 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 2 of 65 Garmin Ltd Or its subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM WITH GFC 700 AUT
29. LANCE disses sissstesasSestsssnsces vshssssssuectsdonstocceseassivioossninisites 58 NOT FAA APPROVED SECTION VII SYSTEM DESCRIPTIONS csccsssssssssssessesessvsssscssvsssscsssseseeerseseeesseseesees 59 NOT FAA APPROVED 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 5 of 65 This page is intentionally blank 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 6 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION I GENERAL Not FAA Approved G1000 The G1000 Integrated Avionics System is a fully integrated flight engine communication navigation and surveillance instrumentation system The system consists of a Primary Flight Display PFD Multi Function Display MFD audio panel Air Data Computer ADC Attitude and Heading Reference System AHRS engine sensors and processing unit GEA and dual integrated avionics units GIA each containing VHF communications VHF navigation and GPS Global Positioning System GIA 63 units are standard and provide non WAAS GPS position information in accordance with TSO C129a class Al Optional GIA 63W units provide WAAS augmented GPS position If the optional GIA63W units incorporate GPS software level 3 0 or later the GPS system meets the requirements of TSO C145a The primary function of the PFD is to provide attitude heading air data navigation and alerting information to the pilo
30. LEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM 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 0 eee eeeeeeeees ADJUST TO APPROPRIATE VALUE 2 Reaching desired altitude eee SELECT ALT on mode controller Be Green AL Ae scc ests Svs a e EAN R E VERIFY on PFD Vertical Path VPTH If equipped with optional GDU 1044 1 Navigation Source cesses SELECT GPS using CDI button on PFD 2 MFD flight plan page eceeseesceeeceeeeeteeeneeees Enter Desired Vertical Profile 3 Altitude Preselect 0 0 0 ce ceeeesesesecneeereseeeees SET TO DESIRED ALTITUDE 4 Mode Controller eeeceeeeesseceeneeeeeeeenees SELECT VNV on mode controller 5 White VPTH Vertical Path armed cccccccccssscesseceseeeeseees NOTE on PFD 6 Green VPTH ososi 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 and Track 1 Navigation Sou
31. OMATIC FLIGHT CONTROL SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F LOG OF REVISIONS Revision Page Number Number s Description Approved Approval Ail inital Reisase Robert 3796 2007 Murray All Add Software Levels Robert 9 6 2007 Murray All Add Software Levels Robert 3 28 2008 Murray All Add Software Levels Robert 4 4 2008 Murray 5 All Update Software Levels See Page See Page for non WAAS 1 1 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 3 of 65 This page is intentionally blank 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 4 of 65 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 I NOT FAA APPROVED SECTION II LIMITATIONS vxcnctecauanutiamantncnslencsinantionndsantidevsianunaes 14 FAA APPROVED SECTION III EMERGENCY PROCEDUREG ccsscsssssssessesesssssesecscnssseseenerseseeserseseeeens 26 NOT FAA APPROVED SECTION IVA NORMAL PROCEDURE sccsssssssssssssssscsessvsesscnevsscscnsesesseersesesserseseseens 40 NOT FAA APPROVED SECTION IVB ABNORMAL PROCEDURES cccssssssssssssssssessesessersesessersesessersesesserseseenens 58 NOT FAA APPROVED SECTION V PERFORMANCE sccssssssssssssvssssscessssescessscesensescssensescescnssscseesessesessessesessers 58 NOT FAA APPROVED SECTION VI WEIGHT AND BA
32. Operational Approvals section 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 17 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F G1000 GPS SBAS NAVIGATION SYSTEM GIA 63W INSTALLED G1000 SYSTEM SW 0369 13 USING GPS SW 2 40 1 The Garmin G1000 GPS SBAS receivers GIA 63W incorporating SW version 2 40 do not comply with US 14 CFR Part 91 SFAR 97 requirements for TSO C145a TSO C146a equipment The following limitations apply ONLY to the GIA 63W WAAS GPS receivers using GPS SW version 2 40 The following limitations do not apply to GIA 63W incorporating SW version 3 00 or later or to the non WAAS GIA 63 GPS receivers While flying under IFR the aircraft must be equipped with an approved and operational alternate means of navigation appropriate to the flight with the exception of oceanic and remote operations For flight planning purposes if an alternate airport is required the alternate airport must have an approved instrument approach procedure other than GPS or RNAV that is anticipated to be operational and available at the estimated time of arrival All equipment required for this procedure must be installed and operational For flight planning purposes Garmin Prediction Program 006 A0154 01 with the 013 00235 00 antenna selection should be used to confirm the availability of RAIM for the intended flight in accordance with the
33. POSITE 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 S3ePrtch Tim eie hei RETRIM if necessary using the trim wheel 4 AFCS Circuit Breakers uneis desis alee eid Giessen e Ene ea PULL 5 AP DISC s Witch i e seine eileen ieee aa 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 5 Diamond DA 40 DA 40F Page 30 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F For lt AIL AIL gt Indication 1 Rudder Trim iesst aiena VERIFY slip skid indicator is centered NOTE Observe the maximum fuel imbalance limitat
34. PPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F G1000 GPS SBAS NAVIGATION SYSTEM GIA 63W INSTALLED G1000 SYSTEM SW 0321 170R LATER USING GPS SW 3 0 OR LATER 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
35. PS using CDI button on PFD 2 APPloac lies sins vsssssstass shes sesuacedesiseestesseaessgeeeeecs LOAD in FMS and ACTIVATE 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller ccccecesesesesereeeeeees SELECT APR on mode controller 5 Green or White GPS annunciation 0 cccceceescsseceseesesssesseseees NOTE on PFD 6 Vertical Mode and Reference 00 ccceceeeeeeees SELECT on mode controller 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 55 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 7 Airspeed eeeeeeeee MAINTAIN 80 KIAS OR GREATER Recommended GPS LPV LNAV VNAV LNAV V If equipped with optional GIA 63W GIA units 1 Navigation Source SELECT GPS using CDI button on PFD 2 Approach irosen reeset emt e eee eanet LOAD in FMS and ACTIVATE 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller cccccseccecesseeceesseeesseees SELECT APR on mode controller 5 Green or White GPS annunciation cccccesceescessseceeeeeesseeees NOTE on PFD 6 Green or White GP annunciation ccccccesceescecsseeeeeeeesseeeees NOTE on PFD 7 Airspeed MAINTAIN 80 KIAS OR GREATER Recommended Localizer Back Course BC 1 Navigation Source SELECT LOC using CDI button on PFD 2 Course Bearing Pointer SET
36. UFFET DISCONNECT THE AUTOPILOT AND MANUALLY RETURN 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 5 Diamond DA 40 DA 40F Page 52 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F CLIMB CRUISE and DESCENT Vertical Speed VS 1 Altitude Preselect ainen n h mna a REOR SET to desired altitude 2 Mode Controller cccccccssssccececeeeessseeeeees SELECT VS on mode controller 3 Vertical Speed Reference ADJUST using NOSE UP and NOSE DN buttons 4 White ALT altitude preselect armed ossssssesessesseeeessreeesee NOTE on PFD S Green ALT ake di ri eee 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 FLC
37. al 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 FAA Order 8400 12A and FAA Order 8700 1 when used in conjunction with Garmin Prediction Program 006 A0154 01 with the 013 00235 00 antenna selection to confirm the availability of RAIM for the intended en route 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 North Atlantic NAT Minimum Navigational Performance Specifications MNPS Airspace per AC 91 49 and AC 120 33 Both GPS SBAS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval NOTE Each GIA 63W computes an independent navigation solution based on its GPS sensor The G1000 will use the GPS sensor with the highest signal quality and will automatically revert to the other sensor if the active sensor fails or if the secondary sensor is determined to be more accurate An AHRS 1 GPS message displayed in the ALERTS window means that one of the GPSs has failed Refer to the MFD AUX GPS STATUS page to determine the state of the GPSs Enroute and Terminal includ
38. are Version number The LRU serial numbers displayed on the screen are for convenience only and should be disregarded in determining the LRU software revision For compliance activities requiring LRU serial number determination the unit serial number used must be that on the physical LRU label not the one displayed on the SYSTEM STATUS page LRU Software Version WAAS Non WAAS WAAS Non WAAS GDC 2 05 GEA 2 07 GIA 1 amp 2 5 31 GMA 3 03 GMU 2 01 GPS 1 amp 2 2 40 GRS 1 2 10 GTX 1 4 06 MFDI 8 02 PFD 1 8 02 GDL 3 10 GSA 2 06 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 14 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F LRU Software Version WAAS WAAS Non WAAS GDC 1 302 CT 3a GEA POE 2007S FP 207 GIA 1 amp 2 s a J 56a 50o GMA 303 d soa f 3o O GMU 20 Tn GPS 1 amp 2 30 8803 GRS DN 2u ou e GTX 1 406 4 4o MFD1 901 9 f ooa O PED 1 90 9 o O GDL 3 20 00 320 00 320 00 GSA 206 2 2 The system s databases and System Software Version number are displayed on the MFD Power up page immediately after system power up and must be acknowledged The LRU software versions can be verified on the AUX group sub page 5 AUX SYSTEM STATUS along with the system s databases 3 Operation is prohibited north of 70 N and
39. as an area of coverage that includes the United States Canada Mexico Latin America and South America c The Obstacle Database has an area of coverage that includes the United States NOTE The area of coverage may be modified as additional terrain data sources become available To avoid unwanted alerts TAWS must be inhibited when landing at an airport that is not included in the airport database The ADF aural identifier must be monitored any time the ADF is used as the primary source of navigation 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 WAAS integrity monitoring must be available at the Final Approach Fix If there is not sufficient GPS WAAS integrity at any time after crossing the Final Approach Fix a Loss Of Integrity LOI will be annunciate
40. ass 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 FAA Order 8400 12A and FAA Order 8700 1 Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval North Atlantic NAT Minimum Navigational Performance Specifications MNPS Airspace per AC 91 49 and AC 120 33 Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval NOTE Each GIA 63 computes an independent navigation solution based on its GPS sensor The G1000 will use the GPS sensor with the highest signal quality and will automatically revert
41. bett estates release 29 Teandanis Hghta niue a a a a ar N ieies ON as required 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 51 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM 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 B
42. cetvca a nciu wckveds eeciaaiates Grats cc toca bee ede dete Aaetane a eee ON 2 Electrical fuel pUMp oo eee eee eseceeceeeeeeeseceeeeceeeeeeeeees ON note pump noise functional check of pump 32 Whrottles ssc eet eee E 3 cm 1 2 in forward from IDLE measured from rear of slot 4 Mixture control lever ceccecceceesseceeeseeeeenee RICH for 1 3 sec then LEAN WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts Ds Temitiom switebs c sieessisc seuss essceuotit she TAES START When engine starts 6 Mixture control lever oo eee ieia rapidly move to RICH Ds MOUSPLESSULE i 5 285 tort eh eesou the erase rae A Wieeeeot ui E o green arc within 15 sec WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 8 Electrical fuel PUMP e a rrari eleta e aera Cers a EES Ea a ESEG OFF 9 ALT alternator SWitCh cesserunt ENEE E ON 10 Ammeter nin E E in eee E a a RT Check Il Fuel press ren aiima Check no messages illuminated 12 Annunciator section Of PFD sessseeesssesesssesersresteeesst
43. ck 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 Loss of instruments or components of the G1000 system will affect the GFC 700 AFCS as follows 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 62 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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 autopilot 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 comp
44. d 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 hs sBAE battery s wite hiss a anes sacs oey a E E E E a ata hesens ON 8 JESS BUSeS witcha EAEE EE E A nes eit onset Soe E oe 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 5 Diamond DA 40 DA 40F Page 33 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM 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 0 ccc cccccescesscecessceeececseceeseeceeeeeseeceseeeeseeceeeeeaaees ON Ts ESS BUS Switch a r a E ines seed te daesssncoivas O EE sect ecosa OFF 12 BATT and ESS TIE circuit breakers 0 ecccecccceccesessscsseeseessssseseseeseesees 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 Alterna
45. d on the HSI and the approach mode will be aborted IFR non precision approach approval using the GPS SBAS sensor is limited to published approaches within the U S National Airspace System Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority Use of the Garmin G1000 GPS SBAS receivers to accomplish ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for or GPS is not authorized Use of the G1000 VOR LOC GS receivers to fly approaches not approved for or GPS requires that VOR LOC GS navigation data is selected and presented on the CDI of the pilot flying i e proper CDI source selection 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 16 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F NOTE Not all published approaches are in the AVIATION database The flight crew must ensure that the planned approach is in the database 6 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 7 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 8 RNP operations are not authorized except as noted in the
46. e battery will not be charged unless the essential tie relay bypass OAM 40 126 is installed 21 BAT battery SWICK tice ccscccscascsleecatctees aectbercavidevi avenlaesaucdava iee ir ON 22 Fuel tank Selector ccccecccececccecececececececececececececececececsceeeeeeeeesesess on fullest tank WARNING Never move the propeller by hand while the ignition is switched on as it may result in serious personal injury Never try to start the engine by hand 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 42 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F STARTING ENGINE DA 40 only a Cold engine 1 Strobe Tight ACI EE sceavaiacesssk S vesaazennees ON 2 Electrical fitel PUP oeiee pener ea ea ON note pump noise functional check of pump J Throttle e r EO E eSNG 3 cm 1 2 in forward from IDLE measured from rear of slot 4 Mixture control lever s nsssseseeeeseseesseseessereeee RICH for 3 5 sec then LEAN 3o Throttle etena eraa a E e 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
47. e force A slight downward pressure on the canopy may be required to ease the handle operation 6 Door warning light DOOR OPEN Check no messages illuminated T Fuel tank selectOr evict este Bivens bial aie REA a ee fullest tank 8 Engine Mstruments c 5202 ccesesesesdtaseas psseusatlesSesbronssctespesteocsebeotases in green sector O Circuit breakers vey cies aces seer diated eean tessa apt sees heey pressed in 10 Fuel pressure egion Check no messages illuminated TT Flectrie fuel pump rni osseous ene EEE AE EEE E EE ee be ON 12 Mixture control lever ccccccccccscesssecssecesececsseeesseeeesaeens 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 a Ee 1 o A aE E TT check T O WA D E Ta a MESA E EEEE EET check T O 15 Fight Conttols eeke e e free movement correct sense 16 Throttle nnie r e a e eos Se S ES 2000 RPM DA 40 1800 RPM DA 40 F 17 Magneto chetka picninn e nE Sina ee 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 n
48. ed key removed Tis Front CANOPY et sssstes ches e e e Aa A Position 1 or 2 cooling gap 8 Canopy lock if installed 0 eee eeeeeecneeeeeneeeeeeee Unblocked key removed 9 Parking brake mnei ic oae aane E ae BL eles ee in es Set 10 Flight controls s es Freedom of movement and proper direction 11 Trimewheel saecah i n bolas dense atiou E A ak T O 12 Friction device throttle quadrant ccceesseesceesceeeceeeceseeeeceeenseenseenes Adjusted AB Thrott errer n set cbeotcnstasswupesceben th E E Sale A R Ea NANE IDLE 14 Mixture control lever s s sesssesensseseesesseeeessrseessesersteseeseseestesereenseeeessrsersee LEAN 15 RPM lever DA 40 only ji sortisi nerenin ntas HIGH RPM 16 Carburetor heat DA 40 F only eee eee ceeeeesseceeececnseceeeeeceeeeneecseeeeneees COLD 17 Alternate air DA 40 only ee eeceecesceeseeeeceeeeeseceseceaeceeeeneecneeeneeeeeees CLOSED 18 Alternate Static Valve cece cccccccccessceceessececesseeecsssseeeenee CLOSED if installed 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 41 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 19 Avionics master SWitCh ccccccccccesessessccsececsessssscsseecsesseessseceeceessesesssceseenees OFF 20 Essential Bus SWitch ccccccccssssssssscvccvscsssscceccecessssseececcecscssssssesescessssans OFF CAUTION When the essential bus is switched ON th
49. ed 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 5 Diamond DA 40 DA 40F Page 13 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION II LIMITATIONS FAA Approved 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 0369 13 P N 190 00324 07 Revision A or later appropriate revision 0321 17 P N 190 00324 08 Revision A or later appropriate revision 0321 18 P N 190 00324 09 Revision A or later appropriate Or revision 0321 19 2 The G1000 installation in the DA 40 requires the following or later FAA approved LRU software versions Approved LRU software versions are referenced to the System Softw
50. eeesseees NOTE on PFD 6 Vertical Mode and Reference ccccceeseeseees 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 VAPP button is pressed and annunciate VAPP in green on the PFD ILS LOC 1 Navigation Source SELECT LOC using CDI button on PFD 2 Course Bearing Pointer cece eeeeceseeeeeecneeeeeeeeeeens SET using course knob 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller ee eeeceessceeneeceeeeeeeeeeee SELECT APR on mode controller 5 Green or White LOC and GS annunciations ccceeeeee 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 rather than APR mode GPS LNAV 1 Navigation Source SELECT G
51. ertssreessteeessesesreseesess Check 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 44 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F c Engine will not start after injection flooded engine Warm engine 1 Strobe light ACL aciari aan tee odin detec renea Sieh aie anise EES ON 2 Electrical fuel PUMP eee cece ceeeeeceseeeeesecneeeeneeeeeeaees ON note pump noise Functional check of pump 3 Mixt re control lever reseno ieoa retea a ae kari Ear aipa LEAN fully aft A Bi TEOS A lO EE EEEE A E E atonal eledaess at mid position WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts 5 Teniton switch 3 206 regeire ane prie deh aati a E EN ei START 6 Throttlesissesisisisi isisisi isssirenissosss pull back towards IDLE when engine starts When engine starts 7 Mixture control lever reniir i iii iiia rapidly move to RICH 8 OI Pressures apren ioe ar E E lies green arc within 15 sec WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF
52. ght 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 MASURIEN I ARE aE SEEE SEN P E E cd cebeguatechige EETA 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 successful 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 ssseseesesseeereseesstsrrresrerssrsesrrrreretsersesreereree NOTE 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 49 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F BEFORE TAKE OFF 1 Position airplane into wind if possible 2 Parking Drake isinen ne e a Ea E E e A aoea ae set 3 Safety Wamesses se ea ae E eoa aorar S ap a aE Ea EREE ETEA on and fastened Ay Reat COOP re e ee n aaeeea ated eee EA check closed and locked o E oI 1121010 oA AAE EE E E EE EESE 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 undu
53. ic 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 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 5 Diamond DA 40 DA 40F Page 61 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G100
54. ing AP on the PFD accompanied by a continuous autopilot disconnect tone The disconnect tone and flashing alert may be cancelled by pressing the AP DISC switch or the left side of the MET switch 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 63 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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 Refer to the Garmin G1000 Cockpit Reference Guide for descriptions of the G1000 and GFC 700 system and operating procedures Refer to the following table to determine the appropriate guide The System Software Version number is displayed at the top right side of the MFD Power up page System Software Version Pilot s Guides 0369 13 Garmin G1000 Cockpit Reference Guide CRG P N 190 00324 07 Revision A or later appropriate revision 0321 17 0321 18 or 0321 19 Garmin G1000 Cockpit Reference Guide CRG P N 190 00324 08 Revision A or later appropriate revision Garmin G1000 Cockpit Reference Guide CRG P N 190 00324 09 Revision A or later appropriate revision 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 64 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 7 10 FUEL
55. ing 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 is 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 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 12 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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 ELECTRONIC FLIGHT BAG The G1000 Integrated Avionics System as installed in this aircraft has been approved as a Hardware Class 3 Software Type C Electronic Flight Bag EFB in accordance with AC 120 76A when using current FliteChart or ChartView data Additional operational approvals may be required For operations under part 91 it is suggest
56. ion If annunciation remains 2 Control Stick ccs iiensce erases aana 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 3 AP DISC Switch sii cavitation aan eion sini ean lade DEPRESS 4 Autopilot nenna 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 for 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 2 AULOPIOt i iien is 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 2 eee ienn iaae DISCONNECT and continue manually or execute missed approach 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 31 of 65 FAA APPROVED
57. its GPS sensor The G1000 will use the GPS sensor with the highest signal quality and will automatically revert to the other sensor if the active sensor fails or if the secondary sensor is determined to be more accurate An AHRS 1 GPS message displayed in the ALERTS window means that one of the GPSs has failed Refer to the MFD AUX GPS STATUS page to determine the state of the GPSs 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 is 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 GPS SBAS NAVIGATION SYSTEM GIA 63W INSTALLED G1000 SYSTEM SW 0369 13 USING GPS SW 2 40 The Garmin G100
58. local aviation authority guidelines for TSO C129a equipment WAAS NOTAMs or their absence and generic prediction tools do not provide an acceptable indication of the availability for the GIA 63W equipment When flight planning an LNAV VNAV or LPV approach operators should use the Garmin Prediction Program 006 A0154 01 with the 013 00235 00 antenna selection in addition to any NOTAMs issued for the approach 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 18 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 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 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 6 ILS approaches using the GFC 700 autopilot flight director are limited to Category I approaches only 190
59. nformation is lost prior to landing ESS BUS switchs 2 a sch0dnn kde ese etal Menai aie ON 6 HORIZON EMERGENCY Switch ceeseeeecseeeeeseeseseessecaeesecneseeseaeeees 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 those busses These items of equipment can be supplied with power by the battery for at least 30 minutes During this 30 minute period the airplane must be landed at a suitable airport Economical use of electrical equipment in particular of pitot heat and switching off equipment that is not needed extends the time during which the other equipment remains available 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 36 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F For cases in which the battery capacity is not sufficient to reach a suitable airport an emergency battery is installed to power the standby attitude gyro 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 F
60. ntrol buttons and knob e PFD softkey buttons including master warning caution acknowledgement e Altitude reference set knob e Heading bug control e Navigation frequency transfer button e Navigation frequency set knobs e Navigation frequency volume and Identifier knob The PFD displays the crew alerting annunciator system When a warning or caution message is received a warning or caution annunciator will flash on the PFD accompanied by an aural tone A warning is accompanied by a repeating tone and a caution is accompanied by a single tone Acknowledging the alert will cancel the flashing and provide a text description of the message Refer to the Emergency or Abnormal Procedures Sections of the AFM or this Supplement for the appropriate procedure to follow for each message Advisory messages related to G1000 system status are shown in white and are accompanied by a white flashing ADVISORY alert Refer to the G1000 Pilot s 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 59 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Guide and Cockpit Reference Guide for descriptions of the messages and recommended actions if applicable Trend vectors are shown on the airspeed and altimeter displays as a magenta line predicting 6 seconds at the current rate The turn rate indicator also functions as a trend indicator on the compass scale The PFD can
61. ointer 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 FUEL QTY GAL will turn red and flash continuously in inverse video 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 65 of 65
62. ot run unduly roughly 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 50 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 18 RPM lever DA 40 only neseser pull back until a drop of max 500 RPM is reached HIGH RPM Cycle 3 times 18a Carburetor Heat DA 40 F only eee eeeecsseceeeeceereeeneeceeeeeneees check function 18b Throttle DA 40 F only MAX PWR minimum 2200 RPM NOTE DA 40 F only The result of the ground check at full throttle depends on a number of environmental factors e g temperature ambient air pressure and in particular head or tailwind components Headwind will cause a higher RPM than tailwind 193 Throtlec erini a E E AEEA set 1000 RPM 20 Carburetor Heat DA 40 F only essesssesssessesssesrssrssressrrssresseresesees check COLD 21 Alternate Air DA 40 only esesesessesseessssrseessesersresesseserseeseesess check CLOSED 22 Flight Planine a E aa E R RER entered 237 Altimeter S tting eines eretia rer aae Tak a aa ao aa e A a tas beers checked set G1000 and standby altimeter 24 Altitude preselector eececcesceessesseeesceseceeeceseceseceaecseecseecaeeeaecaeecaeeeaeeeeeeeneensees set 25 RAQIOS taiseok eetavece E E Maree E E Phone een ees set and checked 26 TranspOndetvisssccch c teeta eee ne aa eee as code set 27 Standby attitude Cyr aroia a erect and no flag 28t Parking brake coinean R aoe Ab
63. pect residual control forces upon disconnect The autopilot will not re engage after disconnect with failed pitch trim If AUTOPILOT OUT OF TRIM ELE 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 TAM nietin tkr ates RETRIM if necessary using the trim wheel 4 AP Circuit Breakers ica sceese lite aaar e esting sre Seati oira eeediepee te PULL SAP DISC Switch nn ele eileen a Tee E tebe 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 5 Diamond DA 40 DA 40F Page 28 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F AUTOPILOT DISCONNECT Yellow AP flashing on PFD 1 AP DISC SWitch oo eeseeseceseeeeeesececesecneeeeeneeeees DEPRESS AND RELEASE to cancel disconnect tone 2 Pitch Trim setepinne 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
64. r for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts CAUTION The use of an external pre heater and external power source is recommended whenever possible in particular at ambient temperatures below 0 C 32 F to reduce wear and abuse to the engine and electrical system Pre heat will thaw the oil trapped in the oil cooler which can be congealed in extremely cold temperatures After a warm up period of approximately 2 to 5 minutes depending on the ambient temperature at 1500 RPM the engine is ready for takeoff if it accelerates smoothly and the oil pressure is normal and steady 6 Startet iae a eee e E a E E ei E S engage 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 46 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F When engine starts Tes OM PLESS ULC A innritar A E RR green arc within 15 sec Se r Throttle eniinn enie Ake aee ee ia eoue ne Revues Assos EE raiik set 1000 RPM 9 Electrical fuel pump iiissiseescsceccesse tess esietteeiesensiedvsi eats ek ela Ena eni 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 ienesis sneti nsn n E se ON T Ammeter nisun n EO Check 1
65. rce 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 ceeeeesseceeneeeseeeenees SELECT NAV on mode controller 5 Green or White VOR or GPS annunciation eee eeeeeneeeee NOTE on PFD 6 Vertical Mode and Reference esceseeceeeees 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 5 Diamond DA 40 DA 40F Page 54 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F APPROACH VOR 1 Navigation Source cesses SELECT VOR using CDI button on PFD 2 Course Bearing Pointer cesses eeeeeceeeeeeneeeeeeaees SET using course knob 3 Intercept Heading 0 ESTABLISH in HDG or ROL mode if required 4 Mode Controller ccccceccescccessseeesseeeeeeee SELECT APR on mode controller 5 Green or White VAPP annunciation cccecccceeseesteceee
66. reerssssseresssssserereessesrrereese Check 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 48 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F BEFORE TAXIING I Avionics master SWiteh s icci ovis a ae oss eande ete ten acted aa ON 2 Electrical equipment 0 eee ceeeeecseesseeeeeseceeeeceeeecaeeeeeseeneeeeens On as required Bs Flap e aa eaa a a aa e aaa UP T O LDG T O indicator and visual check 4 Flight instruments and avionics ceceeeees set test function as required set both altimeters 5 Floodlight meaa ee ee ON test function as required 6 Ammeter iic ssisssaonteeudnsasiunnases check if required increase RPM 7 Fuel tank selector ccccecceeseeeeeseeeeeeeeeeees change tanks confirm that engine also runs on other tank at least 1 minute at 1500 RPM 8 Pitot heating 25 04 set iensen ea noes bias es ON test function HA a aida Melanie no yellow PITOT FAIL annunciation 9 Pitot beatin gs oso pthess tee aa a a e Ee E EAA NEEE OFF if not required E E E AEA AAS yellow PITOT OFF annunciation 10 Strobe lights ACLS s sesessseeesseseesssserssesresesseeeessesees check ON test function tore E E EE E des Pea E E E S E A E eased as required 11 Position lights landing and taxi lights 0 ON test function as required CAUTION When taxiing at close range to other aircraft or during ni
67. roved Page 25 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F SECTION III EMERGENCY PROCEDURES Not FAA Approved 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 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 TAWS N A or red TAWS FAIL annunciator will be displayed on the PFD left of selected altitude or on the MFD TAWS page lower right hand corner If the GPS NAV LOST annunciation is displayed the system will flag and no longer provide GPS based navigational guidance The crew should revert to the G1000 VOR ILS receivers or an alternate means of navigation other than the G1000 GPS receivers If the LOI Loss of Integrity annunciation is displayed in the enroute oceanic or terminal phase of flight continue to naviga
68. s inoperative 2 13 KINDS OF OPERATION Minimum operational equipment serviceable Number VFR VFR Equipment installed Day Night IFR Primary Flight Display 1 1 1 1 Multi Function Display 1 1 1 1 Audio panel 1 1 1 1 Air data computer 1 1 1 1 Attitude and Heading Reference 1 0 1 1 System Static dischargers 7 0 7 GPS 2 0 1 2 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 5 Diamond DA 40 DA 40F FAA Approved Page 24 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 2 15 Limitation Placard Below the MFD next to the fuel quantity indication Standard Tanks Fuel qty Indication max 17 US gal Max difference LH RH tank 10 US gal For use of max tank capacity see AFM Long Range Tanks Fuel qty Indication max 24 US gal Refer to AFM to use entire tank capacity Max difference LH RH tank 8 US gal 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA App
69. scribed 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 oe ceeereeeeeeeeeeeeeeeeee flight planning complete b Airplane document c ceecceeeeeceeeeeeeeeeeceeeeseeneeeees complete and up to date cC Agmition key ereire a E E e R e eles pulled out d Front canopy amp rear doof 2 eee eeeeeeceeecesecesecnseceeeeneeens clean undamaged e All electrical equipment eee eeceeeeceseeeceseceeesecseesecneeecsaeeeceaecaeeseenerats OFF f Circuit breakers eeeeeeeee set in if one has been pulled check reason g Engine control levers cseeeeee check condition freedom of movement Full travel of throttle Full Travel of RPM DA 40 only Full Travel of mixture lever We Throttle i isnin ha is eo eh gs eens IDLE i Mixture control lever ceccccccecccccccessceceensececesssecccsseeceensececeenseeeenssseeees LEAN J RPM lever DA 40 only ainoat aa HIGH RPM k Carburetor Heat DA 40 F only eeeceeeeceesceceeeceeeeceseeeenceeeneecaeeeeees COLD D BAT battery Switch sycsiccices Aven A sits a a Bhd cv aa A an ena eek ON m Fuel Quantity eeceecceesceecceecceeeceeeceseceaecaeeceeeneeeeeeeeees check fuel qty on EIS check with fuel qty measuring device 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 40 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DI
70. south of 70 S latitudes In addition operation is prohibited in the following two regions 1 north of 65 N between 75 W and 120 W longitude and 2 south of 55 S between 120 E and 165 E longitude 4 The fuel quantity fuel required and fuel remaining functions of the FMS are supplemental information only and must be verified by the flight crew 5 Navigation must not be predicated upon the use of the TAWS Terrain or Obstacle data displayed by the G1000 6 TAWS must be inhibited prior to the Final Approach Fix FAF when conducting an instrument approach that terminates in a circling to land or side step maneuver 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 7 Pilots are authorized to deviate from their ATC clearance to the extent necessary to comply with terrain obstacle warnings from TAWS 8 The Terrain Obstacle Airport databases have an area of coverage as detailed below 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 15 of 65 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F a The Terrain Database has an area of coverage from North 75 Latitude to South 60 Latitude in all longitudes b The Airport Terrain Database h
71. t 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 5 Diamond DA 40 DA 40F Page 7 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Operational Approvals G1000 GPS NAVIGATION SYSTEM GIA 63 INSTALLED GIA 63 units are standard and provide position information in accordance with TSO C129a cl
72. te 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 5 Diamond DA 40 DA 40F Page 26 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F 9 In an in flight emergency depressing and holding the COM transfer button for 2 seconds will tune the emergency frequency of 121 500 MHz If the display is available it will also show it in the Active frequency window 10 If the white TAWS N A status annunciator is displayed on the PFD or MFD TAWS page the system
73. to ILS front course using course knob 3 Intercept Heading 0 ESTABLISH in HDG or ROL mode if required 4 Mode Controler iscrisse SELECT NAV on mode controller 5 Green or White BC annunciation see ee eeeesecseeseeeereeeeeeeees 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 cceeececeeeeeeees SELECT on mode controller 7 Airspeed eeeeeeeee MAINTAIN 80 KIAS OR GREATER Recommended GO AROUND 1 Control Stick scsi a Ba NS GRASP FIRMLY 2 GA Dutto rerien iei 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 Landin gires ninenin nn e n aan ene EXECUTE 4 Missed Approach Procedure sseeeeseeeeeeeeeee eee EXECUTE as applicable 5 Altitude Pr sele t snio esssee stss rin isase SET to appropriate altitude At an appropriate safe altitude 6 Autopilot Mode Controller SELECT appropriate lateral and vertical 190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 56 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F modes on mode controller T
74. tor 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 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 5 Diamond DA 40 DA 40F Page 34 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM 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 Pitot heating sch ci aah ane ai Se ead ON COP 1 0 11 0i DTE 1 Gene re E eee ON A Air distributionlever s esccscccseaiseestasssecstasesseniasivenscseedssgeneevnsesteusessatevens A UP Sy RPM
75. uter 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 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 flash
76. 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 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
77. ys 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 Operation of the starter without the key in STARTER ENGD the start position or failure of the starter motor to disengage from the engine after starting Front canopy and or rear door not MACROPEN completely closed and locked Caution annunciations Yellow Annunciation Cause PITOT OFF Pitot heat is not switched on PITOT FAIL Fault in the pitot heating system Fuel quantity in the left tank is less than 3 Pe US gal 1 US gal Fuel quantity in the right tank is less than 3 eerie ie US gal 1 US gal LOW VOLTS On board voltage below 24 volts 190 00492 10 Rev 5 Diamond DA 40 DA 40F FAA Approved Page 23 of 65 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F Advisory annunciations White Annunciation Cause PFD FAN FAIL The cooling fan for the PFD is inoperative MFD FAN FAIL The cooling fan for the MFD is inoperative GIA FAN FAIL The cooling fan for the GIA i

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