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Garmin Software Version 0321.22 FAA Approved Airplane Flight Manual Supplement

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Contents

1. ARR Item Notes Preferred Rating ESD Sensitive Moisture Sensitive Limited Shelf Life Magnetic Sensitive Item Attribution 1 of 1 Item 190 00492 12 Rev 6 ECO 099458 Creation Date 17 May 2013 12 50 PM CST
2. 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 Indication Red arc or Yellow Green arc Yellow Red arc or bar arc or or bar arc or bar bar bar Lower Normal Caution Upper prohibited Caution operating range prohibited range range range range Manifold 13 30 Pressure In Hg Note 1 RPM 500 gt 2700 2700 Note 2 Oil Temp 149 230 231 245 gt 245 F Cylinder Head 150 475 476 2500 Temp 500 F Fuel Press PSI 0 14 14 35 gt 35 DA 40 Note 3 Oil Press 0 25 25 55 56 95 96 97 gt 97 PSI Fuel flow 1 20 gt 20 Gal hr Voltage 0 24 1 24 1 25 25 1 30 30 1 32 gt 32 Volts Amperage 2 75 Amps Fuel quantity 0 gt 0 3 gt 3 17 US gal Standard Tanks Fuel quantity 0 gt 0 3 23 16 s US gal gt 19 24 Long Range Tanks 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT Note 1 Not applicable to DA 40 F Manifold Pressure gauge is not installed in the DA 40 F Note 2 To prevent nuisance alerts during normal takeoffs the legend RPM and digits will not turn red or flash
3. engine speeds up to 2700 RPM are permissible without time limit 8 vie EE EE aie advise if an emergency is expected CAUTION When the pitot heating fails yellow PITOT FAIL annunciation and the alternate static valve is installed 9 Alternate static valve ssis se ee see se ek ee ee Ge Re Ge ee GR ee AAR Re SA Ge ee Ge ee OPEN 10 Emergency WIndOW S issie Vee sesde EE vae VR Ek SEE dek so tenine p bee ek eE Sneg close 190 00492 12 Rev 6 Diamond DA 40 DA 40F 3 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 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 vE1reditbreakerss ss eee eae ea ea as Check in 2 ALT alternator switch iese see se ee ee ee ee RA ee Ge Re ee Ge Re ee ee OFF then ON If alternator does not come back on line message extinguishes and ammeter indication greater than zero 3 ESS OE Ge RE OE OE EE OE ON 4 Switch off any non essential electrical loads 5 Land within 30 minutes If PFD attitude information is lost prior to landing 6 HORIZON EMERGENCY Switch issie ese sesse se ee se ees ee se ee ee see see see ese eke se ee ON CAUTION The following items are available on the Essential Bus PFD in composite backup format NAV COM 1 GPS 1 Attitude
4. BACKUP button on the audio panel button OUT causes both the PFD and MED 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 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 Traffic Information System 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 12 Rev 6 Diamond DA 40 DA 40F 7 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT G1000 KAP 140 INTERFACE The G1000 system provides heading and course information lateral and vertical navigation flags and both lateral and vertical c
5. GIA 63W INSTALLED The Garmin G1000 GPS SBAS receivers GIA 63W incorporating SW version 3 0 or later approved version and GA35 PN 013 00235 00 antennas are approved under TSO C145a TSO C146a equipment Class 3 and installed in accordance with AC 20 138A The Garmin G1000 system has been demonstrated capable of and has been shown to meet the accuracy requirements for the following operations provided it is receiving usable navigation data e The G1000 Integrated Avionics system as installed in this aircraft complies with AC 20 138A for navigation using GPS and WAAS within the coverage of a Space Based Augmentation System complying with ICAO Annex 10 for IFR en route terminal area and non precision approach operations including those approaches titled GPS or GPS and RNAV GPS approaches The G1000 Integrated Avionics system installed in this aircraft is approved for approach procedures with vertical guidance including LPV LNAV VNAV and LNAV V within the U S National Airspace System The G1000 Integrated Avionics system as installed in this aircraft has been found to comply with the requirements for GPS as a Primary Means of Navigation for oceanic and remote navigation RNP 10 per FAA AC 20 138A and FAA Order 8400 12A when used in conjunction with Garmin WAAS Fault Detection Exclusion WFDE Prediction Program part number 006 A0154 01 or later approved version with GA35 PN 013 00235
6. WITH HONEYWELL KAP 140 AUTOPILOT SECTION 3 EMERGENCY PROCEDURES GENERAL 1 If Garmin G1000 GPS navigation information is not available or invalid utilize remaining operational navigation equipment as required If the G1000 system reverts to Dead Reckoning mode indicated by DR displayed on the HSI the moving map will continue to be displayed Aircraft position will be based upon the last valid GPS position and estimated by Dead Reckoning methods Changes in winds aloft can affect the estimated position substantially Dead Reckoning is only available for 20 minutes in Oceanic and Enroute modes Terminal and Approach modes do not support DR If Garmin G1000 GPS navigation information is not available or invalid and the TAWS option is installed TAWS will not be available A white TAWS N A or red TAWS FAIL annunciator will be displayed on the PFD left of selected altitude or on the MFD TAWS page lower right hand corner If the GPS NAV LOST annunciation is displayed the system will flag and no longer provide GPS based navigational guidance The crew should revert to the G1000 VOR ILS receivers or an alternate means of navigation other than the G1000 GPS receivers If the LOI Loss of Integrity annunciation is displayed in the enroute oceanic or terminal phase of flight continue to navigate using the GPS equipment or revert to an alternate means of navigation other than the G1000 GPS receiver appropriate to the rout
7. 2 b Alternator Failure in this Supplement iii Low voltage caution during landing Follow i after landing 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4B 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT AVIONICS COOLING FAN FAILURES NOTE These caution messages are indicated when a cooling fan has failed The avionics may overheat especially in hot temperatures a PFD FAN FAIL caution ON GROUND 1 Do not takeoff in night or in instrument meteorological conditions IN FLIGHT 1 Monitor for PFD OVERHEAT caution message b MED FAN FAIL caution ON GROUND 1 Do not takeoff in night or in instrument meteorological conditions ma IN FLIGHT 1 Monitor for MFD OVERHEAT caution message c GIA FAN FAIL caution ON GROUND 1 Do not takeoff in night or in instrument meteorological conditions IN FLIGHT 1 Minimize all COM transmissions to reduce temperature 2 Monitor for GIA 1 and GIA 2 OVERHEAT caution messages 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4B 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT PFD MFD AND GIA OVERHEAT a PFD OVERHEAT caution NOTE The PFD is approaching its operating temperature limit Display brightness is
8. DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT BEFORE TAKE OFF 1 Position airplane into wind if possible Die Parking Brake ME tes ERENS ies ees Ee De secu ee EN ee Ee ed set 3 Safety haTnESSES re Ee BERGE ONSE roras ip ee Gee SORG Ee ETER on and fastened A REAL dOOR de Res spose ep dee de Riek noe ge Ee eg check closed and locked 5 ooi de UR AO EE OE EE N closed and locked CAUTION When operating the canopy pilots operators must ensure that there are no obstructions between the canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward pressure on the canopy may be required to ease the handle operation 6 Door warning light DOOR OPEN sesse ese Check no messages illuminated 7 Fuel tank selector siisii issssvsocsecssestucstecetisstusbessssnssstessyssseussdatseesesbssts fullest tank Sie Engine mstrurnents is 2226 0 GESE EE NE Res Ee the tesPhesasheotse ii in green sector OG ie Di ee EE N EE RE OE eee ean Ae pressed in 10 Fuel pressure sissies see SEE GER EE ee EO wicks tbe Check no messages illuminated 11 Electric fuel POP reeds RE EERS EE Ge EER Ges Se Ge eee ane ON 12 Mixture control lever esse es see ee ee ee Ge Re ee Re ee 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 se
9. TSO C129a class Al The Garmin G1000 system has been demonstrated capable of and has been shown to meet the accuracy requirements for the following operations provided it is receiving usable navigation data e 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 e The G1000 Integrated Avionics system as installed in this aircraft has been found to comply with the reguirements for GPS as a Primary Means of Navigation for oceanic and remote navigation RNP 10 per FAA AC 20 138A and FAA Order 8400 12A Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval North Atlantic NAT Minimum Navigational Performance Specifications MNPS Airspace per AC 91 49 and AC 120 33 Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval NOTE Each GIA 63 computes an independent navigation solution based on its GPS sensor The G1000 will use the GPS sensor with the highest signal quality and will automatically revert to the
10. after priming flooded engine 1 2 3 4 3 Strobe light ACL 2 023 sce EERS ER Ge iden ely REED es ald ON Electrical fuiel pump AE RE N EE OR EE Ee KEN OFF Mixtiite EE AE EE GE OE DEE LEAN fully aft due EE cs EE OE OE OE OE 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 Startel eve ER EE ie Gis Hata nasa ET RE ik engage When engine starts 0 Throttle rise e pull back towards IDLE when engine fires Te OU DIeSSUIE LE EE eeen ee oek Sire IE Eed 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 8s Throttle secon ie ig Sie area nara N E Se rg RU tae set 1000 RPM 9 ALT alternator SWitCh pre ee ee RA ee RA RA GR Re ee GR E Se Re ee ee ON EE ein EA N OR ER RE EO Check 11 Annunciator section of PFD e esse sesse se se ee Ge ee Re GR Ge RR e Check 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH
11. as it may result in serious personal injury Never try to start the engine by hand STARTING ENGINE DA 40 only a Cold engine 1 2 3 Strobe light ACL ccs RS EER Se Ee dence ER Ee costed Ag Rg N Ee Pe ge Ee ON Electrical fuel PUMP ee se ee Ge ee ee ee Ge Re Gee Re GR ee ee ON note pump noise functional check of pump Throftle ES Re GE RS Ee ee eg oe 3 cm 1 2 in forward from IDLE measured from rear of slot Mixture control lever ees see ee ee ee ee ee ee ee RICH for 3 5 sec then LEAN Throttle 1 cm 0 4 in forward from ees ese ee ee ee RA Ge Re Re Ge Re ee ee IDLE measured from rear of slot WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts CAUTION The use of an external pre heater and external power source is recommended whenever possible in particular at ambient temperatures below 0 C 32 F to reduce wear and abuse to the engine and electrical system Pre heat will thaw the oil trapped in the oil cooler which can be congealed in extremely cold temperatures After a warm up period of approximately 2 to 5 minutes depending on the ambient tempe
12. 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 control buttons and knob e PFD softkey buttons including master warning caution acknowledgement e Altitude reference set knob e Heading bug control e Navigation frequency transfer button e Navigation frequency set knobs e Navigation frequency volume and Identifier knob The PFD displays the crew alerting annunciator system When a warning or caution message is received a warning or caution annunciator will flash on the PFD accompanied by an aural tone A warning is accompanied by a repeating tone and a caution is accompanied by a single tone Acknowledging the alert will cancel the tone and flashing and provide a text description of the message Refer to the Emergency or Abnormal Procedures Sections of the AFM or this Supplement for the appropriate procedure to follow for each message 190 00492 12 Rev 6 Diamond DA 40 DA 40F 7 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MO
13. the KAP 140 autopilot 190 00492 12 Rev 6 Diamond DA 40 DA 40F 7 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 7 10 FUEL SYSTEM Fuel Quantity Indication Each fuel tank has a capacity probe that ascertains fuel quantity in that tank Standard Tank configurations have two fuel probes one in each wing Long Range Tank configurations have four fuel probes two in each wing an outboard tank and an inboard tank When the fuel quantity indicator reads zero only unusable fuel remains in the tank Usable capacity of each tank for the Standard Tank configuration is 20 US gal 76 liters Usable capacity of an outboard and inboard 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 o
14. the left tank is less than 3 EE US gal 1 US gal Fuel guantity in the right tank is less than 3 Seo US gal 1 US gal LOW VOLTS On board voltage below 24 volts PED FAN FAIL PFD Cooling Fan has failed See Abnormal Procedures section 4B MED FAN FAIL MFD Cooling Fan has failed See Abnormal Procedures section 4B GIA FAN FAIL GIA Cooling Fan has failed See Abnormal Procedures section 4B PFD is approaching its operating PFD OVERHEAT temperature limit Display brightness is automatically reduced to 50 of maximum See Abnormal Procedures section 4B MED is approaching its operating MED OVERHEAT temperature limit Display brightness is automatically reduced to 50 of maximum See Abnormal Procedures section 4B GIA1 OVERHEAT GIA2 OVERHEAT GIA 1 is approaching its operating temperature limit See Abnormal Procedures section 4B of the AFMS GIA 2 is approaching its operating temperature limit See Abnormal Procedures section 4B of this AFMS 190 00492 12 Rev 6 FAA Approved Diamond DA 40 DA 40F 2 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 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 Aud
15. until the RPM exceeds 2780 Note 3 Fuel Pressure Gauge is optional for DA 40 aircraft 2 6 WARNING CAUTION AND STATUS MESSAGES The following tables show the color and significance of the warning caution and advisory messages which may appear on the G1000 displays NOTE The G1000 Cockpit Reference Guide and the G1000 Pilot s Guide contain detailed descriptions of the annunciator system and all warnings cautions and advisories Warning annunciations Red Annunciation Cause OIL PRES LO Oil pressure is less than 25 psi FUEL PRES LO DA40 Only Fuel pressure is less than 14 psi FUEL PRES HI DA40 Only Fuel pressure is greater than 35 psi ALTERNATOR Alternator failure Operation of the starter without the key in the start position or failure of the starter STARTER ENGD 2 motor to disengage from the engine after starting Front canopy and or rear door not DOE OEEN completely closed and locked TRIM FAIL The KAP 140 autopilot pitch trim system has failed 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT Caution annunciations Yellow Annunciation Cause PITOT OFF Pitot heat is not switched on PITOT FAIL Fault in the pitot heating system Fuel quantity in
16. 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 190 00492 12 Rev 6 Diamond DA 40 DA 40F 1 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT downloaded from Garmin G1000 website on the Internet For information on using the WFDE Prediction Program refer to Garmin WAAS FDE Prediction Program part number 190 00643 01 WFDE Prediction Program Instructions North Atlantic NAT Minimum Navigational Performance Specifications MNPS Airspace per AC 91 49 and AC 120 33 Both GPS SBAS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational approval NOTE Each GIA 63W computes an independent navigation solution based on its GPS sensor The G1000 will use the GPS sensor with the highest signal quality and will automatically revert to the other sensor if the active sensor fails or if the secondary sensor is determined to be more accu
17. 1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT LOG OF REVISIONS Revision Page Number Number s Description Approved Approval de Mu 228200 Murray Murray Update SW levels for Bober 3 All non WAAS OPC 4 18 2008 f Murray configuration Murray Revised by Garmin ODA Correct minor typographical errors and 5 All administrative 9 21 2010 9 21 2010 corrections to fuel quantity indication range markings Incorporate revisions for All system software level Seg A AE pe 0321 23 190 00492 12 Rev 6 Diamond DA 40 DA 40F iii This page is intentionally blank 190 00492 12 Rev 6 Diamond DA 40 DA 40F iv FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT Table of Contents SECTION 1 GENERAL sesse see sesse see se ese see se se Se ese See Be Ee Ee Be Ee Ee Be Ee Ee Be Ge Ee Se ee 1 1 SECTION 2 LIMITATIONS sesse see sesse see se ese se ese Ee Be Ee Ee Be Ee EE Be Ee EE Be Ee Ee Se ee 2 1 SECTION 3 EMERGENCY PROCEDURES eesee sesse sesse see se ese see se ese see se sees 3 1 SECTION 4A NORMAL PROCEDURES ee sesse see see sesse see se ese see se ese see se ese 4A1 SECTION 4B ABNORMAL PROCEDURES sesesesesesesesesesesesesesesesesesesee 4B 1 SECTION 5 PERFORMANCE esesesesesesesesesesesesesesesesesesesesesesesesese
18. DEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT Advisory messages related to G1000 system status are shown in white and are accompanied by a white flashing ADVISORY alert Refer to the G1000 Pilot s Guide and Cockpit Reference Guide for descriptions of the messages and recommended actions if applicable Trend vectors are shown on the airspeed and altimeter displays as a magenta line predicting 6 seconds at the current rate The turn rate indicator also functions as a trend indicator on the compass scale The PFD can be displayed in a composite format for emergency use by releasing the red DISPLAY BACKUP button at the bottom of the audio panel Manual display backup mode is engaged when the button on the audio panel is OUT In the composite mode the full crew alerting function remains The Multi Function Display MFD typically displays engine data maps terrain traffic and topography displays and flight planning and progress information The display unit is identical to the PFD and contains the same controls as previously listed The audio panel contains traditional transmitter and receiver selectors as well as an integral intercom and marker beacon system The marker beacon lights appear on the PFD to the left of the top end of the altitude tape In addition a clearance recorder records the last 2 minutes of received audio Lights above the selections indicate what selections are active Releasing the red DISPLAY
19. E This removes power from the main and avionics busses and disables alternator operation See the table at the end of this section for the equipment which is still available If smoke or fumes decrease 9 Land at the nearest suitable airport as soon as possible If smoke or fumes persist 10 ALT alternator SWitCh oceneni eri AR Re ee GR Re ee ee Ge Re ee ee ON Ts ESS BUS SWiteh ER EE OR OER EE amass OFF 12 BATT and ESS TIE circuit breakers esse ee ee ee ee ee ee ee ee ee ee ee 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 eguipment which will still be available 190 00492 12 Rev 6 Diamond DA 40 DA 40F 3 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 13 Use standby instruments for attitude airspeed and altitude 14 Refer to Section 3 7 2 b of this Supplement Alternator Failure 15 Land at the nearest suitable airport as soon as possible The equipment available on Essential Bus only operating on battery only and the Essential Bus switch selected is Air Data Computer airspeed altitude vertical speed OAT TAS Attitude and Heading Reference System attitude heading PFD in composite mode Pitot Heat Flaps Com 1 GPS NAV 1 Transponder Landing light Instrument flood lights
20. EMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT TRAFFIC AVOIDANCE SYSTEM LIMITATIONS Use of the MAP TRAFFIC MAP to maneuver the airplane for traffic avoidance without outside visual reference is prohibited The Traffic Information System TIS is intended as an aid for the pilot to visually locate traffic It is the responsibility of the pilot to see and manually maneuver the airplane to avoid other traffic SYNTHETIC VISION LIMITATIONS Use of the Synthetic Vision system display elements alone for aircraft control without reference to the G1000 primary flight instruments or the aircraft standby instruments is prohibited Use of the Synthetic Vision system alone for navigation or obstacle or terrain avoidance is prohibited Use of the SVS traffic display alone to avoid other aircraft is prohibited DATA LINK WEATHER XM AND GFDS WEATHER LIMITATIONS Datalink weather information displayed by the G1000 system is limited to supplemental use only XM and GFDS weather data is not a source of official weather information Use of the NEXRAD and LTNG Lightning data on the MAP NAVIGATION MAP and or MAP WEATHER DATA LINK XM or GFDS page for hazardous weather e g thunderstorm penetration is prohibited NEXRAD and LTNG information on the MAP NAVIGATION or MAP WEATHER DATA LINK XM or GFDS page is intended only as an aid to enhance situational awarene
21. 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 12 Rev 6 Diamond DA 40 DA 40F 3 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 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 ete ie AA tetanic EE ON 3 Cabin heat cri RE EE IN ON 4 Air distribution lever cccccccccssccssccssecscesscesscesscesecsecesecssecssecseecseeeseeeeees A UP Se RPM ER AN EE EE tages increase in order to prevent ice build up on the propeller blades 6 Alternate Air DA 40 only ee RR RA GR Re ee ee ee Re ER EA OPEN 6a Carburetor Heat DA 40 F only ese see ee ee ee ee ae Re Re Gee Ee ee ee ee ee HOT 7 Emergency WindOWI S esse sees se ee ee ee Re GR Re RR GR Re RA GRA Gee ee open if reguired CAUTION Ice build up increases the stalling speed If required for safety reasons
22. Garmin Ltd Or its subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA Document No 190 00492 12 FAA APPROVED FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT Reg No S N This Supplement must be attached to the FAA Approved Airplane Flight Manual when the Garmin G1000 Integrated Avionics System is installed in accordance with STC SA01444WI D The information contained herein supplements the information of the basic Airplane Flight Manual For Limitations Procedures and Performance information not contained in this Supplement consult the basic Airplane Flight Manual Note This Airplane Flight Manual Supplement follows the format and content of the Airplane Flight Manual for the Diamond DA 40 for consistency and ease of use Note This Airplane Flight Manual Supplement supersedes all previously approved G1000 Airplane Flight Manual Supplements for DA 40 and DA 40 F including those required by STC SA01254WI D ODA STC Unit Administrator Garmin International ODA 240087 CE Date Ef AT 2 190 00492 12 Rev 6 Diamond DA 40 DA 40F i This page is intentionally blank 190 00492 12 Rev 6 Diamond DA 40 DA 40F ii Garmin Ltd Or its subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G
23. HONEYWELL KAP 140 AUTOPILOT BEFORE TAXIING 1 Avionics master switchi se sesse se se ee Ge ee Ge ee GR ee AA Ge RR Ge Re GR ee Gee ON 2 Electrical quipment sss is EER r eg ee EDGAR GP oge geheg see gee IR On as reguired GEE EE EE EE AE ER Ee UP T O LDG T O indicator and visual check 4 Flight instruments and avionics ee ee ee ee set test function as reguired set both altimeters S Flood licht ii ie ES DE LEEG EER ek ON test function as reguired io EE EE check if required increase RPM To Fuel tank sel etoOr se Ee EE ek ee Se ee Re N ee gee ge ee Ee change tanks confirm that engine also runs on other tank at least 1 minute at 1500 RPM 8 Pitot beatin Tani deka cise sete N Re A ade RE alent ON test function no yellow PITOT FAIL annunciation 9 Pitot heatingssesosc AE EE N OFF if not required yellow PITOT OFF annunciation 10 Strobe lights ACLs check ON test function as reguired 11 Position lights landing and taxi lights 0 0 ON test function as required 12 CAUTION When taxiing at close range to other aircraft or during night flight in clouds fog or haze the strobe lights should be switched OFF The position lights must always be switched ON during night flight Ide RPM EE OR RE EEN check 600 to 800 RPM 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL
24. PPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT STARTING ENGINE DA 40 F only a Cold engine 1 2 3 MR Strobedlisht ACD sees Ee Ee ist ge eink desea ees GE ge ee ON EP GEE EE RE REEN fully RICH Electrical fuel PUMP eee see Ge ee ee ee Ge Re Gee Re GR ee ee ON note pump noise functional check of pump Throttle ie SEERDE GE ES KEES Ee Ee ee GEGEE EE E aeaa Bes travel forward from IDLE Prime acs EE ER RS eo e ER Ge a he does 1 4 seconds electric pump WARNING Use the primer system to prepare the engine for a starting attempt Do not use the throttle to pump fuel through the carburetor to the engine for priming since this may lead to carburetor fire The primer system delivers fuel to the cylinders directly CAUTION The priming system is not intended for operation in flight WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool for 30 minutes before further start attempts CAUTION The use of an external pre heater and external power source is recommended whenever possible in particular at ambien
25. R EE fully RICH 3 Electrical fuel pump sesse se se ek i Ge ee Ge Re ek ee ee ON note pump noise functional check of pump Ad Thbrottle iss ebubsEse KERE e OER EE Rook SEER EE Ek eg Eb sek Sie 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 Di EE EE ORE EA EEN engage When engine starts 6 Oil RR ene EE EE a green arc within 15 sec Ta N ie GEE EE RE OE EE EE EE Ss set 1000 RPM 8 Electrical fuel purtip ies Re ie RE GEN EE Geek ES eke KEN ED ese ge e OFF WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF THE ENGINE and investigate problem 9 ALT alternator SWitCh enuresis EEA K EE i ON 10 ATMImeter n EE EE EE GE Ee EE Ge EE De Ee Ge P ene EE EISE eg KSSE Check 11 Annunciator section of PFD i iese se se ee ee ee ee ee ee ee ee ee ee ee ee ee ee ee Check 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT c Engine will not start
26. RE AE tes 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 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 12 Rev 6 Diamond DA 40 DA 40F 3 9 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 3 8 5 ERRONEOUS OR LOSS OF WARNING CAUTION ANNUNCIATORS NOTE Loss of an annunciator may be indicated when engine or f
27. RE IN FLIGHT b Electrical fire with smoke in flight 1 Emergency SWItCH si Bree aane Eseg Gegee ge ke Ge eb esse Sheen 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 esse es sees ee se ee ee Ge Re ee Ge Re ee Ge Re ee ee Ge Re ee ee OFF 3 Cabin heat ass EE Ee EE EE E E ee de bao OFF 4 Emergency WindoWI S siese ese ese see se ee ge ee Ge Re Gee Re GR Re GR Ge Re Ge ee eke ee OPEN 5 Use standby instruments for airspeed altitude and attitude reference if necessary 6 Land at the nearest suitable airport as soon as possible If electronic or avionics equipment is required for continued flight the following procedure may be used to isolate the source of the smoke or fumes Te BAT battery SWAER se sos do ge Gegee Ee detec SR Ee oo ee ed ee Ge Go ge Ee de Rek ON 8 ESS BUS SWItED EE Ee ESE Ge Ge Ge bee Ee ee A Geek EE Ee Ee ee eek ee ON NOT
28. SE button shall be OUT NOTE After automatic entry of reversionary mode it is required to release the DISPLAY BACKUP button on the audio panel button OUT With the DISPLAY BACKUP button OUT if the problem causing the automatic entry of reversionary mode is resolved the system will remain in reversionary mode A maximum of one attempt to return to normal mode may be made using the following procedure b DISPLAY BACKUP button on audio panel PUSH button shall be IN e If the system returns to normal mode leave the DISPLAY BACKUP button in and continue e If the system remains in reversionary mode or abnormal display behavior such as display flashing occurs then return the DISPLAY BACKUP button to the OUT position 190 00492 12 Rev 6 Diamond DA 40 DA 40F 3 8 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 3 8 2 AHRS FAILURE NOTE A failure of the Attitude and Heading Reference System AHRS is indicated by removal of the sky ground presentation and a red X and a yellow AHRS FAILURE shown on the PFD The digital heading presentation will be replaced with a yellow HDG and the compass rose digits will be removed The course pointer will indicate straight up and course may be set using the digital window 1 Use Standby Attitude Indicator magnetic compass and Navigation Map SARA RE RE A
29. a Loss Of Integrity LOI will be annunciated on the HSI and the approach mode will be aborted Only applicable to GIA 63W equipped aircraft When operating under instrument flight rules requiring an alternate airport the required alternate airport must not be flight planned based on an RNAV GPS LP LPV or LNAV VNAV approach The alternate airport must be flight planned using an LNAV approach or available ground based approach aid Only applicable to GIA 63 non WAAS equipped aircraft The aircraft must have operational approved navigation equipment other than GPS appropriate to the operation Only applicable to GIA 63 non WAAS equipped aircraft When operating under instrument flight rules requiring an alternate airport the required alternate airport must have an approved instrument approach procedure other than GPS that is anticipated to be operational and available at the estimated time of arrival and which the aircraft is equipped to fly 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 7 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 8 Use of the Ga
30. and Heading Reference System AHRS Air Data Computer Pitot heat Engine instruments Transponder Flood light Landing light Refer to the ESSENTIAL BUS area of the circuit breaker panel for a quick reference to equipment on those busses These items of equipment can be supplied with power by the battery for at least 30 minutes During this 30 minute period the airplane must be landed at a suitable airport Economical use of electrical equipment in particular of pitot heat and switching off equipment that is not needed extends the time during which the other equipment remains available 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 190 00492 12 Rev 6 Diamond DA 40 DA 40F 3 7 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 3 8 AVIONICS EMERGENCIES 3 8 1 PFD OR MFD DISPLAY FAILURE a DISPLAY BACKUP button on audio panel RELEASE 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 RELEA
31. automatically reduced to 50 of maximum 1 Cross check PFD attitude heading altimeter and airspeed with standby instruments If PFD primary flight instruments do not agree with standby flight instruments or the PFD fails or is unusable select Display Reversionary Mode using the red DISPLAY BACKUP button on the audio panel Pull the PFD circuit breaker If the PFD fails or the PFD circuit breaker is pulled the autopilot will operate normally b MFD OVERHEAT caution NOTE The MFD is approaching its operating temperature limit Display brightness is automatically reduced to 50 of maximum 1 Select Display Reversionary Mode using the red DISPLAY BACKUP button on the audio panel Cross check MFD engine instruments and primary flight instruments with the PFD If the MFD does not agree with the PFD or the MFD fails or is unusable pull the MFD circuit breaker If the MFD fails or the MFD circuit breaker is pulled the autopilot vertical modes will operate normally Autopilot lateral modes will be limited to ROL mode only 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4B 3 c d wm FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT PFD OVERHEAT caution AND MED OVERHEAT caution NOTE The PFD and MFD are both approaching operating temperature limits The brightness of both displays is au
32. controls sesse se se ee ee Freedom of movement and proper direction 11 Trim wheels ius EE SEGE GATE ERK Ed ai Ee Ge Ge ee VERG GR ER GE Re one De Gegee bee ie ds T O 12 Friction device throttle guadrant ees ese see ee ee ee ee Ge Re ER EA Adjusted 13 iis OE EE OR EE N EER IDLE 14 Mixture control levers iss ese ee N EER Gee Se eks Es bee RGN GE OE Geb Se ee Vd LEAN 15 RPM lever DA 40 only iese sees see Ge se mennina HIGH RPM 16 Carburetor heat DA 40 F only sesse ee se ee ee GR ee GR Re ee Re ee COLD 17 Alternate air DA 40 only ee ee ER RR RA RA Re Re ee ee ee ee CLOSED 18 Alternate Static Valve ee ee ee ee ee ee Re ee ee ee ee ee ee ee ee CLOSED if installed 19 Avionics master SWitCh ie iese see see ee ee ee ee ee ee Re Re ee Re RR RA GRA Ge ee OFF 20 Essential Bus switch ees ee ee ee ee Ge Re GR Re RR GR Re GRA GRA GR ee Re Ee ee ee ee ee OFF 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 2 21 22 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT CAUTION When the essential bus is switched ON the battery will not be charged unless the essential tie relay bypass OAM 40 126 is installed BAT battery Switch ii ee Ese DE Re EG EE Ee se Dee ee Ge ee N ON AE tank dil eie N ei E N RG on fullest tank WARNING Never move the propeller by hand while the ignition is switched on
33. d data LOI GPS integrity is insufficient for the current phase of flight 190 00492 12 Rev 6 Diamond DA 40 DA 40F 3 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 3 2 3 ENGINE PROBLEMS IN FLIGHT h High Fuel Flow DA 40 only Fuel flow in red sector 1 Fuel pressure iese esse esse ee ee ee ee 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 g High Fuel Flow DA 40 F only T Fuel Quantity SR ine iene N Ee eee Check and Monitor 2 POWer Setting se EE eee ee 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 190 00492 12 Rev 6 Diamond DA 40 DA 40F 3 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 3 3 3 SMOKE AND FI
34. d engine Warm engine T Strobe lisht ACE ees SERE E VER ees ene N Ge Gee Ri ON 2 Electrical fuel PUMP iese sesse ese see se eke RA Ge Ge Re ek ee ee ON note pump noise Functional check of pump 3 Mixture contfol lEVer is iss Anti es ee ee SE sege Se OE ee ede Ee LEAN fully aft do OT ed EE EE RE EE EEN aes 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 5S Ignition swith ER EE EE EE EO ain ieee START 6 Throttle ssc os ERGER caes pull back towards IDLE when engine starts When engine starts 7 Mixture control lever miiir enen a e ee rapidly move to RICH 82 ok vi ARE EE ER EE RE eed green arc within 15 sec WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 9 ALT alternator switch i s sier Ee SG ei eee Rea ON 10 AMMeCtER EE EE EE TE RE pi Check 11 Fuel Pressure esis ic se RE EE ee Ee Ee Check no messages illuminated 12 Annunciator section of PFD e iese sesse se see Ge ee ke GR Ge AR Ge Re GR Re ee Check 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 5 FAA A
35. d will cause a higher RPM than tailwind AB SR dete sateen EE EE Botley set 1000 RPM Carburetor Heat DA 40 F only esse ees ees se ee ee ee se ee ee ge se de ee check COLD Alternate Air DA 40 only ee ee ee ee ee ee ee ee check CLOSED Flight AE ARE HE EE EE N entered Altimeter settings AE EE EE EA EN checked set G1000 and standby altimeter G1000 and autopilot altitude preselectors cee see se ee ee Ge Re ee ee set RAd10S eers RE RE ses E Ee helo sp se aden set and checked Transponder is ESE EG EE ek SE Ee Ge AE Oe Re GER ee EE Ee RSG ee ie code set Standby attitude gyro i e esse see se ee Ge ee GR ee GRA Ge ee Ge ee eke ee erect and no flag Parking brake RE OE EE N EG release Landing lights tee EERS RE AE ER SERE GER Gee REGEER Rg ER ESE Ee GEE ON as reguired Missed Approach See KAP 140 flight manual supplement for additional information a 3 AAP DISC Bitton oieee ses sc Reese ESE EER Pe ee PRESS to disengage AP b MISSED APPROACH esse ses se ese ees se ee se ese ee ee ee ee EXECUTE c AP Button After airplane is in trim and climb established PRESS for autopilot operation if desired d G1000 HDG bug oseese Set to missed approach heading e Autopilot HDG button ee see se se ee Re Re Ge Re GR ee ee PRESS f G1000 Missed Approach iese ese sesse see se Ge ee Gee ee ACTIVATED g Autopilot NAV Dutton ee sesse ee se ee GR ee GR Ge Re Ge Re ek ee ee PRESS After missed approach
36. e 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 12 Rev 6 Diamond DA 40 DA 40F 3 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 9 In an in flight emergency depressing and holding the COM transfer button for 2 seconds will tune the emergency frequency of 121 500 MHz If the display is available it will also show it in the Active frequency window 10 If the white TAWS N A status annunciator is displayed on the PFD or MFD TAWS page the system will no longer provide TAWS alerting or display relative terrain elevations The crew must maintain compliance with procedures that ensu
37. e ese se se ee ee ee ee 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 5 Tenton switch ss REDE anki EG R GEE Ee Se START When engine starts 6 Mixture control lever iese se ee ea ee Re Re ee Ee Ee rapidly move to RICH Te Oil pressure esse ERGE Ee ei SAG ee ER GER Ge Ee A seek edge 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 Ee aiid on EER EE EER Be cn E ee E ee Ge ee Ese ee OFF 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 9 ALT alternator Switch coscceccccsvccesescsesec oesasendsesacdvesteessa EE a R ON 10 AMMeCteD sis EE FEE Check 11 Fuel pressures EE EES Ee EO ieee ee Ede Check no messages illuminated 12 Annunciator section of PFD iese sesse se se ee Ge ee eke GR Ge RR Ge Re GR Re ee Check c Engine will not start after injection floode
38. en approved as a Hardware Class 3 Software Type B Electronic Flight Bag EFB in accordance with AC 120 76B when using current FliteChart or ChartView data Additional operational approvals may be required For operations under part 91 it is suggested that a secondary or back up source of aeronautical information necessary for the flight be available to the pilot in the aircraft The secondary or backup information may be either traditional paper based material or displayed electronically If the source of aeronautical information is in electronic format operators must determine non interference with the G1000 system and existing aircraft systems for all flight phases 190 00492 12 Rev 6 Diamond DA 40 DA 40F 1 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT SECTION 2 LIMITATIONS 2 1 INTRODUCTION GENERAL LIMITATIONS 1 The Garmin G1000 Cockpit Reference Guide CRG must be immediately available to the flight crew The required CRG is referenced to the System Software Version number The System Software Version number is displayed at the top right side of the MFD Power up page System Software Garmin G1000 Cockpit Reference Guide CRG Version revision P N 190 00324 11 Revision B or later appropriate revision 0321 23 2 AHRS Areas of operation Flight operations with the G1000 Integrated Avio
39. f the fuel tanks usable fuel When a fuel tank is completely full the quantity pointer will indicate 24 US gallons As fuel is consumed from the tank the pointer will move to the left Once there is no more measurable fuel in the outboard tank the pointer migrates over a 30 second period to the 16 US gal position The pointer will remain at 16 US gallons while the un gauged fuel quantity is consumed Once the quantity of fuel remaining in the inboard tank is less than 16 gallons the pointer will begin moving left towards zero When either pointer enters the amber portion of the scale the pointer and the gauge title FUEL QTY GAL will turn amber When either pointer enters the red portion of the gauge the pointer will turn red and the gauge title FUEL QTY GAL will turn red and flash continuously in inverse video When the fuel quantity in either tank falls below approximately 3 gallons a message L FUEL LOW or R FUEL LOW will be presented on the PFD along with an alert tone When the fuel quantity in the tanks is low fuel movement during taxiing turns may cause the low fuel warnings to be presented 190 00492 12 Rev 6 Diamond DA 40 DA 40F 7 4 Part Information GPN 190 00492 12 Description AFMS G1000 Integ Avionics Sys Diamond DA40 40F KAP 140 Part Type Manuals Printed Literature Lifecycle Phase Experimental Rev 6 ECO 099458 ltem Attribution Document Review Required
40. io panel 1 1 1 1 Air data computer 1 1 1 1 Attitude and Heading Reference 1 0 1 1 System Static dischargers 7 0 0 7 GPS 2 0 1 2 PFD Cooling Fan 1 0 1 1 MED Cooling Fan 1 0 1 1 GIA Cooling Fan 1 0 1 1 2 14 FUEL Fuel Quantity Total fuel quantity Standard Tanks 2 x 20 6 US gal approx 156 liters Long Range Tanks 2 x 25 5 US gal approx 193 liters Unusable fuel 2x 0 5 US gal approx 3 8 liters Max Indicated Fuel Quantity Standard Tanks 17 US gal per tank Long Range Tanks 24 0 US gal per tank Max permissible difference between right and left tank Standard Tanks 10 US gal approx 38 liters Long Range Tanks 8 US gal approx 30 3 liters 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 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 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 11 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F
41. 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 12 Rev 6 Diamond DA 40 DA 40F 1 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT Operational Approvals G1000 GPS NAVIGATION SYSTEM GIA 63 INSTALLED GIA 63 units are standard and provide position information in accordance with
42. nics installed are prohibited in the following areas due to unsuitability of the magnetic fields near the Earth s poles a b c d e North of 72 North latitude at all longitudes South of 70 South latitude at all longitudes North of 65 North latitude between longitude 75 W and 120 W Northern Canada North of 70 North latitude between longitude 70 W and 128 W Northern Canada North of 70 North latitude between longitude 85 E and 114 E Northern Russia South of 55 South latitude between longitude 120 E and 165 E Region south of Australia and New Zealand NOTE The Garmin G1000 system is not designed for use as a polar navigator and operation outside the approved operating area is prohibited The GRS 77 AHRS internally monitors the magnetic field and will display a GEO LIMITS system message when the magnetic field becomes unsuitable for AHRS operation When the AHRS can no longer reliably compute heading heading information will be removed form the HSI 3 The fuel quantity fuel required and fuel remaining functions of the FMS are supplemental information only and must be verified by the flight crew 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT The ADF aural identifier must be monitored any time the ADF is used as the primary sou
43. ocuments se ee ee ee Re RR RR RA RA Re complete and up to date c Apgnition OO ME OE ER RE ET pulled out d Front canopy amp rear doof oe ee ee se ee ee Ge GR Gee ee ee clean undamaged e Allelectrical equipment ut se EE n GR ee ie ee a pres OFF f Circuit breakers iese see ee ee set in if one has been pulled check reason g Engine control levers ese sesse ee check condition freedom of movement Full travel of throttle Full Travel of RPM DA 40 only Full Travel of mixture lever M Mee lo RE EE ae OE HR EE REEN IDLE 1 Maxture control levers ss EE EE ek ges RE ee eek Re ee GE Ee gee ee LEAN jJ RPM lever DA 40 only oo iese see se ek ee Se Ge Ge Re GR ee ek ee ee HIGH RPM k Carburetor Heat DA 40 F only esse sesse es ses ee ee ee ee ee ee ee ee ee ee COLD D BAT battery SWItR sees cock SS ee tots a seis cose Gee BR Ee sfere ON Mm Fuel Quantity Ui oc GE EER PG GEE Re N EED bos athe Ge Ee eg EE check fuel gty on EIS check with fuel qty measuring device 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 1 n o p q r FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 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 f
44. ond DA 40 DA 40F 5 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT SECTION 6 WEIGHT AND BALANCE See current weight and balance data 190 00492 12 Rev 6 Diamond DA 40 DA 40F 6 1 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT SECTION 7 SYSTEM DESCRIPTIONS G1000 SYSTEM The Garmin G1000 Integrated Avionics System consists of a Primary Flight Display PFD a Multi Function Display MFD an Audio Panel and Attitude and Heading Reference System AHRS an Air Data Computer ADC and the sensors and computers to process flight and engine information for display to the pilot The system contains dual GPS receivers dual VOR ILS receivers dual VHF communications transceivers a transponder and an integrated annunciation system to alert the pilot of certain abnormal conditions Optional equipment includes an Automatic Direction Finder ADF receiver and Distance Measuring Equipment DME 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
45. or flight planning is 17 US gal FOR LONG RANGE TANKS when the fuel indicator reads 16 US gal the correct fuel quantity must be determined with the fuel quantity measuring device There are 3 US gal of un gauged fuel from 16 to 19 US gal If this measurement is not carried out the fuel quantity available for flight planning is 16 US gal Position lights strobe light ACL S ese se sesse se Ge ee Ge ee GR ee GRA Se ee ee check BAT battery witeite ie ek EER GE ien ee ee ke Re Ee Ge Ee ee Ge Ee OFF Check for loose tems ES ges AS GE GEES ogi ain aie complete Flight controls and HIM ees ee ee se ee Re RR RA RA Re free to move and correct Baggage Vis Ee KIN Heb ese eaa e tnsveans dv schaviivous aE asii stowed and secure NOTE Refer to DA 40 and DA 40 F AFMs to complete the Walk Around check visual inspection BEFORE STARTING ENGINE 1 Preflight inspection sn Be RE EE Se RE Ee a ee De Ge canis Complete 2 Ridder pedale EER Ee Ee N See EG Ee Ee ee ed Ee Adjusted and locked Bix PaSSCMSOrss ii EE EE SE DR gene GE Ge DS EES ee ee Ge ee Instructed 4 Safety Harnesses 0 0 see se ee se a ea Ge Re Ge ee ee All on and fastened 5 Reat door EE EE EE OO nies Closed and locked 6 Door lock if installed ccc eee ee ee ee RR ee Unblocked key removed Te ES AO EE eee Position or 2 cooling gap 8 Canopy lock if installed 0 eect se ek Ge ee Re ee Unblocked key removed EE id side ED OE RE OE EE EG Set 10 Flight
46. other sensor if the active sensor fails or if the secondary sensor is determined to be more accurate An AHRS 1 GPS message means that one of the GPS receivers has failed Refer to the MFD AUX GPS STATUS page to determine the state of the GPS receivers Enroute and Terminal including RNP5 BRNAV and PRNAV RNP 1 In accordance with JAA TGL 10 Rev 1 ACJ 20X4 AC 90 96A and AC 90 100A provided the FMS is receiving usable navigation information from one or more GPS SBAS receivers The G1000 Integrated Avionics system as installed in this aircraft is eligible for B RNAV in accordance with AMJ20X2 190 00492 12 Rev 6 Diamond DA 40 DA 40F 1 2 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 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 e 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
47. ourse deviation signals to the KAP 140 autopilot When course deviation signals are available from the G1000 the KAP 140 may be coupled to those signals as described in the autopilot documentation When navigation changes on the G1000 cause the KAP 140 autopilot to automatically revert to ROL mode the G1000 system will provide a message to alert the pilot to verify that the autopilot mode is as desired The G1000 system controls and displays affecting KAP 140 autopilot operation are PFD mounted CDI selector button PFD MFD mounted heading select knob HDG PFD MFD mounted course select knob CRS Course Deviation Indicator CDI and flag Vertical Deviation Indicator GS VPTH and flag No altitude information or altitude preselect settings are exchanged between the autopilot and the G1000 system Altitude and barometric setting entries must be made separately on the G1000 and KAP 140 autopilot systems as appropriate When passing the missed approach point MAP on an instrument approach the aircraft should either be hand flown or the autopilot operated in HDG mode until the appropriate missed approach path and climb has been established Before re engaging the autopilot the pilot must carefully assure that the autopilot programming will result in a turn in the correct direction and the required climb Refer to the appropriate KAP 140 autopilot Airplane Flight Manual or Airplane Flight Manual Supplement for information and procedures for
48. path has been verified NOTE If engaged the autopilot must be operated in HDG mode until the pilot has verified that the autopilot programming will result in the required climb and tracking of the missed approach path If tracking the ILS course outbound as part 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 11 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT of the missed approach procedure is desired use the autopilot NAV mode to prevent inadvertent GS coupling 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 De
49. rate An AHRS 1 GPS message displayed in the ALERTS window means that one of the GPS receivers has failed Refer to the MFD AUX GPS STATUS page to determine the state of the GPS receivers e Enroute and Terminal including RNP5 BRNAV and PRNAV RNP 1 In accordance with JAA TGL 10 Rev 1 ACJ 20X4 AC 90 96A and AC 90 100A provided the FMS is receiving usable navigation information from one or more GPS SBAS receivers The G1000 Integrated Avionics system as installed in this aircraft is eligible for B RNAV in accordance with AMJ20X2 e 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 12 Rev 6 Diamond DA 40 DA 40F 1 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT ELECTRONIC FLIGHT BAG The G1000 Integrated Avionics System as installed in this aircraft has be
50. rature at 1500 RPM the engine is ready for takeoff if it accelerates smoothly and the oil pressure is normal and steady Ignition Switch seision e ER Ke Gee ERK Ge ge Geb Re ie ee EE Ee EE due START 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT When engine starts 7 Mixture control lever esse ese ee ee ee Ge Re ee ee rapidly move to RICH 8 Oil SR OE ER EE at green arc within 15 sec 9 Electrical foel Pupici RE RE EE EER GE Er EEUE OFF WARNING If the oil pressure has not moved into the green arc within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 10 ALT alternator switch ees see es se Ge AR Re ee RA ee GR ee ee ER Re ee ee Ee Re ee Ge ee ee ON 11 Ammeter is Ee EER EE EG ek GR BE GR EG Ge De ke Ee REGEER Ee Es GR ee N se al Check 12 FUE pressure iiss es ee ek sege Ese See See ese muha Check no messages illuminated 13 Annunciator section of PFD i ie ee see ee ee ee ee Ge Re GR Re GR Re RR RA Re ee Check b Warm engine 1 Strobe light ACL Ai acs EES Ee e a GE ES Ee ae ON 2 Electrical fuel pump ssi stain KERE n ier ae oe ke be ON note pump noise functional check of pump Be Ehrottle i rs EE ESE EE EER GEE Do Ee egg 3 cm 1 2 in forward from IDLE measured from rear of slot 4 Mixture control lever sess
51. rce of navigation Do not use SafeTaxi or Chartview functions as the basis for ground maneuvering SafeTaxi and Chartview functions do not comply with the requirements of AC 20 159 and are not qualified to be used as an airport moving map display AMMD SafeTaxi and Chartview are to be used by the flight crew to orient themselves on the airport surface to improve situational awareness during ground operations Do not move the aircraft until the AHRS has aligned and displays valid attitude information on the PFD after the G1000 system has been turned on G1000 GPS NAVIGATION SYSTEM LIMITATIONS 1 GPS SBAS based IFR enroute oceanic and terminal navigation is prohibited unless the pilot verifies and uses a valid compatible and current Aviation database or verifies each waypoint for accuracy by reference to current approved data GPS or GPS and RNAV GPS instrument approaches using the G1000 System are prohibited unless the pilot verifies and uses the current Aviation database GPS based instrument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the Aviation database Instrument approaches utilizing the GPS receiver must be conducted in the approach mode LNAV LNAV V L VNAV or LPV and GPS W AAS integrity monitoring must be available at the Final Approach Fix If there is not sufficient GPS WAAS integrity at any time after crossing the Final Approach Fix
52. re 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 display field such as COM frequencies NAV frequencies or engine data indicates that display field is not receiving vali
53. rmin 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 NOTE Not all published approaches are in the AVIATION database The flight crew must ensure that the planned approach is in the database 9 Use of the G1000 VOR ILS receiver to fly approaches not approved for GPS requires VOR ILS navigation data to be present on the display 10 When conducting missed approach procedures autopilot coupled operation is prohibited until the pilot has established a course and rate of climb that ensures all altitude and path requirements of the procedure will be met 11 RNP operations are not authorized except as noted in the Operational Approvals section 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 3 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT TERRAIN AWARNESS AND WARNING SYSTEM TA WS SYSTEM LIMITATIONS NOTE The terrain display is intended to serve as a situational awareness tool only It may not provide either the accuracy or fidelity or both on which to solely base decisions and plan maneuve
54. rs to avoid terrain or obstacles 1 Navigation must not be predicated upon the use of the TAWS Terrain or Obstacle data displayed by the G1000 2 Pilots are authorized to deviate from their ATC clearance to the extent necessary to comply with terrain obstacle warnings from TAWS 3 The Terrain and Obstacle databases have an area of coverage as detailed below a The Terrain Database has an area of coverage from North 90 Latitude to South 90 Latitude in all longitudes b The Obstacle Database coverage area includes the United States and Europe NOTE The area of coverage may be modified as additional terrain data sources become available 4 When replacing or updating the TAWS terrain and obstacle database cards the following procedure must be conducted e The G1000 system must be turned off e After database card replacement apply power to the G1000 system to perform a TAWS system test A successful TAWS system test will result in the aural TAWS SYSTEM TEST OK message being played and removal of the TAWS TEST annunciator from the PFD and MFD displays Note the cockpit speaker must be ON or a headset worn to hear the TAWS aural message e Turn the G1000 system off 5 To avoid unwanted alerts TAWS must be inhibited when landing at an airport that is not included in the airport database 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPL
55. scent 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 12 Rev 6 Diamond DA 40 DA 40F 4A 12 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT SECTION 4B ABNORMAL PROCEDURES 4B 3 FAILURES IN THE ELECTRICAL SYSTEM a Low voltage caution LOW VOLTS This caution is indicated when the normal on board bus voltage 28V drops below 24V Possible reasons are A fault in the power supply RPM is too low i Low voltage caution on the ground 1 Engine speed is acne dedi tial elas sake ds 1200 RPM 2 Electrical equipment sis dusted ohio taney Bik dee devise Pe DER Re OFF 3 Ammeter and voltmeter iss esse es see ee ee ee ee ee ee ee ee ee Re ed ee ee check If the caution message does not extinguish and the ammeter legend flashes and ammeter gauge reads zero discontinue the flight ii Low voltage caution during flight 1 Electrical equipment iese ee soe sesse see E Gee ee OFF if not needed 2 Ammeter and voltmeter 00 0 eee esse ee se ee ee GR ee Re E a ee RR ee check If the caution message does not go out and the ammeter legend flashes and ammeter gauge reads zero follow procedure 3 7
56. seseseeesesesese 5 1 SECTION 6 WEIGHT AND BALANCE ees sesse see sesse see se ese see se ese see se ese see se ese 6 1 SECTION 7 SYSTEM DESCRIPTIONS ee ses sesse see se ese see se ese see se see se ese see se ese 7 1 190 00492 12 Rev 6 Diamond DA 40 DA 40F v This page is intentionally blank 190 00492 12 Rev 6 Diamond DA 40 DA 40F vi FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT SECTION 1 GENERAL G1000 The G1000 Integrated Avionics System is a fully integrated flight engine communication navigation and surveillance instrumentation system The system consists of a Primary Flight Display PFD Multi Function Display MFD audio panel Air Data Computer ADC Attitude and Heading Reference System AHRS engine sensors and processing unit GEA and dual integrated avionics units GIA each containing VHF communications VHF navigation and GPS Global Positioning System GIA 63 units are standard and provide non WAAS GPS position information in accordance with TSO C129a class Al Optional GIA 63W units provide WAAS augmented GPS position If the optional GIA63W units incorporate GPS software level 3 0 or later the GPS system meets the requirements of TSO C145a Class 3 The primary function of the PFD is to provide attitude heading air data navigation and alerting information to the pilot The PFD
57. ss of hazardous weather not penetration It is the pilot s responsibility to avoid hazardous weather using official weather data sources and the airplane s in flight weather radar if installed VERTICAL NAVIGATION VNAV LIMITATIONS Use of VNAV is prohibited with course changes greater than 90 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 5 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 2 3 AIRSPEED MARKINGS Marking IAS Significance Red band 20 KIAS 53 KIAS Low speed awareness stall is imminent Low speed awareness reduced Yellow band 53 KIAS 58 KIAS airspeed margin to stall White band 58 KIAS 91 KIAS Operating range with flaps fully extended Green band 58 KIAS 129 KIAS Normal operating range Yellow band 129 KIAS 178 KIAS Caution range smooth air only Red band 178 KIAS and greater 178 KIAS is the maximum speed for all operations The airspeed indicator is marked in IAS values 190 00492 12 Rev 6 Diamond DA 40 DA 40F FAA Approved 2 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 2 5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the table below
58. t for smooth running engine 135 FlapSi ss ee ES da ee ge sd gece ge ge eg ee ess dation Js check T O DA SST a E a EE ER NR EK ON check T O 15 ElightiGontrols iese ses ss SEE Gee e free movement correct sense 162 Throttle N EE EE EE EE aR 2000 RPM DA 40 1800 RPM DA 40 F T7 Magneto check sick HE EE 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 not run unduly roughly 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT 18 RPM lever DA 40 only 0 ese ee se se se ee pull back until a drop of max 500 RPM is reached HIGH RPM Cycle 3 times 18a Carburetor Heat DA 40 F only ese esse ee see es se ee ee ee se ee ee ge ee ee check function 18b Throttle DA 40 F only esse ee sees se ee ee MAX PWR minimum 2200 RPM 19 20 21 22 23 24 25 26 27 28 29 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 Headwin
59. t 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 Startel AREA EE Ar deere Rie Geis aA nasa vie HERE ik engage 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4A 6 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT When engine starts Ta POU pressures 42 55 EE NE RE ES green arc within 15 sec Mi ORR EE ER EE EE GE TE EE EE EE set 1000 RPM 9 Eleetrieal fuel pump i s is sees eb GE ER Ee Ge ee es eN ER bee ee Ge ER Gee GE Ee ER Dee Ee Ged 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 iese esse ee se ee RA ee ee Re GR Re ee Ge Re ee Ee Re ee ee ON Tdi AMI ter is ER as GE EE ta GER Ee ev Re Ge Se EE GE OE Ge Ge ee Oe Ge ve Oe Check 12 Annunciator section of PFD ieeee ee se se ee ee ee ee ee ee ee ee ee ee ee ee ee ee ee Check b Warm engine 1 Strobe light ACI EE ER ened Ha i Ge Ge Ee RE Re ee Ee ee ON Pe n OE EE EE RE E
60. tomatically reduced to 50 of maximum 1 Refer to standby attitude heading altimeter and airspeed instruments to maintain aircraft control 2 If either the PFD or MFD fails or is unusable pull the circuit breaker of the affected device and select Display Reversionary Mode using the red DISPLAY BACKUP button on the audio panel 3 Land as soon as practical at a suitable airport If the PFD fails or the PFD circuit breaker is pulled the autopilot will operate normally If the MFD fails or the MFD circuit breaker is pulled the autopilot vertical modes will operate normally Autopilot lateral modes will be limited to ROL mode only GIA1 OVERHEAT caution OR GIA2 OVERHEAT caution NOTE Either GIA 1 or GIA 2 is approaching its operating temperature limit 1 Minimize all COM transmissions to reduce temperature GIA1 OVERHEAT caution AND GIA2 OVERHEAT caution NOTE Both GIA 1 and GIA 2 are approaching their operating temperature limits COM 1 COM 2 NAV 1 NAV 2 GPS 1 and GPS 2 may fail 1 Minimize all COM transmissions to reduce temperature 2 Land as soon as practical at a suitable airport 190 00492 12 Rev 6 Diamond DA 40 DA 40F 4B 4 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT SECTION 5 PERFORMANCE No change Refer to the Aircraft Flight Manual 190 00492 12 Rev 6 Diam
61. uel displays show an abnormal or emergency situation and the annunciator is not present An erroneous annunciator may be identified when an annunciator appears which does not agree with other displays or system information 1 If an annunciator appears treat it as if the condition exists Refer to the AFM Emergency or Abnormal procedures or the procedures contained in this AFMS 2 If a display indicates an abnormal condition but no annunciator is present use other system information such as engine displays ENGINE SYSTEM page GAL REM and FFLOW GPH displays to determine if the condition exists If it cannot be determined that the condition does not exist treat the situation as if the condition exists Refer to the AFM Emergency or Abnormal procedures or the procedures contained in this AFMS 190 00492 12 Rev 6 Diamond DA 40 DA 40F 3 10 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT GARMIN G1000 INTEGRATED AVIONICS SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F WITH HONEYWELL KAP 140 AUTOPILOT SECTION 4A NORMAL PROCEDURES NOTE Readability of the PFD and MFD displays may be degraded when wearing polarized sunglasses DETAILED OPERATING PROCEDURES Normal operating procedures for the G1000 are described in the Garmin G1000 Cockpit Reference Guide and the Garmin G1000 Pilot s Guide PRE FLIGHT INSPECTION I Cabin check a MET NAV Mass amp CG oe cece sees se es se ee ee ee flight planning complete b Airplane d

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