Diamond DA 62 Flight Manual Download

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DA 62 AFM

Mass and Balance

6.4.5 PERMISSIBLE MOMENT RANGE

The flight mass moments shown in the diagram are those from the example in Table 6.4.3

- CALCULATION OF LOADING CONDITION, rows 11 and 14.

Doc. No. 11.01.05-E

Rev. 0

11-Jan-2019

Page 6 - 17

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Summary of Contents for DA 62

Page 1: ...he List of Effective Pages and in the Record of Revisions Signature Authority g A K J I Chief Flight Test Chief Flight Test for Director National Aircraft Transport Canada Civil AviatiorCertification ANSPORT CANADA Date of approval 3cJ ro1q This Airplane Flight Manual has been approved by the Canadian Department of Transport in accordance with the Canadian Aviation Regulations Diamond Aircraft Ind...

Page 2: ...DA 62 AFM Introduction Intentionally left blank Page 0 0a Rev 0 11 Jan 2019 Doc 11 01 05 E ...

Page 3: ... complete contents of this Airplane Flight Manual In the event that you have obtained your DIAMOND DA 62 second hand please let us know your address so that we can supply you with the publications necessary for the safe operation of your airplane This document is protected by copyright All associated rights in particular those of translation reprinting radio transmission reproduction by photo mech...

Page 4: ... page If pages are revised which contain information valid for your particular serial number modification level of the airplane weighing data Equipment Inventory List of Supplements thenthisinformation must be transferred to the newpagesin hand writing Temporary Revisions if applicable are inserted behind the cover page of this manual Temporary Revisions are used to provide information on systems ...

Page 5: ...DA 62 AFM Introduction Rev No Reason Chapter Page s Date of Revision Approval No Approval Date Date Inserted Signature Doc 11 01 05 E Rev 0 11 Jan 2019 Page 0 3 ...

Page 6: ...11 Jan 2019 0 13 11 Jan 2019 0 14 11 Jan 2019 0 15 11 Jan 2019 Ch Page Date 1 1 1 11 Jan 2019 1 2 11 Jan 2019 1 3 11 Jan 2019 1 4 11 Jan 2019 1 5 11 Jan 2019 1 6 11 Jan 2019 1 7 11 Jan 2019 1 8 11 Jan 2019 1 9 11 Jan 2019 1 10 11 Jan 2019 1 11 11 Jan 2019 1 12 11 Jan 2019 1 13 11 Jan 2019 1 14 11 Jan 2019 1 15 11 Jan 2019 1 16 11 Jan 2019 1 17 11 Jan 2019 1 18 11 Jan 2019 1 19 11 Jan 2019 1 20 11 ...

Page 7: ...Jan 2019 DOT appr 2 20 11 Jan 2019 DOT appr 2 21 11 Jan 2019 DOT appr 2 22 11 Jan 2019 DOT appr 2 23 11 Jan 2019 DOT appr 2 24 11 Jan 2019 DOT appr 2 25 11 Jan 2019 DOT appr 2 26 11 Jan 2019 DOT appr 2 27 11 Jan 2019 Ch Page Date 2 DOT appr 2 28 11 Jan 2019 DOT appr 2 29 11 Jan 2019 DOT appr 2 30 11 Jan 2019 DOT appr 2 31 11 Jan 2019 DOT appr 2 32 11 Jan 2019 DOT appr 2 33 11 Jan 2019 DOT appr 2 3...

Page 8: ...9 3 23 11 Jan 2019 3 24 11 Jan 2019 3 25 11 Jan 2019 3 26 11 Jan 2019 3 27 11 Jan 2019 Ch Page Date 3 3 28 11 Jan 2019 3 29 11 Jan 2019 3 30 11 Jan 2019 3 31 11 Jan 2019 3 32 11 Jan 2019 3 33 11 Jan 2019 3 34 11 Jan 2019 3 35 11 Jan 2019 3 36 11 Jan 2019 3 37 11 Jan 2019 3 38 11 Jan 2019 3 39 11 Jan 2019 3 40 11 Jan 2019 3 41 11 Jan 2019 3 42 11 Jan 2019 3 43 11 Jan 2019 3 44 11 Jan 2019 3 45 11 J...

Page 9: ... 2019 3 74 11 Jan 2019 Ch Page Date 4A 4A 1 11 Jan 2019 4A 2 11 Jan 2019 4A 3 11 Jan 2019 4A 4 11 Jan 2019 4A 5 11 Jan 2019 4A 6 11 Jan 2019 4A 7 11 Jan 2019 4A 8 11 Jan 2019 4A 9 11 Jan 2019 4A 10 11 Jan 2019 4A 11 11 Jan 2019 4A 12 11 Jan 2019 4A 13 11 Jan 2019 4A 14 11 Jan 2019 4A 15 11 Jan 2019 4A 16 11 Jan 2019 4A 17 11 Jan 2019 4A 18 11 Jan 2019 4A 19 11 Jan 2019 4A 20 11 Jan 2019 4A 21 11 J...

Page 10: ...9 4A 45 11 Jan 2019 4A 46 11 Jan 2019 4A 47 11 Jan 2019 4A 48 11 Jan 2019 4A 49 11 Jan 2019 4A 50 11 Jan 2019 4A 51 11 Jan 2019 4A 52 11 Jan 2019 4A 53 11 Jan 2019 4A 54 11 Jan 2019 Ch Page Date 4A 4A 55 11 Jan 2019 4A 56 11 Jan 2019 4A 57 11 Jan 2019 4A 58 11 Jan 2019 4A 59 11 Jan 2019 4A 60 11 Jan 2019 4A 61 11 Jan 2019 4A 62 11 Jan 2019 4A 63 11 Jan 2019 4A 64 11 Jan 2019 4A 65 11 Jan 2019 4A 6...

Page 11: ... 2019 4B 18 11 Jan 2019 4B 19 11 Jan 2019 4B 20 11 Jan 2019 4B 21 11 Jan 2019 4B 22 11 Jan 2019 4B 23 11 Jan 2019 4B 24 11 Jan 2019 4B 25 11 Jan 2019 4B 26 11 Jan 2019 4B 27 11 Jan 2019 Ch Page Date 4B 4B 28 11 Jan 2019 4B 29 11 Jan 2019 4B 30 11 Jan 2019 4B 31 11 Jan 2019 4B 32 11 Jan 2019 4B 33 11 Jan 2019 4B 34 11 Jan 2019 4B 35 11 Jan 2019 4B 36 11 Jan 2019 4B 37 11 Jan 2019 4B 38 11 Jan 2019 ...

Page 12: ...9 5 23 11 Jan 2019 5 24 11 Jan 2019 5 25 11 Jan 2019 5 26 11 Jan 2019 5 27 11 Jan 2019 Ch Page Date 5 5 28 11 Jan 2019 5 29 11 Jan 2019 5 30 11 Jan 2019 5 31 11 Jan 2019 5 32 11 Jan 2019 5 33 11 Jan 2019 5 34 11 Jan 2019 5 35 11 Jan 2019 5 36 11 Jan 2019 5 37 11 Jan 2019 5 38 11 Jan 2019 5 39 11 Jan 2019 5 40 11 Jan 2019 5 41 11 Jan 2019 5 42 11 Jan 2019 5 43 11 Jan 2019 5 44 11 Jan 2019 5 45 11 J...

Page 13: ... 2019 5 69 11 Jan 2019 5 70 11 Jan 2019 5 71 11 Jan 2019 5 72 11 Jan 2019 5 73 11 Jan 2019 5 74 11 Jan 2019 5 75 11 Jan 2019 5 76 11 Jan 2019 5 77 11 Jan 2019 5 78 11 Jan 2019 5 79 11 Jan 2019 5 80 11 Jan 2019 5 81 11 Jan 2019 Ch Page Date 5 5 82 11 Jan 2019 5 83 11 Jan 2019 5 84 11 Jan 2019 5 85 11 Jan 2019 5 86 11 Jan 2019 5 87 11 Jan 2019 5 88 11 Jan 2019 5 89 11 Jan 2019 5 90 11 Jan 2019 5 91 ...

Page 14: ... 23 11 Jan 2019 6 24 11 Jan 2019 6 25 11 Jan 2019 6 26 11 Jan 2019 6 27 11 Jan 2019 6 28 11 Jan 2019 Ch Page Date 6 6 29 11 Jan 2019 Ch Page Date 7 7 1 11 Jan 2019 7 2 11 Jan 2019 7 3 11 Jan 2019 7 4 11 Jan 2019 7 5 11 Jan 2019 7 6 11 Jan 2019 7 7 11 Jan 2019 7 8 11 Jan 2019 7 9 11 Jan 2019 7 10 11 Jan 2019 7 11 11 Jan 2019 7 12 11 Jan 2019 7 13 11 Jan 2019 7 14 11 Jan 2019 7 15 11 Jan 2019 7 16 1...

Page 15: ... 2019 7 49 11 Jan 2019 7 50 11 Jan 2019 7 51 11 Jan 2019 7 52 11 Jan 2019 7 53 11 Jan 2019 Ch Page Date 7 7 54 11 Jan 2019 7 55 11 Jan 2019 7 56 11 Jan 2019 7 57 11 Jan 2019 7 58 11 Jan 2019 7 59 11 Jan 2019 7 60 11 Jan 2019 7 61 11 Jan 2019 7 62 11 Jan 2019 7 63 11 Jan 2019 7 64 11 Jan 2019 7 65 11 Jan 2019 7 66 11 Jan 2019 7 67 11 Jan 2019 7 68 11 Jan 2019 7 69 11 Jan 2019 7 70 11 Jan 2019 7 71 ...

Page 16: ...3 11 Jan 2019 7 94 11 Jan 2019 Ch Page Date 8 8 1 11 Jan 2019 8 2 11 Jan 2019 8 3 11 Jan 2019 8 4 11 Jan 2019 8 5 11 Jan 2019 8 6 11 Jan 2019 8 7 11 Jan 2019 8 8 11 Jan 2019 8 9 11 Jan 2019 8 10 11 Jan 2019 8 11 11 Jan 2019 8 12 11 Jan 2019 8 13 11 Jan 2019 8 14 11 Jan 2019 8 15 11 Jan 2019 8 16 11 Jan 2019 Ch Page Date 9 9 1 11 Jan 2019 9 2 11 Jan 2019 9 3 11 Jan 2019 9 4 11 Jan 2019 Page 0 14 Re...

Page 17: ...RATING PROCEDURES a non approved chapter 4A ABNORMAL OPERATING PROCEDURES a non approved chapter 4B PERFORMANCE a non approved chapter 5 MASS AND BALANCE EQUIPMENT LIST a non approved chapter 6 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS a non approved chapter 7 AIRPLANE HANDLING CARE AND MAINTENANCE a non approved chapter 8 SUPPLEMENTS 9 Doc 11 01 05 E Rev 0 11 Jan 2019 Page 0 15 ...

Page 18: ...5 1 5 DEFINITIONS AND ABBREVIATIONS 1 7 1 6 UNITS OF MEASUREMENT 1 16 1 6 1 CONVERSION FACTORS 1 16 1 6 2 CONVERSION CHART LITERS US GALLONS 1 18 1 7 THREE VIEW DRAWING 1 19 1 8 G1000 AVIONICS SYSTEM 1 20 1 9 SOURCE DOCUMENTATION 1 21 1 9 1 ENGINE 1 21 1 9 2 PROPELLER 1 21 1 9 3 AVIONICS SYSTEM 1 22 Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 1 1 ...

Page 19: ...e depending on the respective equipment and modification level The exact equipment of your serial number is recorded in the Equipment Inventory in Section 6 5 The modification level is recorded in the following table as far as necessary for this manual Modification Source Installed MTOM 2300 kg 5071 lb MÄM 62 001 9 yes 9 no Maximum Zero Fuel Mass 2200 kg 4850 lb MÄM 62 063 9 yes 9 no Engine Softwa...

Page 20: ...ft seat The designated place for the Garmin G1000 Cockpit Reference Guide is the bag on the rear side of the forward right seat CAUTION The DA 62 is a twin engine airplane When the operating limitationsand maintenancerequirementsare compliedwith it has the high degree of reliability which is required by the certification basis Nevertheless an engine failure is not completely impossible For this re...

Page 21: ...operation of the airplane are highlighted by being prefixed by one of the following terms WARNING means that the non observation of the corresponding procedure leads to an immediate or important degradation in flight safety CAUTION means that the non observation of the corresponding procedure leads to a minor or to a more or less long term degradation in flight safety NOTE draws the attention to a...

Page 22: ...m 47 ft 10 in Length 9 17 m 30 ft 1 in Height 2 82 m 9 ft 3 in Wing Airfoil Wortmann FX 63 137 20 W4 Wing Area 17 10 m 184 1 sq ft Mean aerodynamic chord 1 247 m 4 ft 1 in Aspect ratio 12 8 Dihedral 5 2 Leading edge sweep 1 Aileron Area total left right 0 65 m 7 sq ft Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 1 5 ...

Page 23: ... 83 sq ft Angle of incidence 2 relative to longitudinal axis of airplane Vertical Tail Area 2 31 m 24 86 sq ft Rudder area 0 74 m 7 97 sq ft Landing Gear Track 2 95 m 9 ft 8 in Wheelbase 1 91 m 6 ft 3 in Nose wheel 6 00 6 for details refer to AMM Main wheel 6 00 6 for details refer to AMM Page 1 6 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 24: ...ve this speed vFE Maximum Flaps Extended Speed This speed must not be exceeded with the given flap setting vLE Maximum Landing Gear Extended Speed This speed may not be exceeded if the landing gear is extended vLOE Maximum Landing Gear Operating Speed for Extension This speed may not be exceeded during the extension of the landing gear vLOR Maximum Landing Gear Operating Speed for Retraction This ...

Page 25: ...imum Control Speed for Schooling Minimum speed necessary in case of one engine intentionally inoperative idle training purposes vx Best Angle of Climb Speed vy Best Rate of Climb Speed vYSE Best Rate of Climb Speed for one engine inoperative v50ft Speed at 50 ft above take off surface b Meteorological Terms ISA International Standard Atmosphere Conditions at which air is identified as an ideal dry...

Page 26: ...to 1013 25 hPa 29 92 inHg The Pressure Altitude is the Indicated Pressure Altitude corrected for installation and instrument errors In this Airplane Flight Manual altimeter instrument errors are regarded as zero Wind The wind speeds which are shown as variables in the diagrams and tables in this manual should be regarded as headwind or tailwind components of the measured wind c Flight Performance ...

Page 27: ...The Moment Arm which is obtained if one divides the sum of the individual moments of the airplane by its total mass Center of Gravity Limits The Center of Gravity range within which the airplane at a given mass must be operated DP Datum Plane an imaginary vertical plane from which all horizontal distances for center of gravity calculations are measured Empty Mass The mass of the airplane including...

Page 28: ...ent arm Usable fuel The quantity of fuel available for flight planning Unusable fuel The quantity of fuel remaining in the tank which cannot be used for flight Useful load The difference between take off mass and empty mass e Engine EECU Electr Engine Control Unit RPM Revolutions per minute rotational speed of the propeller Engine starting fuel temperature Above this fuel temperature the engine ma...

Page 29: ...omputer AHRS Attitude Heading Reference System GEAR WRN Landing Gear Annunciation GEAR Landing Gear Control AUX PUMPS Aux Fuel Pumps RH MAIN BUS MFD Multi Function Display SAM Standby Altitude Module STALL WRN Stall Warning System FLAP Flap System LDG LT START Landing Light Start NAV LT FLOOD Navigation Position Light Flood Light AV GDU FAN Avionic GDU Cooling Fans AVIONIC BUS Avionic Bus AV CONT ...

Page 30: ...stance Measuring Equipment Wx RDR Weather Radar TAS Traffic Advisory System DATA LINK Data Link System IRIDIUM Satellite Receiver EVS Enhanced Vision System GCU FLT STRM Control Unit Keypad Flight Stream LH ENG ECU BUS ECU BUS LH ECU Bus ECU B LH ECU B ECU A LH ECU A LH BUS ALT LH LH Alternator BATT Battery LH ENGINE FUEL PUMP A LH ECU A Fuel Pump FUEL PUMP B LH ECU B Fuel Pump Doc No 11 01 05 E R...

Page 31: ...BATT Battery RH ENGINE FUEL PUMP A RH ECU A Fuel Pump FUEL PUMP B RH ECU B Fuel Pump g Equipment ELT Emergency Locator Transmitter h Design Change Advisories MÄM Mandatory Design Change Advisory OÄM Optional Design Change Advisory VÄM Variant Design Change Advisory Page 1 14 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 32: ...Plastic DOT Department of Transport EASA European Aviation Safety Agency EPU External Power Unit GIA Garmin Integrated Avionics GFRP Glass Fiber Reinforced Plastic GPS Global Positioning System IFR Instrument Flight Rules JC VP Joint Certification Validation Procedure PCA Primary Certification Authority TCCA Transport Canada Civil Aviation VFR Visual Flight Rules Doc No 11 01 05 E Rev 0 11 Jan 201...

Page 33: ...ometers per hour m s meters per second kts knots mph miles per hour fpm feet per minute km h 1 852 kts km h 1 609 mph m s x 196 85 fpm fpm 196 85 m s Speed of rotation RPM revolutions per minute Mass kg kilograms lb pounds kg x 2 2046 lb Force weight N Newtons lbf pounds force N x 0 2248 lbf Pressure hPa hecto pascals mbar millibars bar bars inHg inches of mercury psi pounds per square inch hPa mb...

Page 34: ... Dimension SI Units US Units Conversion Intensity of electric current A ampères Electric charge battery capacity Ah ampère hours Electric potential V volts Time sec seconds Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 1 17 ...

Page 35: ...8 30 3 30 7 9 10 37 9 35 9 2 12 45 4 40 10 6 14 53 0 45 11 9 16 60 6 50 13 2 18 68 1 60 15 9 20 75 7 70 18 5 22 83 3 80 21 1 24 90 9 90 23 8 26 98 4 100 26 4 28 106 0 110 29 1 30 113 6 120 31 7 32 121 1 130 34 3 34 128 7 140 37 0 36 136 3 150 39 6 38 143 8 160 42 3 40 151 4 170 44 9 45 170 3 180 47 6 50 189 3 Page 1 18 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 36: ...DA 62 AFM General 1 7 THREE VIEW DRAWING Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 1 19 ...

Page 37: ...o 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 satellites recoverorbitaldata makerange and Doppler measurements and process this information in real time to obtain the user s position...

Page 38: ...ight Manual is valid 1 9 1 ENGINE Address Austro Engine GmbH Rudolf Diesel Str 11 A 2700 Wiener Neustadt AUSTRIA Phone 43 2622 23 000 Fax 43 2622 23 000 2711 Internet www austroengine at Documents Operation Manual E4 01 02 latest revision 1 9 2 PROPELLER Address mt propeller Airport Straubing Wallmühle D 94348 Atting GERMANY Phone 49 9429 9409 0 E mail sales mt propeller com Website www mt propell...

Page 39: ...onal Inc 1200 East 151st Street Olathe Kansas 66062 USA Phone 1 913 3978200 Fax 1 913 3978282 Website www garmin com Documents G1000 Cockpit Reference Guide P N 190 01896 latest revision G1000 Pilot s Guide P N 190 01895 latest revision G1000 NXi Cockpit Reference Guide P N 190 01905 latest revision G1000 NXi Pilot s Guide P N 190 01904 latest revision Page 1 22 Rev 0 11 Jan 2019 Doc No 11 01 05 E...

Page 40: ... 2 6 2 OTHER WARNING ALERTS 2 18 2 7 MASS WEIGHT 2 19 2 8 CENTER OF GRAVITY 2 20 2 9 APPROVED MANEUVERS 2 21 2 10 MANEUVERING LOAD FACTORS 2 22 2 11 OPERATING ALTITUDE 2 23 2 12 FLIGHT CREW 2 23 2 13 KINDS OF OPERATION 2 23 2 14 FUEL 2 27 2 15 LIMITATION PLACARDS 2 30 2 16 OTHER LIMITATIONS 2 36 2 16 1 FUEL TEMPERATURE 2 36 2 16 2 BATTERY CHARGE 2 36 2 16 3 DOOR LOCKING DEVICE 2 36 2 16 4 ELECTRON...

Page 41: ... LIMITATIONS 2 42 2 16 7 SMOKING 2 43 2 16 8 GROUND OPERATION 2 43 2 16 9 GARMIN GWX 70 WEATHER RADAR OPERATION 2 43 2 16 10 USE OF THE SUN VISORS 2 44 2 16 11 PDF MFD CONTROL UNIT KEYPAD 2 44 Page 2 2 Rev 0 11 Jan 2019 DOT approved Doc No 11 01 05 E ...

Page 42: ...rkings and placards necessary for the safe operation of the airplane its powerplants standard systems and standard equipment The limitations included in this Chapter are approved WARNING Operation of the airplane outside of the approved operating limitations is not permissible Doc No 11 01 05 E Rev 0 11 Jan 2019 DOT approved Page 2 3 ...

Page 43: ...00 kg 4189 lb to 1999 kg 4407 lb 131 KIAS above 1800 kg 3968 lb to 1900 kg 4189 lb 128 KIAS up to 1800 kg 3968 lb 120 KIAS vFE Max flaps extended speed LDG 119 KIAS Do not exceed these speeds with the given flap setting T O 136 KIAS vLO Max landing gear operating speed Extension vLOE 205 KIAS Do not operate the landing gear above this speed Retraction vLOR 162 KIAS vLE Max landing gear extended sp...

Page 44: ...e inoperative keep airspeed above this limit UP 76 KIAS vNO Max structural cruising speed 162 KIAS Do not exceed this speed except in smooth air and then only with caution vNE Never exceed speed in smooth air 205 KIAS Do not exceed this speed in any operation Doc No 11 01 05 E Rev 0 11 Jan 2019 DOT approved Page 2 5 ...

Page 45: ...arc 70 162 KIAS Normal operating range If MÄM 62 001 is carried out 73 162 KIAS Yellow arc 162 205 KIAS Caution range Only in smooth air Blue radial 87 KIAS Best rate of climb speed single engine If MÄM 62 001 is carried out 89 KIAS Red radial 76 KIAS Minimum control speed single engine Red radial 205 KIAS Maximum speed for all operations vNE Page 2 6 Rev 0 11 Jan 2019 DOT approved Doc No 11 01 05...

Page 46: ...imum overspeed 2500 RPM max 20 sec e Engine power Max take off power 100 132 kW max 5 min Max continuous power 95 126 kW f Oil pressure absolute Minimum 1500 RPM 0 9 bar 13 05 psi Minimum 1500 RPM 2 5 bar 36 26 psi Maximum 6 5 bar 94 25 psi Normal range 2 5 bar 6 bar 36 26 psi 87 02 psi g Oil quantity Minimum 5 0 l 5 28 qts Maximum 7 0 l 7 40 qts Maximum oil consumption 0 1 liter h 0 11 qts h Doc ...

Page 47: ... there is a delay between power changes and gearbox temperature Therefore a cautionary range has been added to the G1000 gearbox temperature instrument solely to make the pilot attentive to the gearbox temperature approaching the maximum allowable limit There is no specific time limit associated with operating in the cautionary gearbox temperature range j Coolant temperature Minimum at start up 30...

Page 48: ...will illuminate on the PFD if the pressure is below limit m Voltage Minimum 24 1 V Maximum 32 0 V n Amperage Maximum 70 A o Propeller manufacturer mt Propeller p Propeller designation MTV 6 R C F CF 194 80 q Propeller diameter 194 cm 76 38 in r Prop pitch angle 0 75 R 11 0 2 low pitch 80 1 feathered position s Governor mt PropellerP 877 16 electricalgovernorwith feather position Doc No 11 01 05 E ...

Page 49: ...40 SHELL HELIX ULTRA LIQUI MOLY LEICHTLAUF HIGH TECH MEGOL MOTORENOEL HIGH CONDITION PETRONAS Syntium 3000 LUKOIL LUXE SYNTHETIC CASTROL Edge Professional A3 CASTROL Magnatec Professional A3 VALVOLINE SynPower HST VALVOLINE SynPower GULF Formula GX AUSTRO ENGINE Aero produced by Liqui Moly recommended by Austro Engine GmbH SAE Grade 0W 40 CASTROL SLX PROFESSIONAL LONGTEC CASTROL Edge 0W 40 A3 B4 C...

Page 50: ...water cooler protection BASF Glysantin Protect Plus G48 1 1 The freezing point of the coolant is 38 C 36 4 F CAUTION If the coolant or gearbox oil level is low the reason must be determined and the problem must be corrected byauthorized personnel w Maximum restart altitude 20 000 ft pressure altitude for immediate restarts 10 000 ft pressure altitude for restarts within two minutes If MÄM 62 168 e...

Page 51: ... whichever is lower WARNING VMCA is 76 KIAS and should be considered when attempting to engine restart with the starter and obtaining a stationary propeller This limitation should be observed Restart airspeed windmilling Maximum 115 KIAS Minimum 110 KIAS below 10 000 ft 100 KIAS above 10 000 ft y No intentional shutdown below 3 000 ft AGL and above 10 000 ft pressure altitude Page 2 12 Rev 0 11 Ja...

Page 52: ...0 RPM Oil pressure below 0 9 bar 0 9 to 2 5 bar 2 5 to 6 0 bar 6 0 to 6 5 bar above 6 5 bar Oil temp below 30 C 30 to 50 C 50 to 135 C 135 to 139 C above 139 C Coolant temp below 30 C 30 to 60 C 60 to 95 C 95 to 100 C above 100 C Gearbox temp below 30 C 30 to 35 C 35 to 115 C 115 to 120 C above 120 C Load up to 95 95 100 Fuel temp below 30 C 30 to 55 C 55 to 60 C above 60 C Ammeter up to 60A 60 to...

Page 53: ...aning Cause WARNING One of the warnings listed below is being indicated L R ENG TEMP Left Right engine coolant temperature is in the upper red range too high 100 C 212 F L R OIL TEMP Left Right engine oil temperature is in the upper red range too high 139 C 282 F L R OIL PRES Left Right engine oil pressure is in the lower red range too low 0 9 bar 13 05 psi L R FUEL TEMP Left Right fuel temperatur...

Page 54: ...information from the AHRS AIRSPEED FAIL The display system is not receiving airspeed input from the air data computer ALTITUDE FAIL The display system is not receiving altitude input from the air data computer VERT SPEED FAIL The display system is not receiving vertical speed input from the air data computer HDG The display system is not receiving valid heading input from the AHRS WARN RAIM positi...

Page 55: ... Right main tank fuel quantity is low L R ALTN FAIL Left Right engine alternator has failed L R VOLTS LOW Left Right engine bus voltage is too low 25 V L R COOL LVL Left Right engine coolant level is low PITOT FAIL Pitot heat has failed PITOT HT OFF Pitot heat is OFF STAL HT FAIL Stall warning heat has failed STAL HT OFF Stall warning heat is OFF LOI GPS integrity is insufficient for the current p...

Page 56: ...ory Alerts on the G1000 Advisory Alerts White Meaning Cause L R GLOW ON Left Right engine glow plug active L R AUXPUMP ON Fuel transfer from auxiliary to main tank is in progress if installed PFD FAN FAIL Cooling fan for the PFD is inoperative MFD FAN FAIL Cooling fan for the MFD is inoperative GIA FAN FAIL Cooling fan for the GIAs is inoperative Doc No 11 01 05 E Rev 0 11 Jan 2019 DOT approved Pa...

Page 57: ...gear is neither in the final up nor in the down locked position Audible Warning Alerts Audible Warning Alert Meaning Cause GEAR RETRACTED CHIME TONE repeating Resounds if the landing gear is in retracted configuration and the flaps move into LDG position or when the power lever is placed in a position below approximately 25 Page 2 18 Rev 0 11 Jan 2019 DOT approved Doc No 11 01 05 E ...

Page 58: ...66 lb Max total load in rear baggage compartment 120 kg 265 lb Max load in section A of rear baggage compartment 6 kg 13 lb Max load in section B of rear baggage compartment 6 kg 13 lb Max load in section C of rear baggage compartment 68 kg 150 lb Max load in section D of rear baggage compartment 40 kg 88 lb If OÄM 62 019 is carried out Max load total load in rear baggage compartment 46 kg 101 lb ...

Page 59: ...mitations The center of gravity CG position for flight conditions must be between the following limits Most forward flight CG 2 340 m 92 13 in aft of datum plane at 1600 kg 3527 lb to 1800 kg 3968 lb 2 460 m 96 85 in aft of datum plane at max take off mass see Section 2 7 linear variation in between Most rearward flight CG 2 460 m 96 85 in aft of datum plane at 1600 kg 3527 lb 2 510 m 98 82 in aft...

Page 60: ...d 3 Lazy Eights Chandelles as well as steep turns and similar maneuvers in which an angle of bank of not more than 60 is attained CAUTION Aerobatics spinningand flight maneuverswith morethan60 of bank are not permitted in the Normal Category Stalling with asymmetric power or one engine inoperative is not permitted CAUTION Intentional negative g maneuvers are not permitted Doc No 11 01 05 E Rev 0 1...

Page 61: ...rved Refer to the corresponding operation manual for the engine at vO at vNE with flaps in APP or LDG position Positive 3 8 3 8 2 0 Negative 1 52 0 0 0 0 WARNING Exceeding the maximum structural load factors will lead to overstressing of the airplane CAUTION Intentional negative g maneuvers are not permitted Page 2 22 Rev 0 11 Jan 2019 DOT approved Doc No 11 01 05 E ...

Page 62: ...pment nightflightsaccordingtoVisualFlightRules NVFR with the appropriate equipment flights according to Instrument Flight Rules IFR take off and landing on paved surfaces take off and landing on grass surfaces Flights into known or forecast thunderstorms are prohibited Flights into known or forecast icing conditions are prohibited Minimum Operational Equipment Serviceable The following table lists...

Page 63: ...et used by pilot in command vertical speed indicator VSI attitude gyro artificial horizon on G1000 PFD or backup turn bank indicator on G1000 PFD directional gyro VHF radio COM VOR receiver transponder XPDR mode A and mode C GPS receiver part of G1000 second headset second airspeed indicator both on G1000 PFD and backup second altimeter both on G1000 PFD and backup second attitude gyro both on G10...

Page 64: ...il press 2x oil temp 2x coolant temp 2x coolant level indicator 2x gearbox temp 2x load 2x prop RPM 2x fuel temp left right tank fuel flow 2x fuel px warning ammeter voltmeter Lighting position lights strobe lights anti collision lights landing light instrument lighting flood light flashlight Doc No 11 01 05 E Rev 0 11 Jan 2019 DOT approved Page 2 25 ...

Page 65: ...cupied seat Airplane Flight Manual Egress Hammer Pitot heating system alternate static valve sufficient charge for the internal battery of the Standby Attitude Module NOTE A list of approved equipment can be found in Chapter 6 Engine Systems and Equipment Allenginesystemsand equipmentmust be functionalpriorto airplane take off Anyengine system or equipment failure must be corrected before next fli...

Page 66: ...el grades NOTE A minimum cetane number of 36 determined acc to EN ISO 5165 ASTM D613 is recommended NOTE Use only uncontaminated fuel from reliable sources Any mixture of the different types of fuel additives is not permitted OPERATION WITH ANTI MICROBIAL LIFE FUEL ADDITIVES The application of the following additives is permitted KATHON FP 1 5 max 100 ppm BIOBOR JF max 270 ppm for initial treatmen...

Page 67: ...h the certified fuel grades NOTE The instructionsof thefueladditivesuppliermust be followed OPERATION WITH ANTI ICING FUEL ADDITIVES The application of the following additive is permitted PRIST Hi Flash max 1500 ppm CAUTION The useof PRIST Hi Flash fuel additive isonlypermitted with JET A JET A 1 ASTM D 1655 and JP 8 F34 NOTE The instructionsof thefueladditivesuppliermust be followed Page 2 28 Rev...

Page 68: ...S gal Liter US gal Liter US gal Liter Total fuel quantity 2 x 26 0 2 x 98 4 2 x 18 5 2 x 70 0 2 x 44 5 2 x 168 4 Usable fuel 2 x 25 0 2 x 94 6 2 x 18 2 2 x 68 9 2 x 43 2 2 x 163 5 Max permissible difference LH RH 5 0 18 9 Doc No 11 01 05 E Rev 0 11 Jan 2019 DOT approved Page 2 29 ...

Page 69: ...cards are shown below A list of all placards is included in the Airplane Maintenance Manual Doc No 7 02 25 Chapter 11 The following limitation placards are in the forward view of the pilot Left of the Instrument Panel Page 2 30 Rev 0 11 Jan 2019 DOT approved Doc No 11 01 05 E ...

Page 70: ...the Emergency Landing Gear Extension Lever On the Instrument Panel Standard Tank Auxiliary Tank if installed max usable fuel 2 x 25 US gal max difference LH RH tank 5 US gal max usable fuel main tank 2 x 25 US gal auxiliary tank 2 x 18 2 US gal max difference LH RH main tank 5 US gal Doc No 11 01 05 E Rev 0 11 Jan 2019 DOT approved Page 2 31 ...

Page 71: ... Filler Necks b In Addition Next to Each of the Two Auxiliary Fuel Filler Necks if installed In Each Cowling on the Door for the Oil Filler Neck OIL AUSTRO ENGINE Aero 5W 40 or see Airplane Flight Manual OR OIL SHELL HELIX ULTRA 5W 30 or see Airplane Flight Manual Page 2 32 Rev 0 11 Jan 2019 DOT approved Doc No 11 01 05 E ...

Page 72: ...ns Next to the Flap Selector Switch In the Nose Baggage Compartments LH Nose Baggage Compartment RH Nose Baggage Compartment Max Baggage 30 kg 66 lb Max Baggage 30 kg 66 lb Doc No 11 01 05 E Rev 0 11 Jan 2019 DOT approved Page 2 33 ...

Page 73: ...Operating Limitations DA 62 AFM In the Rear Baggage Compartment If OÄM 62 019 is NOT carried out If OÄM 62 019 is carried out Page 2 34 Rev 0 11 Jan 2019 DOT approved Doc No 11 01 05 E ...

Page 74: ...m Center of the Instrument Panel On the Armrest with Integrated Keypad if OÄM 62 031 is carried out STOW FOR TAKE OFF AND LANDING IN ALL EMERGENCIES AND ABNORMAL OPERATING PROCEDURES EMERGENCY EXIT The keylock must be unlocked during flight NO SMOKING Doc No 11 01 05 E Rev 0 11 Jan 2019 DOT approved Page 2 35 ...

Page 75: ...t the engine cannot be started with battery power The use of an externalpowersupply for engine starting with a discharged airplane battery is not permitted if the subsequent flight is intended to be a Night VFR or IFR flight In this case the airplane main battery must be charged first 2 16 3 DOOR LOCKING DEVICE The LH RH CREW DOORS and the passenger door must not be blocked by the key lock during ...

Page 76: ...dio controls Video screens employing CRTs Minidisc recorders in record mode This list is not exhaustive The use of laptop and handheld computers including those with CD ROM drives CD and mini discplayersin thereplaymode cassette playersand videocamerasispermitted All this equipment however should be switched off for take off and landing NOTE Referto theapplicableflightauthority for the use of elec...

Page 77: ...ce with the mandatory service bulletin DAI MSB 62 003 latest version Software Part Number Approved Version Function System for approved version see DAI MSB 62 003 latest version 010 01895 Manifest 006 B0093 GPS1 GPS2 006 B0172 GTX1 GIA1 GTX1 GIA2 006 B0190 GIA1 GIA2 006 B0193 GEA1 GIA1 GEA1 GIA2 006 B0203 GMA1 GIA1 GMA1 GAI2 006 B0223 GRS1 GIA1 GRS1 GIA2 006 B0224 GMU1 006 B0319 PFD1 MFD1 006 B032...

Page 78: ...reference to current approved data 4 Instrument approach navigation predicated upon the G1000 GPS receiver must be accomplished inaccordance with approved instrument approach procedures that are retrieved from the GPS equipment database The GPS equipment database must incorporate the current update cycle NOTE Not all published approaches are in the FMS database The pilot must ensure that the plann...

Page 79: ...down fix altitude protection or arrival at approach minimums in normal position to land f RNAV GPS approaches must be conducted utilizing the GPS sensor g RNP RNAV operations are not authorized except as noted in Chapter 1 of this AFM 5 If not previously defined the following default settings must be made in the SYSTEM SETUP menu of the G1000 prior to operation refer to Pilot s Guide for procedure...

Page 80: ...sia f South of 55 S latitude between longitude 120 E and 165 E Region south of Australia and New Zealand When day VFR operations are conducted in the above areas the MFD must be in a non heading up orientation 7 The fuel quantity fuel required and fuel remaining functions of the FMS are supplemental information only and must be verified by the flight crew 8 The GPS is approved for SBAS operations ...

Page 81: ...on has been determined and corrected 4 The Garmin G1000 Cockpit Reference Guide for the Diamond DA 62 P N 010 01896 or Garmin G1000 NXi Cockpit Reference Guide for the Diamond DA62 P N 010 01905 approved revision must be immediately available to the flight crew 5 ILS approachesusing the GFC700 flight directorare limitedto CategoryI approaches only 6 Autopilot maximum airspeed 185 KIAS Autopilot mi...

Page 82: ... is not permitted 2 16 8 GROUND OPERATION Take off and landing has been demonstrated on hard paved surfaces asphalt concrete etc and grass runways 2 16 9 GARMIN GWX 70 WEATHER RADAR OPERATION WARNING The Garmin GWX 70 Weather Radar System if installed must not be operated on ground except in standby mode during taxiing If the system is transmitting it may result in bodily injury if persons are wit...

Page 83: ...g cruise During all other phases of flight the sun visors must be locked in the fully upward position 2 16 11 PDF MFD CONTROL UNIT KEYPAD The PFD MFD control unit must be stowed during take off and landing all emergencies and abnormal operating procedures Page 2 44 Rev 0 11 Jan 2019 DOT approved Doc No 11 01 05 E ...

Page 84: ...IL TEMP 3 8 3 2 4 L R OIL PRES 3 10 3 2 5 L R GBOX TEMP 3 11 3 2 6 L R FUEL TEMP 3 12 3 2 7 L R FUEL PRESS 3 13 3 2 8 L R ALTN AMPS 3 13 3 2 9 L R ENG FIRE 3 14 3 2 10 L R STARTER 3 14 3 2 11 DOOR OPEN 3 15 3 3 AIRPLANE RELATED G1000 CAUTIONS 3 16 3 3 1 L R ALTN FAIL 3 16 3 4 G1000 SYSTEM WARNINGS 3 17 3 4 1 RED X YELLOW X 3 17 3 4 2 ATTITUDE FAIL 3 17 3 4 3 AIRSPEED FAIL 3 17 3 4 4 ALTITUDE FAIL ...

Page 85: ...SECURING FEATHERING PROCEDURE 3 29 3 7 4 UNFEATHERING RESTARTING THE ENGINE IN FLIGHT 3 30 3 7 5 ENGINE FAILURE DURING TAKE OFF 3 34 3 7 6 ENGINE FAILURES IN FLIGHT 3 37 3 7 7 LANDING WITH ONE ENGINE INOPERATIVE 3 39 3 7 8 GO AROUND BALKED LANDING WITH ONE ENGINE INOPERATIVE 3 42 3 7 9 FLIGHT WITH ONE ENGINE INOPERATIVE 3 45 3 8 ENGINES OUT LANDING 3 47 3 9 DITCHING 3 49 3 10 LANDING GEAR SYSTEM F...

Page 86: ...62 3 13 OTHER EMERGENCIES 3 63 3 13 1 SUSPICION OF CONTAMINATION IN THE CABIN CARBON MONOXIDE COOLANT LIQUID ODOUR OR VAPOR 3 63 3 13 2 UNLOCKED DOORS 3 64 3 13 3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM 3 66 3 13 4 UNINTENTIONAL FLIGHT INTO ICING 3 69 3 13 5 FUEL SUPPLY FAILURE 3 70 3 13 6 RECOVERY FROM AN UNINTENTIONAL SPIN 3 71 3 13 7 EMERGENCY DESCENT 3 72 3 13 8 EMERGENCY EXIT 3 72 3 13 9 AU...

Page 87: ...horough understanding of the airplane by the pilot is in addition to his knowledge and experience an essential factor for the solution of any problems which may arise WARNING In each emergency control over the flight attitude and the preparation of a possible emergency landing have priority over attempts to solve the current problem first fly the airplane Prior to the flight the pilot must conside...

Page 88: ...r best rate of climb vYSE 87 KIAS up to 1999 kg 4407 lb 89 KIAS above 1999 kg 4407 lb 3 1 3 SELECTING EMERGENCY FREQUENCY In an in flight emergency depressing and holding the Com transfer button º on the G1000 for 2 seconds will tune the emergency frequency of 121 500 MHz If the display is available it will also show it in the Active frequency window Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 5 ...

Page 89: ...P Left Right engine coolant temperature is in the upper red range too high above 100 C Coolant temperatures above the limit value of 100 C can lead to a total loss of power due to engine failure Check G1000 for L R COOL LVL caution message low coolant level L R COOL LVL caution message not displayed During climb Reduce power on affected engine by 10 or more as required Increase airspeed by 10 KIAS...

Page 90: ...ature s This might not be the case if the coolant temperature does not return to the green range In this case perform a precautionary landing on the nearest suitable airfield Prepare for an engine failure in accordance with 3 7 6 ENGINE FAILURES IN FLIGHT END OF CHECKLIST L R COOL LVL caution message displayed Reduce power on affected engine Expect loss of coolant WARNING A further increase in coo...

Page 91: ...failure Check oil pressure If the oil pressure is outside of the green range lower limit Reduce power on affected engine Expect loss of engine oil WARNING A further increase in oil temperature must be expected Prepare for an engine failure in accordance with 3 7 6 ENGINE FAILURES IN FLIGHT If the oil pressure is within the green range Reduce power on affected engine Increase airspeed CONTINUED Pag...

Page 92: ... engine oil system and that the above mentioned procedure can decrease the temperature s This might not be the case if the oil temperature does not return to the green range In this case perform a precautionary landing on the nearest suitable airfield Prepare for an engine failure in accordance with 3 7 6 ENGINE FAILURES IN FLIGHT END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 9 ...

Page 93: ...Oil pressures below the limit value of 0 9 bar can lead to a total loss of power due to engine failure Reduce power on affected engine Expect loss of oil WARNING Land at the nearest suitable airfield Prepare for an engine failure in accordance with 3 7 6 ENGINE FAILURES IN FLIGHT END OF CHECKLIST Page 3 10 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 94: ...h ambient temperature conditions and or at low airspeeds with high power settings it can be assumed that there isno technical defect in the gearbox and that the above mentioned procedure will decrease the temperature s This might not be the case if the gearbox temperature does not return to the green range In this case perform a precautionarylandingonthenearest suitableairfield Prepare for an engi...

Page 95: ...and or at low airspeeds with high power settings and low fuel quantities it can be assumed that the above mentioned procedure will decrease the temperature s If the fuel temperature does not returntothegreenrange perform a precautionarylanding on the nearest suitable airfield NOTE Increased fueltemperature may occur when the fuel quantity in the main tank is low If the auxiliary tank is installed ...

Page 96: ...EL SELECTOR of affected engine CROSSFEED if L R FUEL PRESS warning still remains WARNING Imminent engine failure must be expected Prepare for an engine failure in accordance with 3 7 6 ENGINE FAILURE IN FLIGHT END OF CHECKLIST 3 2 8 L R ALTN AMPS L R ALTN AMPS Left Right engine alternator output is in the upper red range too high above 70 A Proceed according to 3 10 2 HIGH CURRENT END OF CHECKLIST...

Page 97: ... severe structural damage Proceed according to the following procedures as applicable 3 11 1 ENGINE FIRE ON GROUND 3 11 2 ENGINE FIRE DURING TAKE OFF 3 11 3 ENGINE FIRE IN FLIGHT END OF CHECKLIST 3 2 10 L R STARTER L R STARTER Left Right engine starter is engaged Proceed according to 3 10 3 STARTER MALFUNCTION END OF CHECKLIST Page 3 14 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 98: ...eft Right door is not closed and locked REAR DOOR OPEN Rear door is not closed and locked FWD DOOR OPEN Left or right baggage door is are not closed and locked Proceed according to 3 12 2 UNLOCKED DOORS END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 15 ...

Page 99: ...f both alternators fail at the same time reduce all electrical equipment to a minimum Expect battery power to last 30 minutesand land the airplane assoon aspossible Expect engine stoppage after this period of time 1 AVIONICS MASTER OFF 2 LH RH Alternator OFF 3 XPDR STBY 4 LANDING GEAR down when down and locked pull Emergency Release 5 Stall Pitot Static Heat OFF 6 All lights OFF END OF CHECKLIST P...

Page 100: ...ver the attitude area Revert to the standby attitude indicator part of the Standby Attitude Module 3 4 3 AIRSPEED FAIL AIRSPEED FAIL The display system is not receiving airspeed input from the air data computer accompanied by a red X through the airspeed display Revert to the standby airspeed indicator part of the Standby Attitude Module 3 4 4 ALTITUDE FAIL ALTITUDE FAIL The display system is not ...

Page 101: ...ccompanied by a red or yellow X through the vertical speed display Determine vertical speed based on the change of altitude information 3 4 6 HDG HDG The display system is not receiving valid heading input from the AHRS accompanied by a red X through the digital heading display Revert to the emergency compass Page 3 18 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 102: ...have automatically entered reversionary mode use the following procedure a DISPLAY BACKUP button on audio panel PUSH button will be OUT NOTE After automatic entry of reversionary mode the pilot must presstheDISPLAYBACKUPbuttononthe audio panel After the DISPLAY BACKUP button has been pushed the system will remain in reversionary mode even if the problem causing the automatic entry of reversionary ...

Page 103: ...3 AHRS FAILURE NOTE A failure of the Attitude and Heading Reference System AHRS is indicated by a removal of the sky ground presentation and a red X and a yellow AHRS FAILURE shown on the PFD The digital heading presentation will be replaced with a yellow HDG and the compass rose digits will be removed The course pointer will indicate straight up and course may be set using the digital window 1 Us...

Page 104: ...meter is indicated by a red or yellow X through the data field Erroneous information may be identifiedbyindications which do not agree with othersystem information Erroneous indications may be determined by comparing a display with other displays and other system information 1 Set power based on power lever position engine noise and speed 2 Monitor other indications to determine the health of the ...

Page 105: ...nnunciator appears treat it as if the condition exists Refer to Chapter 3 EMERGENCY PROCEDURES or Chapter 4B ABNORMAL OPERATING PROCEDURES 2 If a display indicates an abnormal condition but no annunciator is present use other systeminformation suchasengine displays GPS fuelquantityand flowtodetermine if the condition exists If it cannot be determined that the condition does not exist treat the sit...

Page 106: ...gency Procedures 3 6 ABNORMAL ENGINE BEHAVIOUR 1 Full power apply If the abnormal engine behavior sustains refer to 3 7 ONE ENGINE INOPERATIVE PROCEDURES END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 23 ...

Page 107: ...tion ambient conditions speed and pilot skill negative climb performance may result Refer to Chapter 5 PERFORMANCE forone engine inoperative performance data In any event the sudden application of power during one engineinoperativeoperation makesthe controloftheairplane more difficult Page 3 24 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 108: ...rectionalcontrolbymainly rudder and additional aileron input The following mnemonic can help to identify the failed engine Dead foot dead engine This means that once directional control is re established the pilot can feel the control force on the foot pushing the rudder pedal on the side of the operative engine while the foot on the side of the failed engine feels no force Further the engine inst...

Page 109: ...U A and ECU B Cautions Appear Simultaneous if the indicated LOAD remains unchanged and if the perceived thrust is reduced and if the engine noise level changes or the engine is running rough 1 POWER lever IDLE for 1 second 2 POWER lever slowly increase to 1975 RPM If the engine shows a power loss during the POWER lever increases 3 POWER lever IDLE for 1 second 4 POWER lever slowly increase stop pr...

Page 110: ...975 RPM 5 Land at the next suitable airfield Otherwise NOTE If the loss of power was due to unintentional setting of the POWER lever you may adjust the friction lock and continue flight Depending on the situation the following attempts can be made to restore normal engine operation 1 Circuit breakers check reset if necessary If normal engine operation is restored continue flight and land as soon a...

Page 111: ...f normal engine operation is restored continue flight Remain within maximum allowable lateral imbalance Otherwise 5 FUEL SELECTOR of affected engine ON CROSSFEED as required above 10000 ft turn LH RH FUEL PUMP to ON before crossfeed operation 6 ALTERNATE AIR OPEN 7 POWER lever of affected engine apply power as required If normal engine operation is restored continue flight and land as soon as prac...

Page 112: ...ternator affected engine OFF 4 Fuel pump check OFF 5 FUEL SELECTOR affected engine OFF NOTE The remaining fuel in the tank of the secured engine can be used for the remaining engine to extend range and maintain lateral balance by setting the FUEL SELECTOR of the remaining engine in the CROSSFEED position If one of the POWER levers is set to low settings the landing gear warning horn is activated S...

Page 113: ... software VC33_2P_05_19 or later approved software is installed 15 000 ft pressure altitude for immediate restarts Up to 10 000 ft pressure altitude OAT Max engine OFF time C F minutes below 15 below 5 2 15 to 5 5 to 23 5 above 5 above 23 10 Maximum restart airspeed max 80 KIAS or airspeed for a stationary propeller whichever is lower WARNING VMCA is 76 KIAS and should be considered when attemptin...

Page 114: ...WER lever of affected engine IDLE 2 FUEL SELECTOR of affected engine check ON 3 Alternate air as required 4 ALTERNATOR of affected engine ON 5 ENGINE MASTER of affected engine ON propeller un feathers 6 STARTER of affected engine engage when propeller is stationary CAUTION After the engine has started the POWER lever should be set to a moderate power setting until engine temperatures have reached ...

Page 115: ...titude for restarts within two minutes If MÄM 62 168 engine software VC33_2P_05_19 or later approved software is installed 15 000 ft pressure altitude for immediate restarts Up to 10 000 ft pressure altitude OAT Max engine OFF time C F minutes below 15 below 5 2 15 to 5 5 to 23 5 above 5 above 23 10 Minimum restart airspeed 110 KIAS below 10 000 ft pressure altitude 100 KIAS above 10 000 ft pressu...

Page 116: ...llermaynot windmill continuously Continuous windmilling is required for a successful restart Above 115 KIAS a restart can overspeed the propeller 1 POWER lever of affected engine IDLE 2 FUEL SELECTOR of affected engine check ON 3 Alternate air as required 4 ALTERNATOR of affected engine ON 5 ENGINE MASTER of affected engine ON propeller un feathers and restarts by windmilling CAUTION After the eng...

Page 117: ...ver IDLE BOTH 2 Rudder maintain directional control 3 Brakes as required CAUTION If sufficient time is remaining the risk of fire in the event of a collision with obstacles can be reduced as follows 4 ENGINE MASTER both OFF 5 FUEL SELECTOR both OFF 6 ELECT MASTER OFF END OF CHECKLIST Page 3 34 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 118: ...ontinued take off is not recommended if the steady rate of climb according to Section 5 3 8 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE is less than 3 3 Under certain combinations of ambient conditions such as turbulence crosswinds and wind shear as well as pilot skill the resulting climb performance may nevertheless be insufficient to continue the take off successfully Therefore a continued take off...

Page 119: ... to achieve a positive ROC 5 FLAPS check UP 6 Inoperative engine secureaccordingto 3 7 3 ENGINE SECURING FEATHERING PROCEDURE Land as soon as possible according to 3 7 7 LANDING WITH ONE ENGINE INOPERATIVE If a diversion is required before landing continue according to Section 3 7 9 FLIGHT WITH ONE ENGINE INOPERATIVE END OF CHECKLIST Page 3 36 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 120: ...udder maintain directional control 2 Airspeed vYSE 87 KIAS up to 1999 kg 4407 lb 89 KIAS above 1999 kg 4407 lb 3 Operative engine increasepowerasrequiredif directional control has been established Establish minimum zero sideslip condition approx half ball towards good engine 3 to 5 bank 4 Inoperative engine Secureaccordingto3 7 3 ENGINE SECURING FEATHERING PROCEDURE Land as soon as possible accord...

Page 121: ...stablish minimum zero sideslip condition approx half ball towards good engine 3 to 5 bank 4 Inoperative engine Secureaccordingto3 7 3 ENGINE SECURING FEATHERING PROCEDURE Land as soon as possible according to 3 7 7 LANDING WITH ONE ENGINE INOPERATIVE If a diversion is required before landing continue according to Section 3 7 9 FLIGHT WITH ONE ENGINE INOPERATIVE END OF CHECKLIST Page 3 38 Rev 0 11 ...

Page 122: ...ght position described by a placard on the roll over bar and verify proper fixation 2 Safety harnesses check fastened and tightened 3 Landing light as required 4 Gear warning horn check function Operative engine 5 Fuel pump remaining engine ON 6 FUEL SELECTOR check ON Inoperative engine 7 Engine checksecured feathered according to 3 7 3 ENGINE SECURING FEATHERING PROCEDURE CONTINUED Doc No 11 01 0...

Page 123: ...G above 1999 kg 4407 lb 95 KIAS vREF FLAPS UP 91 KIAS vREF FLAPS T O 89 KIAS vREF FLAPS LDG WARNING One engine inoperative approaches for landing with flap settings of more than flaps UP are not recommended unless a safe landing is assured Making the field Higher flap settings increase the loss of altitude during the transition to a one engine inoperative go around balked landing 14 POWER lever as...

Page 124: ...cantly longer landing distance during flare CAUTION In conditionssuch as e g strongwind dangerof wind shear or turbulence a higher approach speed should be selected Perform normal touchdown and deceleration on ground END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 41 ...

Page 125: ...n combinations of ambient conditions such as turbulence cross wind and windshear as well as pilot skill the resulting climb performance may nevertheless be insufficient for a successful go around balked landing 1 POWER lever MAX 2 Initial pitch attitude 6 UP 3 Rudder maintaindirectionalcontrolmaintain 4 Airspeed vYSE 87 KIAS up to 1999 kg 4407 lb 89 KIAS above 1999 kg 4407 lb 5 Landing gear UP 6 F...

Page 126: ... the flaps to LDG will increase drag and incur a high sink rate Only when the landing area can be reached safely landing with flaps LDG is advisable NOTE If landing is performed off airfield depending on the surface condition it may be beneficial to land with the gear UP Note that the energy absorbing function of the landing gear is lost in such cases 9 Approach speed up to 1999 kg 4407 lb min 88 ...

Page 127: ... MASTER OFF 13 Touch down lowest practical speed If landing with landing gear retracted 11 LANDING GEAR UP 12 Touch down lowest practical speed Immediately after touch down 14 ELECT MASTER OFF NOTE If the ELECT MASTER is switched OFF before touchdown the landing gear will extend slowly END OF CHECKLIST Page 3 44 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 128: ...ised by LOW FUEL indication on the G1000 In this case return to coordinated flight or use CROSSFEED on the affected engine 1 Airspeed as required above vYSE 87 KIAS up to 1999 kg 4407 lb 89 KIAS above 1999 kg 4407 lb 2 Remaining engine monitor engine instruments continuously 3 Fuel quantity monitor continuously 4 FUEL SELECTOR remaining engine set CROSSFEED above 10000 ft turn LH RH FUEL PUMP to O...

Page 129: ...e supplied with fuel from the main tank on the opposite side This will extend range and helps to keep the wings laterally balanced see 2 14 FUEL Land as soon as possible according to Section 3 7 7 LANDING WITH ONE ENGINE INOPERATIVE END OF CHECKLIST Page 3 46 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 130: ...LDG will increase drag and incur a high sink rate Only when the landing area can be reached safely landing with flaps LDG is advisable NOTE If landing is performed off airfield depending on the surface condition it may be beneficial to land with the gear UP Note that the energy absorbing function of the landing gear is lost in such cases 8 Approach speed up to 1999 kg 4407 lb min 88 KIAS flaps T O...

Page 131: ...k 3 green 11 POWER lever both IDLE 12 ELECT MASTER OFF 13 Touch down lowest practical speed If landing with landing gear retracted 10 LANDING GEAR UP 11 POWER lever both IDLE 12 Touch down lowest practical speed Immediately after touch down 14 ELECT MASTER OFF END OF CHECKLIST Page 3 48 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 132: ...REF 89 KIAS above 1999 kg 5 POWER 300 ft min rate of descent 6 Touchdown level attitude NOTE Avoid a landing flare because of difficulty in judging height over a water surface It isexpectedthat the airplane mayskip clear of the water once ortwice using the technique outlined On final contact with the water surface the airplane will experienceseveralsecondsof moderateabruptdeceleration and then wil...

Page 133: ...n of this light is therefore normal during transit If thelight remainson forlongerthan 20 secondsduring landinggearretraction extension 1 Airspeed check below vLOR 162 KIAS 2 Gear selector re cycle if continued illumination occurs If the landing gear cannot be extended to the down locked position or red light does not extinguish Continue with 3 9 2 MANUAL EXTENSION OF THE LANDING GEAR CONTINUED Pa...

Page 134: ...ed fuel consumption and decreased range With the landing gear extendedandataft CG locations with flaps up and full power applied the airplane will easily recover from sideslip if the trim is set to neutral normal procedure Otherwise it may require corrective action with a moderate amount of rudder input In cold ambient temperatures it may help to reduce the airspeed below 110 KIAS for landing gear...

Page 135: ...ELECT MASTER check ON 3 Bus voltage check in normal range 4 Circuit breaker check in reset if necessary Manual landing gear extension procedure 5 Gear selector select DOWN 6 Manual gear extension handle pull out NOTE The landing gear should now extend by gravity and relief of hydraulic pressure from the system If one or more landing gearindicatorlightsdo not indicatethe geardown and locked after c...

Page 136: ...y extended and locked as indicated by the 3 green lights the red light is illuminated additionally if the GEAR circuit breaker is pulled If the landinggearcannot beextendedtothe down and locked positioncontinue according to 3 9 3 LANDING WITH GEAR UP END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 53 ...

Page 137: ...ps can help to reduce the risk of fire 3 ENGINE MASTER both OFF 4 Fuel pumps check OFF 5 FUEL SELECTOR both OFF Touchdown 6 Touchdown contact surface with minimum airspeed 7 On ground maintain directional control with rudder as long as possible so as to avoid collision with obstacles Immediately after touchdown 8 ELECT MASTER OFF NOTE If the ELECT MASTER is switched OFF before touchdown the landin...

Page 138: ...the side of the intact tire so that changes in direction which must be expected during roll out due to the braking action of the defective tire can be corrected on the runway 2 Land with one wing low The wing on the side of the intact tire should be held low 3 Direction should be maintained using the rudder This should be supported byuse of the brake It is possible that the brake must be applied s...

Page 139: ...e 1 Safety harness check fastened and tightened CAUTION If sufficient time is remaining the risk of fire in the event of a collision can be reduced asfollowsaftera safe touch down ENGINE MASTER both OFF FUEL SELECTOR both OFF ELECT MASTER OFF END OF CHECKLIST Page 3 56 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 140: ...iven position Refer to 4B 5 FAILURES IN FLAP OPERATING SYSTEM 5 Land on the nearest suitable airfield WARNING Enginestoppage may occur dependingon the failure mode Backup batteries are installed for the ECUs to provide electrical power solely to the ECU and their systems for at least 30 minutes NOTE The landing gear uplock is no longer ensured The landing gear may slowly extend The landing gear ca...

Page 141: ...ule Engine power can be set via visual reference of the POWER lever position END OF CHECKLIST 3 11 2 HIGH CURRENT If high current is indicated on the G1000 1 Circuit breakers check 2 Reduce electric load to minimum required for continued safe flight 3 Land on the nearest suitable airfield END OF CHECKLIST Page 3 58 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 142: ... field illuminates aftertheengine hasstarted On Ground 1 POWER lever affected engine IDLE 2 ENGINE MASTER affected engine OFF 3 ELECT MASTER OFF Terminate flight preparation In flight Refer to 3 7 4 UNFEATHERING RESTARTING THE ENGINE IN FLIGHT If restart is not successful Refer to 3 7 9 FLIGHT WITH ONE ENGINE INOPERATIVE END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 59 ...

Page 143: ... bracket it is necessary to catch the bottle at the agent outlet nozzle near the Y spring 3 12 1 ENGINE FIRE ON GROUND 1 ENGINE MASTER both OFF 2 FUEL SELECTOR both OFF 3 ELECT MASTER OFF After standstill 4 Doors open 5 Airplane evacuate immediately END OF CHECKLIST 3 12 2 ENGINE FIRE DURING TAKE OFF 1 Cabin heat Defrost OFF Proceed according to 3 7 5 ENGINE FAILURES DURING TAKE OFF END OF CHECKLI...

Page 144: ...e engine according to 3 7 3 ENGINE SECURING FEATHERING PROCEDURE END OF CHECKLIST 3 12 4 ELECTRICAL FIRE ON GROUND 1 ELECT MASTER OFF If the engine is running 2 POWER lever both IDLE 3 ENGINE MASTER both OFF 4 FUEL SELECTOR both OFF When the engine has stopped after standstill 5 Doors open 6 Airplane evacuate immediately END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 61 ...

Page 145: ...f required 5 Land on the next suitable airfield CAUTION Switching OFF the ELECT MASTER will lead to total failure of all electronic and electric equipment The attitude and heading reference system AHRS will also be affected However theinternalbatterywillsupplypowertothe standby attitude module END OF CHECKLIST Page 3 62 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 146: ... gases is noticed in the cabin the following measures should be taken 1 Cabin heat Defrost OFF 2 Ventilation open 3 Emergency windows open END OF CHECKLIST Coolant Liquid Odour or Vapor Coolant liquid odour or vapor can enter the airplane cabin through the heating system in case a coolant radiator is leaking due to damage Coolant liquid odour or vapor is harmful to health and has a product specifi...

Page 147: ...F CHECKLIST Passenger Door Unlocked 1 Airspeed below 140 KIAS 2 Land on the next suitable airfield WARNING Do not try to lock the passenger door in flight The safety latch maydisengage and the door opens Usuallythisresults in a separation of the door from the airplane NOTE If a door has been lost the airplane can be safely flown to the next suitable airfield END OF CHECKLIST Page 3 64 Rev 0 11 Jan...

Page 148: ...n 1 Airspeed reduce so that door is in a stable position 2 Land on the next suitable airfield WARNING Separation of the baggage door may damage the propeller and may lead to an engine failure END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 65 ...

Page 149: ... case of a malfunction of the engine control unit it is possible that the propeller blades will remain in the position of highest pitch In thiscase the reduced engine performance should be taken into consideration a Oscillating RPM 1 POWER setting change If the problem does not clear 2 Garmin G1000 check L R ECU A B FAIL caution If L R ECU A FAIL indicated 3 VOTER switch ECU B If L R ECU B FAIL in...

Page 150: ...a engine control unit malfunction 1 POWER setting reduce as required If the problem does not clear 2 Garmin G1000 check L R ECU A B FAIL caution If L R ECU A FAIL indicated 3 VOTER switch ECU B If L R ECU B FAIL indicated 3 VOTER switch ECU A CAUTION If the problem does not clear itself switch back to AUTO and land on the nearest suitable airfield Prepare for engine malfunction according to 3 7 6 ...

Page 151: ...in G1000 check L R ECU A B FAIL caution If L R ECU A FAIL indicated 3 VOTER switch ECU B If L R ECU B FAIL indicated 3 VOTER switch ECU A NOTE If the problem does not clear itself switch back to AUTO and land on the nearest suitable airfield END OF CHECKLIST Page 3 68 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 152: ... Cabin heat Defrost ON 4 POWER lever increase power in order to prevent ice build up on thepropellerblades apply power changes periodically 5 ALTERNATE AIR OPEN 6 Emergency windows open if required CAUTION Ice build up increases the stalling speed 7 ATC advise if an emergencyisexpected END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 3 69 ...

Page 153: ... crossfeed operation WARNING In case of a fuel supply failure a fuel pump inspection is required prior to the next flight 2 Fuel quantity monitor 3 Fuel pump of affected engine ON If fuel supply failure remains 4 FUEL SELECTOR ON 5 Fuel pump of affected engine ON 6 Fuel quantity monitor END OF CHECKLIST Page 3 70 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 154: ...red unintentionally immediate recovery actions must be taken CAUTION Steps 1 to 4 must be carried out immediately and simultaneously 1 POWER lever IDLE 2 Rudder fulldeflectionagainstdirectionofspin 3 Elevator control stick fully forward 4 Ailerons neutral 5 FLAPS UP When rotation has stopped 6 Rudder neutral 7 Elevator control stick pull carefully 8 Return the airplane from a descending into a nor...

Page 155: ... as exit In case the doors are blocked the egress hammer may be used to break through the door windows If OÄM 62 019 is installed a maximum of seven seats may be installed In case of an emergency the passengers on passenger row I must exit the airplane first The LH seat backrest of passenger row I can be released by pulling the red emergency handle on the backside of the seat pan The released back...

Page 156: ... AP indication on the PFD or a yellowCHECK ATTITUDEonthe 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 flashing on the PFD may not cause the autopilot to disconnect Be alert to possible autopilot out of trim conditions see AUTOPILOT OUT OF TRIM procedure below and expect resid...

Page 157: ...4 AFCS ESP USP circuit breaker pull 5 AP DISC switch RELEASE NOTE When the AFCS ESP USP circuit breaker is pulled the manual electric trim and autopilot autotrim systems will be disabled WARNING Do not attempt to re engage the autopilot following an autopilot autotrim or manual electric trim malfunction until the cause for the malfunction has been corrected END OF CHECKLIST Page 3 74 Rev 0 11 Jan ...

Page 158: ...N 4A 5 4A 4 FLIGHT CHARACTERISTICS 4A 6 4A 5 DAILY CHECK 4A 6 4A 6 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4A 7 4A 6 1 PRE FLIGHT INSPECTION 4A 7 4A 6 2 BEFORE STARTING ENGINE 4A 19 4A 6 3 STARTING ENGINE 4A 22 4A 6 4 BEFORE TAXIING 4A 24 4A 6 5 TAXIING 4A 26 4A 6 6 BEFORE TAKE OFF 4A 27 4A 6 7 TAKE OFF 4A 35 4A 6 8 CLIMB 4A 38 4A 6 9 CRUISE 4A 44 4A 6 10 DESCENT 4A 50 4A 6 11 APPROACH LANDING ...

Page 159: ... EXIT AIRPLANE 4A 64 4A 6 16 POST FLIGHT INSPECTION 4A 64 4A 6 17 PARKING 4A 64 4A 6 18 FLIGHT IN RAIN 4A 65 4A 6 19 REFUELING 4A 65 4A 6 20 FLIGHT AT HIGH ALTITUDE 4A 69 4A 6 21 DEMONSTRATION OF ENGINE SHUTDOWN RESTART 4A 69 Page 4A 2 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 160: ... procedures for GFC 700 are described in the Garmin G1000 Cockpit Reference Guide P N 190 01896 00 or later and the Garmin G1000 Pilot s Guide for the Diamond DA 62 P N 190 01895 00 or later If MÄM 62 254 is installed normal operating procedures for GFC 700 are described in the Garmin G1000 NXi Cockpit Reference Guide P N190 01905 00 orlater and the Garmin G1000 NXi Pilot s Guide for the Diamond D...

Page 161: ...te of climb vY UP 87 89 T O 83 86 Airspeed for cruise climb UP min 93 min 96 Reference landing approach speed UP 91 95 T O min 88 min 91 Final approach speed LDG min 84 min 89 Minimum speed during go around UP min 91 min 95 Max structural cruising speed Do not exceed this speed except in smooth air and then only with caution UP 162 162 Safe intentional one engine inoperative speed VSSE a minimum s...

Page 162: ...eft Right engine glow plug active 4A 3 3 PFD MFD GIA FAN FAIL PFD FAN FAIL Cooling fan for the PFD is inoperative MFD FAN FAIL Cooling fan for the MFD is inoperative GIA FAN FAIL Cooling fan for the GIA is inoperative The flight may be continued but maintenance action is required after landing 4A 3 4 L R AUXPUMP ON L R AUXPUMP ON Fuel transfer from auxiliary to main tank is in progress if installe...

Page 163: ...rrective action with a moderate amount of rudder input 4A 5 DAILY CHECK Before the first flight of a day it must be ensured that the following checks are performed On condition check of the LH and RH pilot door the passenger door and the baggage compartment doors for cracks and major scratches On condition check of the hinges for the LH and RH pilot door the passenger door and the baggage compartm...

Page 164: ...n e Baggage stowed and secured f Foreign objects check g Emergency equipment egress hammer first aid kit fire extinguisher belt cutter if OÄM 62 019 is installed and equipment necessary by national operation rules stowed and secured Center console a FUEL SELECTORS check ON b POWER levers checkcondition freedomof movement and full travel adjust friction set IDLE Below instrument panel in front of l...

Page 165: ...SELECTOR check UP h Circuit breakers set in if one has been pulled check reason i All electrical equipment OFF j ELT armed Check procedure a ELECT MASTER ON CAUTION When switching the ELECT MASTER ON the electrically driven hydraulic gear pump may activate itself for 5 to 20 seconds in order to restore the system pressure Should the pump continue to operate continuously or periodically terminate f...

Page 166: ... function e Stall warning stall heat Pitot heat static port heat check NOTE Because the stall warning switch gets slightly warmer on ground STAL HT FAIL may be indicated on the PFD f Gear warning fire detector TEST BUTTON PUSH check aural alert fire detectionwarningandauralalertand CHECK GEAR caution CAUTION If the aural alert or the warning on the PFD does not appear terminate flight Unscheduled ...

Page 167: ...s DA 62 AFM g ELECT MASTER OFF h Flight controls check free and correct movement up to full deflection i Trims check free and correct movement up to full deflection END OF CHECKLIST Page 4A 10 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 168: ...d de icing fluids refer to Section 8 7 GROUND DE ICING CAUTION Prior to flight remove such items as control surfaces gust lock Pitot cover tow bar etc 1 Left main landing gear a Landing gear strut and lock visual inspection sufficient height typical visible length of bare piston at least 5 cm 2 0 in b Down and uplock switches 2 pieces visual inspection c Wear tread depth of tire visual inspection ...

Page 169: ...r water and sediment drain until no water comes out clear f Venting pipe check for blockage g Exhaust visual inspection WARNING The exhaust can cause burns when hot h Propeller visual inspection WARNING Never move the propeller by hand while the ENGINE MASTER switch is ON Also do not move the propeller by hand while the ENGINE MASTER is OFF immediately after operation remaining pressure in the inj...

Page 170: ...spection c Tank drain tank air inlet drain off to check for water and sediment drain until no water comes out visual inspection d Openings on lower surface check for foreign objects and for traces of fuel if tank is full fuel may spill over through the tank vent e Stall warn device visual inspection f Tank filler visual inspection check closed g Pitot probe clean orifices clear cover removed no de...

Page 171: ... LH Pilot door visual inspection b Passenger door window visual inspection c Fuselage skin visual inspection d Antennas visual inspection e Fuselage check for contamination hydraulic fluid f Static source check for blockage 5 Empennage a Stabilizers and control surfaces elevator tips visual inspection b Hinges visual inspection c Elevator trim tab visual inspection check safetying d Rudder trim ta...

Page 172: ... 0 in b Down and uplock switches 2 pieces visual inspection c Wear tread depth of tire visual inspection d Tire wheel brake visual inspection e Brake line connection check for leaks f Slip marks visual inspection g Chocks remove h Landing gear door visual inspection 8 Right wing a Entire wing surface visual inspection b Tank air outlet on lower surface visual inspection c Tank drain tank air inlet...

Page 173: ...nges and safety pin visual inspection m Foreign objects in aileron paddle visual inspection n Flap and linkage covers visual inspection o Flap hinges and safety pin visual inspection p Nacelle underside visual inspection q Step visual inspection r Cabin vent air inlet check clear 9 Right engine nacelle a 3 air inlets 2 air outlets clear b Engine oil level check dipstick inspection hole in the side...

Page 174: ...hile the ENGINE MASTER is OFF immediately after operation remaining pressure in the injection system rail Serious personal injury may result i Nacelle underside check for excessive contamination particularly by oil fuel and other fluids j Auxiliary tank drain if installed drain off to check for water and sediment drain until no water comes out visual inspection k Auxiliary tank filler if installed...

Page 175: ...ches visual inspection d Wear tread depth of tire check e Slip marks visual inspection f Gear door and linkage visual inspection g If OÄM 62 009 is installed Nose cone surface visual inspection h If OÄM 62 009 is installed Nose cone attachment screws visual inspection i If OÄM 62 009 is installed Nose cone lightning protection strips visual inspection j Chocks remove k OAT sensor check l EPU conne...

Page 176: ...their placarding and the ban on smoking 3 Passenger door closed and locked CAUTION When operating the doors pilots operatorsmust ensure that there are no obstructions between the doors and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward inward pressure on the doors may be required to ease the handle operation CAUTION...

Page 177: ... IDLE 8 Parking brake set CAUTION If the provisions for tablet mounts are installed on the LH and RHA column OÄM62 033isinstalled andatablet computer is used the pilot must ensure that the mount is adjusted to not interfere with the cockpit controls to provide sufficient view outside and sufficient view for the instruments and to not interfere with the control sticks in any position 9 AVIONIC MAST...

Page 178: ...ystem pressure Should the pump continue to operate continuously or periodically terminate flight preparation There is a malfunction in the landing gear system 15 G1000 wait until power up completed Press ENT on MFD to acknowledge NOTE The engine instruments are only available on the MFD after item 16 has been completed 16 Fuel temperature check END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 ...

Page 179: ...Annunciations check L ENGINE GLOW ON NOTE L ENGINE GLOW isindicated onlywhen theengine is cold 4 Annunciations Engine System Page check OK normal range WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered After the L ENGINE GLOW indication is extinguished 5 START LEFT button PRESS as required release when engine has started CONTI...

Page 180: ... started and the START push button has been released set the ENGINE MASTER to OFF and investigate the problem 6 Annunciations Engine System Page check OK normal range 7 Annunciations Starter check OFF 8 Annunciations Oil pressure check OK WARNING If the oil pressure has not moved from the red range within 3 seconds after starting set the ENGINE MASTER switch to OFF and investigate problem 9 Circui...

Page 181: ...ing switch gets slightly warmer on ground only and STAL HT FAIL is indicated on the PFD 7 Pitot and stall warn heating OFF 8 Strobe lights ACLs check ON 9 Position lights landing and taxi lights as required CAUTION When taxiingat close range to otherairplanes orduringnight flight in clouds fog or haze the strobe lights should be switched OFF The position lights must always be switched ON during ni...

Page 182: ...t tone sounds If AFCS annunciation remains on or a failure of the preflight test is indicated terminate flight preparation and investigate the problem 12 MANUAL ELECTRIC TRIM TEST as follows Press the AP DISC button down and hold while commanding trim Manual electric trim should not operate either nose up or nose down 13 AUTOPILOT engage by pressing AP button 14 AP DISC switch press Verify that th...

Page 183: ...Thefuelcrossfeedfunctioncanbetested simultaneouslywith both engines Proper function can be tested by running the engines forapprox 30secondswithCROSSFEED selected The operation of both engineswithboth FUEL SELECTORS in CROSSFEEDposition otherthan forthistest isprohibited 7 FUEL SELECTOR ON LH RH CAUTION When taxiing on a poor surface select the lowest possible RPM to avoid damage to the propeller ...

Page 184: ...r check closed and locked CAUTION When operatingthe doors pilots operators must ensure that there are no obstructions between the doors and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward inward pressure on the doors may be required to ease the handle operation 6 LH RH Pilot doors closed and locked 7 Front baggage do...

Page 185: ...Circuit breakers check pressed in 11 Longitudinal trim set T O WARNING Take off with CROSSFEED selected is prohibited 12 FUEL SELECTOR check ON LH RH 13 Directional trim centered 14 FLAPS check function indicator set T O 15 Flight controls unrestricted free movement correct sense 16 PITOT HEAT ON if required 17 Landing light ON if required CONTINUED Page 4A 28 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 186: ...herefore the parking brake must be set A Under 7500 ft CAUTION If the L R ECU A B FAIL indicators do not illuminate during the test sequence there is a malfunction in the engine control system Terminate flight preparation The whole test procedure must be completed without any error L R ECU A B FAIL extinguished after test completion In casethe testprocedure aborts with an error indication one or b...

Page 187: ... Propeller RPM check below 1000 rpm 3 Fuel pumps check OFF NOTE By switching between ECU A and B the two independent electrical fuel pumps are switched over as well 4 VOTER switch ECU A 5 Engine check running without a change shake may occur 6 VOTER switch AUTO 7 Engine check running without a change shake may occur 8 VOTER switch ECU B 9 Engine check running without a change shake may occur 10 VO...

Page 188: ...n the following sequence ECU A B FAIL lights ON Propeller RPM increase above 1800 rpm Propeller RPM decrease Propeller RPM increase above 1800 rpm Propeller RPM decrease to idle At this point the test transfers from one ECU channel to the other Propeller RPM increase above 1800 rpm Propeller RPM decrease Propeller RPM increase above 1800 rpm Propeller RPM decrease to idle At this point control of ...

Page 189: ...uments check within normal range 4 RPM stabilizes at 2250 to 2300 RPM 5 LOAD indication stabilizes at 89 to 100 CAUTION The load indications in the table below are minimum values to be indicated with the airplane stationary in no wind conditions If the engine does not stabilize at the target RPM and the required load indication terminate flight preparation CONTINUED Page 4A 32 Rev 0 11 Jan 2019 Do...

Page 190: ... green range NOTE With the power lever in IDLE the oil pressure may be in the low yellow range This is acceptable to continue flight preparation 8 Fuel pumps LH RH ON END OF CHECKLIST B Over 7500 ft In case of aircraft operation at high elevated airfields above 7500 ft below 22 65 inHg it is possible that the ECU Test will not start due to increased engine idle power In this case proceed instead o...

Page 191: ...ine check running without a change shake may occur 3 Power lever MAX 4 Propeller RPM stabilizes at 2250 to 2300 RPM 5 Load indication stabilizes at 89 to 100 see table power check 6 Power lever IDLE 7 VOTER switch ECU B 8 Engine check running without a change shake may occur 9 Power lever MAX 10 Propeller RPM stabilizes at 2250 to 2300 RPM 11 Load indication stabilizes at 89 to 100 see table power...

Page 192: ...if necessary 3 Elevator neutral 4 Rudder maintain direction NOTE In strong crosswinds steering can be augmented by use of the toe brakes It should be noted however that this method increases the take off roll and should not generally be used 5 Nose wheel lift off up to 1999 kg 4407 lb vR min 76 KIAS above 1999 kg 4407 lb vR min 78 KIAS 6 Airspeed for initial climb up to 1999 kg 4407 lb min 83 KIAS...

Page 193: ...selecting gear up 8 ALTERNATE AIR OPEN in rain snow or visible moisture END OF CHECKLIST b Take off with Flaps UP 1 Transponder as required 2 POWER lever MAX NOTE The proper and symmetric performance of the engines at MAX should be checked early during the take off run so that the take off can be aborted if necessary 3 Elevator neutral 4 Rudder maintain direction CONTINUED Page 4A 36 Rev 0 11 Jan ...

Page 194: ...t off vR min 80 KIAS 6 Airspeed for initial climb up to 1999 kg 4407 lb min 87 KIAS above 1999 kg 4407 lb min 89 KIAS When safe climb is established 7 LANDING GEAR apply brakes UP check unsafe light off NOTE To avoid damage and excessive wear of the main landing gear wheels firmly apply brakes before selecting gear up 8 ALTERNATE AIR OPEN in rain snow or visible moisture END OF CHECKLIST Doc No 11...

Page 195: ...quired for en route cruise climb up to 1999 kg 4407 lb 93 KIAS above 1999 kg 4407 lb 96 KIAS 6 POWER lever up to 95 7 Trim as required ball centered 8 Annunciations Engine System Page monitor CAUTION If the oil temperature and orcoolant temperature reachesthe yellow range duringclimb flight should be continued with the airspeed increased by 10 kts and power reduced by 10 reduced climb rate for bet...

Page 196: ...ch 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 a Vertical Speed VS 1 Altitude preselect set to desired altitude 2 Mode controller select VS on mode controller 3 Vertical speed reference adjust using NOSE UP and NOSE ...

Page 197: ...descent Use engine power to maintain appropriate airplane speed If the CWS switch is used while in VS mode the VS reference will change to the vertical speed when the CWS switch is released END OF CHECKLIST b Flight Level Change FLC 1 Altitude preselect set to desired altitude 2 Mode controller select FLC on mode controller 3 Airspeed speed reference adjust using NOSE UP and NOSE DN buttons 4 Whit...

Page 198: ... maintained without deviating away from the selected altitude the system will maintain level flight until the power or reference is changed to allowclimbingordescending towardsthe selectedaltitude The FLC mode is limited to airspeeds between 90 KIAS and 185 KIAS Use engine powerto maintain appropriate vertical speed If the CWS switch is used while in FLC mode the airspeed reference willchange toth...

Page 199: ...ect armed note on PFD 5 Green ALT verify upon altitude capture NOTE In ALT mode the autopilot willmaintain 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 END OF CHECKLIS...

Page 200: ...te on PFD 6 Vertical mode and reference select on mode controller NOTE If the Course Deviation Indicator CDI 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 m...

Page 201: ...nce in the auxiliary tanks both AUX PUMP switches must be operated simultaneously 1 Transfer the first half of the auxiliary fuel As soon as the fuel quantity in each main fuel tank is 15 US gal or less set both AUX PUMP switches to ON until the main tanks are full again Monitor the fuel quantity indicatorto verifythat fuel is properlytransferred to both main fuel tanks approx 1 US gal per minute ...

Page 202: ... MFDare referencedtoairplane 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 a Vertical Speed VS 1 Altitude preselect set to desired altitude 2 Mode controlle...

Page 203: ...descent Use engine power to maintain appropriate airplane speed If the CWS switch is used while in VS mode the VS reference will change to the vertical speed when the CWS switch is released END OF CHECKLIST b Flight Level Change FLC 1 Altitude preselect set to desired altitude 2 Mode controller select FLC on mode controller 3 Airspeed speed reference adjust using NOSE UP and NOSE DN buttons 4 Whit...

Page 204: ...o allowclimbingordescending towardsthe selectedaltitude The FLC mode is limited to airspeeds between 90 KIAS and 185 KIAS Use engine powerto maintain appropriate vertical speed If the CWS switch is used while in FLC mode the airspeed reference willchange totheairspeedwhenthe CWS switch is released END OF CHECKLIST c To Capture a Selected Altitude 1 Altimeter setting adjust to appropriate value 2 A...

Page 205: ...the altimeter s barometric pressure setting If the altimeter setting is changed the autopilot will climb or descend to maintain the reference altitude END OF CHECKLIST d Altitude Hold To maintain a selected altitude 1 Altimeter setting adjust to appropriate value 2 Reaching desired altitude select ALT on mode controller 3 Green ALT verify on PFD END OF CHECKLIST Page 4A 48 Rev 0 11 Jan 2019 Doc No...

Page 206: ...te on PFD 6 Vertical mode and reference select on mode controller NOTE If the Course Deviation Indicator CDI 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 m...

Page 207: ...ce 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 a Vertical Speed VS 1 Altitude preselect set to desired altitude 2 Mode controller select VS on mode controller 3 Vertical speed reference adjust using NOSE UP and...

Page 208: ...descent Use engine power to maintain appropriate airplane speed If the CWS switch is used while in VS mode the VS reference will change to the vertical speed when the CWS switch is released END OF CHECKLIST b Flight Level Change FLC 1 Altitude preselect set to desired altitude 2 Mode controller select FLC on mode controller 3 Airspeed speed reference adjust using NOSE UP and NOSE DN buttons 4 Whit...

Page 209: ...o allowclimbingordescendingtowards the selected altitude The FLC mode is limited to airspeeds between 90 KIAS and 185 KIAS Use enginepowerto maintain appropriate vertical speed If the CWS switch is used while in FLC mode the airspeed reference willchange totheairspeedwhentheCWS switch is released END OF CHECKLIST c To Capture a Selected Altitude 1 Altimeter setting adjust to appropriate value 2 Al...

Page 210: ...e knob VOR Only 3 Intercept heading establish in HDG or ROL mode if required 4 Mode controller select NAV on mode controller 5 Green or white VOR or GPS annunciation note on PFD 6 Vertical mode and reference select on mode controller NOTE If the Course Deviation Indicator CDI 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 pil...

Page 211: ...roll over bar and verify proper fixation 2 Safety harnesses check fastened and tightened 3 Yaw damper check OFF 4 Controls no interference by foreign objects 5 Landing light as required 6 Gear warning horn check function 7 FUEL SELECTOR check both ON 8 Fuel pumps LH RH ON 9 LANDING GEAR DOWN check 3 green 10 Parking brake check released 11 Trim as required directional trim neutral CONTINUED Page 4...

Page 212: ... lever as required 15 Trim as required directional trim neutral 16 Final approach speed up to 1999 kg 4407 lb min 84 KIAS with FLAPS LDG above 1999 kg 4407 lb min 89 KIAS with FLAPS LDG NOTE Higherapproachspeedsresult in a significantlylongerlanding distance during flare CAUTION In conditions such as e g strongwind dangerof windshear or turbulence a higher approach speed should be selected END OF ...

Page 213: ...ion note on PFD 6 Vertical mode and reference select on mode controller NOTE If the Course Deviation Indicator CDI 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 headingwillresultina capture of the selected course If the CDI is one dot or less from center the autopilot will enterthe capture mode ...

Page 214: ...ontroller 5 Green or white LOC and GS annunciation note on PFD 6 Vertical mode and reference select on mode controller NOTE When the selected navigation sourceisavalidILS 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 END OF CHECKLIST...

Page 215: ...white GPS annunciation note on PFD 6 Vertical mode and reference select on mode controller END OF CHECKLIST d Back Course BC 1 Navigation source select LOC using CDI button on PFD 2 Course bearing pointer set to ILS front Course using course knob 3 Intercept heading establish in HDG or ROL mode if required 4 Mode controller select NAV on mode controller 5 Green or white BC annunciation note on PFD...

Page 216: ...eticheadingbefore BCwillbeannunciated in the lateral mode field Until that point LOC will be annunciated SelectingNAV mode for back course approaches inhibitsthe glideslope from coupling 6 Vertical mode and reference select on mode controller END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4A 59 ...

Page 217: ...afe light off 5 FLAPS retract position UP When a safe climb is established 6 Fuel pumps LH RH OFF END OF CHECKLIST GFC 700 Operation During Go Around 1 Control stick GRASP FIRMLY 2 GA button PUSH verify GA GA on PFD in lateral and vertical mode fields NOTE After the GA button is pressed the autopilot disconnects if ESPisnot installed and the flight director indicates a 6 pitch up attitude CONTINUE...

Page 218: ...mode on controller 7 Autopilot RE ENGAGE if desired NOTE If the missed approach procedure requires tracking the localizeroutbound from the airport use NAVmode to prevent inadvertent coupling to glideslope END OF CHECKLIST 4A 6 13 AFTER LANDING 1 POWER lever IDLE 2 Brakes as required 3 ALTERNATE AIR CLOSED 4 PITOT HEAT OFF 5 Avionics as required 6 Lights as required 7 FLAPS UP 8 Fuel pumps LH RH OF...

Page 219: ... switching the ELECT MASTER OFF This ensures that engine and flight data can be written to non volatile memory before removing electrical power NOTE During engine shut down at altitudes greater than 7500 ft it is possible that the propeller will feather due to the increased engine idle power As the increase in propeller RPM can prevent the propeller start locks from engaging proceed with steps 9 1...

Page 220: ... run for at least 1 minute with the power lever up to 10 to avoid heat damage of the turbo charger CAUTION Do not shut down an engine with the FUEL SELECTOR valve The high pressure fuel pump can otherwise be damaged END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4A 63 ...

Page 221: ...LIGHT INSPECTION 1 Record any problem found in flight and during the post flight check in the log book 2 Park the airplane 3 If necessary moor the airplane END OF CHECKLIST 4A 6 17 PARKING 1 Parking brake release use chocks 2 Airplane moor if unsupervised for extended period 3 Pitot probe cover END OF CHECKLIST Page 4A 64 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 222: ...ance and to the maximum horizontal speed The effect on the flight characteristics is minimal Flight through very heavy rain should be avoided because of the associated visibility problems END OF CHECKLIST 4A 6 19 REFUELING CAUTION Before refueling the airplane mustbe connected to electrical ground Grounding points exhaust left and right Refer to Section 2 14 for approved fuel grades Doc No 11 01 0...

Page 223: ...dditives mayhave been alreadymixedinto the fuel when stored In this case make sure that the brand is approved and the concentration does not exceed the approved values Anti microbial life fuel additives may be manually batch blended into the fuel tanks In this case introduce the additive while filling the tank after approximately the half tank is filled Anti icing fuel additives should not be batc...

Page 224: ... 23 2 0 78 Densities used for calculation Fuel 0 804 kg L KATHON FP 1 5 1 04 kg L b BIOBOR JF Fuel Quantity Fuel Additive BIOBOR JF 135 ppm 270 ppm Liter US gal kg lb mL oz mL oz 50 13 2 40 2 88 68 5 2 0 18 10 4 0 35 100 26 4 80 4 177 37 10 4 0 35 20 9 0 71 150 39 6 120 6 266 05 15 6 0 53 31 3 1 06 200 52 8 160 8 354 73 20 9 0 71 41 8 1 42 300 79 3 241 2 532 10 31 3 1 06 62 7 2 13 Calculation acco...

Page 225: ...re used then both tanks must be refueled to the maximum level Onlythen the pilot has proper information concerning the fuelquantityin the auxiliarytanks If the auxiliary tanks are not in use make sure that they are empty refer to Section 6 4 FLIGHT MASS CENTER OF GRAVITY Page 4A 68 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 226: ...AUTION Do not attempt an in flight engine restart if the engine has been shutdown for more than two minutes NOTE When demonstrating handling qualities with one engine inoperative the left engine is the critical engine Shutdown and Restarting the Engine with the Starter Maximum restart airspeed max 80 KIAS or airspeed for a stationary propeller whichever is lower WARNING VMCA is 76 KIAS and should ...

Page 227: ...bove 2 Airspeed trim to 86 KIAS VSSE The following actions must be completed in not more than two minutes If MÄM 62 168 engine software VC33_2P_05_19 orlaterapproved software is installed refer to the times shown in the table below OAT Max Engine OFF Time C F minutes below 15 below 5 2 15 to 5 5 to 23 5 above 5 above 23 10 1 ENGINE MASTER of selected engine OFF propeller feathers 2 POWER lever of ...

Page 228: ...ed engine engage when propeller is stationary CAUTION After the engine has started the POWER lever should be set to a moderate power setting until engine temperature have reached the green range END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4A 71 ...

Page 229: ...BOX TEMPERATURE 4B 9 4B 2 6 FUEL TEMPERATURE 4B 9 4B 2 7 VOLTAGE 4B 10 4B 3 CAUTION ALERTS ON THE G1000 4B 11 4B 3 1 CAUTIONS GENERAL 4B 11 4B 3 2 L R ECU A FAIL 4B 12 4B 3 3 L R ECU B FAIL 4B 15 4B 3 4 L R FUEL LOW 4B 18 4B 3 5 LOW VOLTAGE CAUTION LOW VOLTS 4B 19 4B 3 6 L R ALTN FAIL 4B 20 4B 3 7 L R COOL LVL 4B 21 4B 3 8 PITOT FAIL HT OFF 4B 22 4B 3 9 STALL HT FAIL OFF 4B 23 4B 3 10 L R AUXILIAR...

Page 230: ... 4B 7 2 STARTING ENGINE 4B 33 4B 8 LIGHTNING STRIKE 4B 35 4B 9 FAILURES IN THE AUTOPILOT SYSTEM 4B 36 4B 9 1 AUTOPILOT DISCONNECT Yellow AP Flashing on PFD 4B 36 4B 9 2 AUTOPILOT OVERSPEED RECOVERY Yellow MAXSPD on PFD 4B 36 4B 9 3 LOSS OF NAVIGATION INFORMATION Yellow VOR VAPP GPS or LOC Flashing on PFD 4B 37 4B 9 4 AUTOPILOT OUT OF TRIM Yellow 7AIL 6AIL 8ELE 9ELE 7RUD or 6RUD on PFD 4B 38 4B 9 5...

Page 231: ...lower risk than the attempt toreach the nearest airfield under all circumstances NOTE If no level landing area is available a landing on an upward slope should be sought 1 Select appropriate landing area 2 Consider wind 3 Approach If possible the landing area should be overflown at a suitable height in order to recognize obstacles The degree of offset at each part of the circuit will allow the win...

Page 232: ...t time is remaining the risk of fire in the event of a collision with obstacles can be reduced as follows after a safe touch down 6 ENGINE MASTER both OFF 7 FUEL SELECTOR both OFF 8 ELECT MASTER OFF END OF CHECKLIST Page 4B 4 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 233: ...RPM High RPM 1 Reduce power of affected engine 2 Keep RPM within the green range using the power lever If the above mentioned measures do not solve theproblem refer to 3 13 3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM 3 Land at the nearest suitable airfield END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4B 5 ...

Page 234: ...nt from high altitudes with a low power setting coolant temperature may decrease In this case an increase in power and a decrease in airspeed can help L R COOL LVL Caution Message displayed Reduce power on affected engine Expect loss of coolant WARNING A furtherdecrease in coolant temperature must be expected Prepare for an engine failure in accordance with 3 7 6 ENGINE FAILURES IN FLIGHT END OF C...

Page 235: ...according to 3 2 3 L R OIL TEMP b Low Oil Temperature NOTE During an extended descent from high altitudes with a low power setting oil temperature may decrease In this case an increase in power can help Increase power Reduce airspeed END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4B 7 ...

Page 236: ...se oil pressure indication Keep monitoring temperatures If the temperatures are outside of the green range Reduce power on affected engine WARNING Land at the nearest suitable airfield Prepare for an engine failure in accordance with 3 7 6 ENGINE FAILURES IN FLIGHT END OF CHECKLIST b Low Oil Pressure Proceed according to 3 2 4 L R OIL PRES Page 4B 8 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 237: ...d engine Reduce airspeed CAUTION At low ambient temperature conditions and or at high airspeeds with low power settings it can be assumed that the above mentioned procedure will increase the temperature s If the fuel temperature does not return to the green range perform a precautionary landing on the nearest suitable airfield Prepare for an engine failure in accordance with 3 7 6 ENGINE FAILURES ...

Page 238: ...CAUTION LOW VOLTS 4B 4 5 is still indicated on the G1000 Terminate flight preparation b Low Voltage During Flight 1 ALTERNATORS check ON 2 Circuit breakers check 3 Electrical equipment OFF if not needed If LOW VOLTAGE CAUTION LOW VOLTS 4B 4 5 is still indicated on the G1000 Follow procedure in 4B 4 6 L R ALTN FAIL END OF CHECKLIST Page 4B 10 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 239: ...LERTS ON THE G1000 The G1000 provides the following CAUTION alerts on the PFD in the ALERT area 4B 3 1 CAUTIONS GENERAL CHARACTERISTICS Amber color coded text Single warning chime tone of 1 5 seconds duration Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4B 11 ...

Page 240: ...til cleared through maintenance action A non latched caution clears itself only on the active ECU Non latched caution messages can be cleared on the passive ECU by switching to that ECU with the voter switch a ECU A Caution on the Ground 1 VOTER switch check AUTO 2 ECU B caution check OFF 3 VOTER switch ECU A 4 Wait 5 seconds 5 VOTER switch AUTO If the ECU A caution persists terminate flight prepa...

Page 241: ...rocedure WARNING When carrying out the clearing procedure be prepared for a loss of engine power In case of a negative single engine climb rate do not carry out this procedure unless a suitable landing site is available within gliding distance Dependingon the cause of the ECU caution switching to the passive failed ECU may lead to rough engine run power fluctuation or temporary loss of power In th...

Page 242: ...s 8 VOTER switch AUTO If the ECU A caution persists land at the next suitable airfield NOTE An ECU FAIL CAUTION is caused by various types of malfunctions These include internal ECU problems sensor failures or insufficient performance of air fuel or electrical supply system e g air filter icing NOTE If additional engine problems are observed refer to 3 7 2 ENGINE TROUBLESHOOTING END OF CHECKLIST P...

Page 243: ...til cleared through maintenance action A non latched caution clears itself only on the active ECU Non latched caution messages can be cleared on the passive ECU by switching to that ECU with the voter switch a ECU B Caution on the Ground 1 VOTER switch check AUTO 2 ECU A caution check OFF 3 VOTER switch ECU B 4 Wait 5 seconds 5 VOTER switch AUTO If the ECU B caution persists terminate flight prepa...

Page 244: ...rocedure WARNING When carrying out the clearing procedure be prepared for a loss of engine power In case of a negative single engine climb rate do not carry out this procedure unless a suitable landing site is available within gliding distance Depending on the cause of the ECU caution switchingto the passive failed ECU may lead to rough engine run power fluctuation or temporary loss of power In th...

Page 245: ...s 7 VOTER switch AUTO If the ECU B caution persists land at the next suitable airfield NOTE An ECU FAIL CAUTION is caused by various types of malfunctions These include internal ECU problems sensor failures or insufficient performance of air fuel or electrical supply system e g air filter icing NOTE If additional engine problems are observed refer to 3 7 2 ENGINE TROUBLESHOOTING END OF CHECKLIST D...

Page 246: ...while taxiing in curves If L R FUEL LOW caution is caused by un coordinated flight CAUTION Prolonged un coordinated flight canlead to a L RFUEL LOW caution andsubsequent LOW PXwarningand L RECUFAIL caution and can cause fuel starvation to the engine resulting in a loss of power 2 Return to coordinated flight not more than approx half a ball sideslip 3 5 bank If LH RH main tanks show remarkable dif...

Page 247: ...T 4B 3 5 LOW VOLTAGE CAUTION LOW VOLTS L R VOLTS LOW Left Right engine bus voltage is too low less than 25 Volts Possible reasons are A fault in the power supply ALTERNATORS off Continue with 4B 3 7 VOLTAGE CAUTION If both low voltage indications are ON expect failure of both alternators and follow 4B 4 6 L R ALTN FAIL END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4B 19 ...

Page 248: ...e alternator has failed a One Alternator Failed 1 ALTERNATOR OFF affected side 2 Bus voltage monitor 3 Electrical consumers reduce as practicable END OF CHECKLIST b Both Alternators Failed Proceed according to 3 3 1 L R ALTN FAIL END OF CHECKLIST Page 4B 20 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 249: ...y lead to decreased engine cooling capability loss of engine power due to engine failure 1 Annunciations Engine instruments monitor See 4B 3 2 COOLANT TEMPERATURE NOTE The indication is calibrated for straight and level flight The caution message may be triggered during turns which are flown with slip or while taxiing in curves END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4B 21 ...

Page 250: ...peration of the Pitot heating on the ground can also cause the Pitot heating caution message to be displayed In this case it indicatesthe activation of the thermal switch which prevents overheating of the Pitot heating system on the ground This is a normal function of the system After a cooling period the heating system will be switched on again automatically If in icing conditions 2 Expect loss o...

Page 251: ...ng heating system Operation of the stall warning heating on the ground also causes the stall warning heating failed caution message to be displayed In this case it indicates the activation of the thermal protection relay which prevents overheating of the stallwarningheating system on the ground This is a normal function of the system If in icing conditions 2 Expect loss of acoustic stall warning 3...

Page 252: ...y auxiliaryfuel tank while the auxiliary fuel pump is switched ON 1 L R auxiliary fuel pump OFF END OF CHECKLIST 4B 3 11 CHECK GEAR CHECK GEAR Landing gear is not down and locked 1 Landing gear down as required NOTE TheCHECKGEARcautionmessageisdisplayedwhen either the flaps are in LDG position or one power lever is less than approx 20 and the landing gear is not down and locked END OF CHECKLIST Pa...

Page 253: ...vigate 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 b Final Approach If the LOI annunciation is displayed while on the final approach segmen...

Page 254: ... 4B 3 13 AHRS ALIGNING KEEP WINGS LEVEL AHRS ALIGN Keep Wings Level The AHRS Attitude and Heading Reference System is aligning Keep wings level using standby attitude indicator END OF CHECKLIST Page 4B 26 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 255: ...erto5 3 10 LANDINGDISTANCESforlandingdistances with abnormal flap positions a Only UP available Airspeed up to 1999 kg 4407 lb min 91 KIAS above 1999 kg 4407 lb min 95 KIAS Land at a flat approach angle use power lever to control airplane speed and rate of descent b Only T O available Airspeed up to 1999 kg 4407 lb min 88 KIAS above 1999 kg 4407 lb min 91 KIAS Land at a flat approach angle use pow...

Page 256: ...Abnormal Operating Procedures DA 62 AFM c Only LDG available Perform normal landing END OF CHECKLIST Page 4B 28 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 257: ...RUDDER PEDAL ADJUSTMENT Runaway of Electrical Rudder Pedal Adjustment NOTE The circuit breaker for the rudder pedal adjustment islocated on the RH side of the instrument panel 1 PEDALS circuit breaker pull END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4B 29 ...

Page 258: ...increased fuel consumption and decreased range Unscheduled maintenance action is required after landing END OF CHECKLIST 4B 6 2 HYDRAULIC PUMP FAILURE 1 Landing gear indication lights check 2 Prepare for manual landing gear extension Refer to Section 3 10 2 MANUAL EXTENSION OF THE LANDING GEAR NOTE The landing gear might extend as the hydraulic system pressure decreases Consider for higher aerodyn...

Page 259: ...nd emergency exits and the ban on smoking 3 Rear door closed and locked 4 Front doors closed and locked 5 Rudder pedals adjusted 6 Safety harnesses all on and fastened 7 POWER lever check IDLE 8 Parking brake set 9 AVIONIC MASTER check OFF 10 GEAR selector check DOWN 11 VOTER switch check AUTO 12 ALTERNATORS check ON 13 ELECT MASTER check OFF 14 ENGINE MASTER check OFF 15 PROPELLER check clear 16 ...

Page 260: ...rate continuously or periodically terminate flight There is a malfunction in the landing gear system NOTE When switching the external power unit ON all electrical equipment connected to the LH and RH main buses is powered 17 G1000 wait until power up completed Press ENT on MFD to acknowledge NOTE The engine instruments are only available on the MFD after item 17 has been completed END OF CHECKLIST...

Page 261: ...NGINE GLOW is indicated only when the engine is cold 6 Annunciations Engine System Page check OK normal range WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered After the L ENGINE GLOW indication is extinguished 7 START LEFT button PRESS as required release when engine has started CONTINUED Doc No 11 01 05 E Rev 0 11 Jan 2019 P...

Page 262: ...the START button has been released set the ENGINE MASTER to OFF and investigate the problem 8 Annunciations Engine System Page check OK normal range 9 Annunciations Starter check OFF 10 Annunciations Oil pressure check OK WARNING If the oil pressure has not moved from the red range within 3 seconds after starting set the ENGINE MASTER switch to OFF and investigate problem 11 Circuit breakers check...

Page 263: ...dically 5 Continue flight under VMC 6 Land on the next suitable airfield CAUTION Due to possible damage to the airplane obey the following instructions Avoid abrupt or full control surface movements Avoid high g loads on the airframe Avoid high yaw angles Avoid turbulent airasfaraspossible e g lee effects Do not fly into areas of known or forecast icing Maintain VMC END OF CHECKLIST Doc No 11 01 0...

Page 264: ...s which has failed The autopilot cannot be re engaged with either of these annunciations present END OF CHECKLIST 4B 9 2 AUTOPILOT OVERSPEED RECOVERY yellow MAXSPD on PFD 1 POWER lever reduce power When overspeed condition is corrected 2 Autopilot reselect VERTICAL MODE if necessary NOTE Overspeed recovery mode provides a pitch up command to decelerate the airplane at or below the maximum autopilo...

Page 265: ... it the autopilot will roll the airplane wings level and default to roll mode ROL 1 Autopilot select HDG on mode controller 2 Nav source select a valid NAV source 3 Autopilot select NAV on mode controller If on an instrument approach at the time the navigation signal is lost 4 Missed approach procedure EXECUTE as applicable END OF CHECKLIST Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 4B 37 ...

Page 266: ...ondition 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 8ELE or 9ELE indication during configuration or la...

Page 267: ...tch RELEASE WARNING Followingan autopilot autotrimormanualelectrictrim system malfunction do not engage the autopilot or operate the manual electric trim until the cause of the malfunction has been corrected END OF CHECKLIST For 6AIL 7AIL or 6RUD 7RUD Indication 1 Rudder trim VERIFY slip skid indicator is centered trim is necessary NOTE Observe the maximum fuel imbalance limitation CONTINUED Doc N...

Page 268: ...ces in the direction of the annunciation arrow For example an 6AIL indicates that sustained right wing down control stick force or for 6RUD sustained right rudder force will be required upon autopilot disconnect 3 AP DISC switch DEPRESS 4 Autopilot RE ENGAGE if lateral trim is re established END OF CHECKLIST Page 4B 40 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 269: ...r 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 1 Autopilot mode controls select another vertical mode If on an instrument approach 2 Autopilot DISCONNECT and continue manually or execute missed approach Loss of Selected Lateral Mode HDG NAV GPS LOC VAPP BC 1 Autopilot mode controls select another lateral mode If on an...

Page 270: ...isconnects and autopilot and flight director are inoperative Manual electric trim is available GIA No 1 The autopilot disconnects and autopilot flight director and manual electric trim are inoperative GIA No 2 The autopilot disconnects and autopilot and manual electric trim are inoperative Flight director is available GPS No 1 and 2 The autopilot and flight director operates in NAV modes only LOC ...

Page 271: ...lance in the main tanks is less than 1 US gal 3 8 liters 3 Check fuel imbalance in the main tanks use CROSSFEED function above 10000 ft turn LH RH FUEL PUMP to ON before crossfeed operation to keep the LH and RH main tank imbalance within the permissible limit of 1 US gal 3 8 liters 4 Switch the remaining AUX PUMP ON 5 Use crossfeed function to keep the LH and RH main tank imbalance within the per...

Page 272: ...ATMOSPHERE 5 5 5 3 4 STALLING SPEEDS 5 6 5 3 5 WIND COMPONENTS 5 8 5 3 6 TAKE OFF DISTANCE 5 9 5 3 7 CLIMB PERFORMANCE TAKE OFF CLIMB 5 35 5 3 8 CLIMB PERFORMANCE CRUISE CLIMB 5 44 5 3 9 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE 5 49 5 3 10 TIME FUEL DISTANCE TO CLIMB 5 54 5 3 11 CRUISE PERFORMANCE 5 59 5 3 12 LANDING DISTANCES 5 62 5 3 13 GO AROUND CLIMB PERFORMANCE 5 88 5 3 14 APPROVED NOISE DATA...

Page 273: ...s quoted in this manual are applied and the airplane has been well maintained 5 2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS In order to illustrate the influence of a number of different variables the performance data is reproduced in the form of tables or diagrams These contain sufficiently detailed information so that conservative values can be selected and used for the determination of adequate...

Page 274: ...nded retracted has no significant influenceon the airspeed indicator system Airspeed Indicator Calibration Indicated Airspeed KIAS Calibrated Airspeed KCAS 75 74 80 79 85 84 90 89 95 94 100 99 105 104 110 109 115 114 120 119 125 124 130 129 135 134 140 138 150 148 160 158 170 167 180 177 190 186 200 196 205 201 Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 5 3 ...

Page 275: ...ated from the last fuel quantity update done by the pilot and actual fuel flow data Therefore the endurance and range data is for information only and must not be used for flight planning Fuel Flow Power Setting Fuel Flow US gal h Fuel Flow Liter h 30 3 3 12 5 35 3 7 14 0 40 4 1 15 5 45 4 5 17 0 50 4 9 18 5 55 5 4 20 5 60 5 9 22 5 65 6 4 24 5 70 6 9 26 0 75 7 4 28 0 80 7 8 29 5 85 8 3 31 5 90 9 0 ...

Page 276: ...DA 62 AFM Performance 5 3 3 INTERNATIONAL STANDARD ATMOSPHERE Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 5 5 ...

Page 277: ...1 80 78 94 93 DOWN LDG 63 61 67 66 74 73 88 87 1900 kg 4189 lb Bank Angle 0 30 45 60 Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP UP 69 68 74 73 82 81 97 96 DOWN T O 68 66 73 71 80 79 95 94 DOWN LDG 63 62 68 67 75 74 89 88 1999 kg 4407 lb Bank Angle 0 30 45 60 Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP UP 70 69 75 74 83 82 99 98 DOWN T O 69 67 74 72 81 80 96 95 DOWN LDG 64 63 6...

Page 278: ...0 30 45 60 Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP UP 72 71 77 76 85 84 101 100 DOWN T O 70 68 75 73 83 81 98 97 DOWN LDG 68 67 74 73 82 81 97 96 2300 kg 5071lb Bank Angle 0 30 45 60 Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP UP 73 72 78 77 87 86 103 102 DOWN T O 71 69 76 74 83 82 99 98 DOWN LDG 69 68 74 73 82 81 97 96 NOTE KIAS values may not be accurate at stall Doc No 1...

Page 279: ...ormance DA 62 AFM 5 3 5 WIND COMPONENTS Example Flight direction 360 Wind 32 30 kts Result Crosswind component 16 kts Max demonstrated crosswind component 25 kts Page 5 8 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 280: ...way dry 5 cm 2 in long Increase the ground roll by 10 Grass runway dry 5 cm 2 in to 10 cm 3 9 in long Increase the ground roll by 15 Grass runway dry 25 cm 9 8 in long Increase the ground roll by 25 Grass runway longer than 25 cm 9 8 in A take off should not be attempt Grass runway wet Increase the dry grass runway distance calculation by 10 Soft ground Increase the ground roll by 45 in addition t...

Page 281: ...ical values On wet ground or wet soft grass covered runways the take off rollmay become significantly longer thanstatedabove In any case the pilot must allow for the condition of the runway to ensure a safe take off The above corrections for runway slope should be used with caution since published runway slope data is usually the net slope from one end of the runway to the other Runways may have p...

Page 282: ... 1200 1370 910 3000 914 Ground Roll 530 560 600 660 750 850 555 15 m 50 ft 910 960 1020 1120 1290 1470 952 4000 1219 Ground Roll 560 600 640 710 810 920 582 15 m 50 ft 960 1020 1080 1210 1390 1590 996 5000 1524 Ground Roll 600 640 680 770 870 613 15 m 50 ft 1020 1080 1150 1310 1500 1047 6000 1829 Ground Roll 650 690 730 840 960 655 15 m 50 ft 1100 1160 1250 1430 1640 1118 7000 2134 Ground Roll 700...

Page 283: ...00 914 Ground Roll 500 530 570 620 710 810 527 15 m 50 ft 860 910 960 1060 1210 1380 895 4000 1219 Ground Roll 540 570 610 670 770 880 555 15 m 50 ft 910 960 1020 1140 1300 1490 938 5000 1524 Ground Roll 570 600 650 730 830 584 15 m 50 ft 960 1010 1080 1230 1400 984 6000 1829 Ground Roll 620 650 700 800 910 624 15 m 50 ft 1040 1100 1170 1340 1530 1049 7000 2134 Ground Roll 670 710 770 880 1000 667...

Page 284: ... 3000 914 Ground Roll 480 510 540 590 680 770 502 15 m 50 ft 810 850 900 990 1130 1290 841 4000 1219 Ground Roll 510 540 570 640 730 830 527 15 m 50 ft 850 900 960 1070 1220 1400 879 5000 1524 Ground Roll 540 580 610 690 790 555 15 m 50 ft 900 950 1020 1150 1310 925 6000 1829 Ground Roll 580 620 660 760 860 592 15 m 50 ft 970 1030 1100 1260 1430 984 7000 2134 Ground Roll 630 670 730 830 950 633 15...

Page 285: ...0 694 3000 914 Ground Roll 430 450 480 530 600 680 444 15 m 50 ft 690 730 780 850 970 1110 727 4000 1219 Ground Roll 450 480 510 570 650 740 468 15 m 50 ft 730 770 820 920 1050 1200 759 5000 1524 Ground Roll 480 510 540 610 700 493 15 m 50 ft 780 820 880 990 1130 797 6000 1829 Ground Roll 520 550 590 670 760 525 15 m 50 ft 840 880 940 1080 1230 848 7000 2134 Ground Roll 560 600 650 740 840 563 15 ...

Page 286: ... 970 636 3000 914 Ground Roll 400 430 450 500 570 640 420 15 m 50 ft 640 680 720 800 910 1040 668 4000 1219 Ground Roll 430 450 480 540 610 700 442 15 m 50 ft 680 720 770 860 980 1120 703 5000 1524 Ground Roll 460 480 520 580 660 466 15 m 50 ft 730 770 820 920 1060 746 6000 1829 Ground Roll 490 520 560 640 720 498 15 m 50 ft 780 830 880 1010 1150 794 7000 2134 Ground Roll 530 560 610 700 800 531 1...

Page 287: ...770 890 576 3000 914 Ground Roll 380 400 430 470 540 610 398 15 m 50 ft 580 610 650 720 830 960 603 4000 1219 Ground Roll 400 430 450 510 580 660 416 15 m 50 ft 610 650 690 780 900 1050 631 5000 1524 Ground Roll 430 450 490 550 620 438 15 m 50 ft 650 690 740 850 980 666 6000 1829 Ground Roll 460 490 520 600 680 468 15 m 50 ft 710 750 800 930 1070 713 7000 2134 Ground Roll 500 530 580 660 750 501 1...

Page 288: ...Ground Roll 560 590 630 690 780 890 584 15 m 50 ft 900 940 1000 1100 1250 1430 936 4000 1219 Ground Roll 590 630 660 740 840 960 611 15 m 50 ft 950 1000 1060 1180 1350 1540 981 5000 1524 Ground Roll 630 670 710 800 910 643 15 m 50 ft 1000 1060 1130 1280 1450 1027 6000 1829 Ground Roll 680 720 770 880 1000 687 15 m 50 ft 1080 1140 1220 1390 1590 1095 7000 2134 Ground Roll 730 780 840 960 1100 733 1...

Page 289: ...4 Ground Roll 530 560 600 650 740 850 556 15 m 50 ft 840 890 940 1040 1180 1340 883 4000 1219 Ground Roll 560 600 630 700 800 920 582 15 m 50 ft 890 940 1000 1110 1270 1450 921 5000 1524 Ground Roll 600 630 680 760 870 612 15 m 50 ft 940 1000 1060 1200 1370 968 6000 1829 Ground Roll 640 690 730 830 950 653 15 m 50 ft 1020 1070 1150 1310 1490 1030 7000 2134 Ground Roll 700 740 800 920 1040 697 15 m...

Page 290: ... 914 Ground Roll 510 530 570 620 710 800 527 15 m 50 ft 800 840 890 970 1110 1260 830 4000 1219 Ground Roll 530 570 600 670 760 870 551 15 m 50 ft 840 880 940 1040 1190 1360 868 5000 1524 Ground Roll 570 600 640 720 820 582 15 m 50 ft 890 940 1000 1130 1280 910 6000 1829 Ground Roll 610 650 690 790 900 621 15 m 50 ft 950 1010 1080 1230 1400 967 7000 2134 Ground Roll 660 700 760 870 990 663 15 m 50...

Page 291: ...3000 914 Ground Roll 480 510 540 590 670 760 501 15 m 50 ft 710 750 790 870 990 1120 738 4000 1219 Ground Roll 510 540 570 630 720 820 523 15 m 50 ft 750 790 830 930 1060 1200 771 5000 1524 Ground Roll 540 570 610 690 780 550 15 m 50 ft 790 830 890 1000 1140 809 6000 1829 Ground Roll 580 620 660 750 850 589 15 m 50 ft 850 900 950 1090 1240 859 7000 2134 Ground Roll 630 660 720 830 940 629 15 m 50 ...

Page 292: ...666 3000 914 Ground Roll 450 480 510 560 630 720 472 15 m 50 ft 670 700 740 810 920 1050 694 4000 1219 Ground Roll 480 510 540 600 680 780 495 15 m 50 ft 700 740 780 870 990 1130 726 5000 1524 Ground Roll 510 540 570 650 740 520 15 m 50 ft 740 780 830 940 1070 759 6000 1829 Ground Roll 550 580 620 710 810 556 15 m 50 ft 800 840 900 1020 1160 809 7000 2134 Ground Roll 590 630 680 780 880 594 15 m 5...

Page 293: ...0 610 3000 914 Ground Roll 430 450 480 530 600 680 445 15 m 50 ft 610 650 680 760 870 980 637 4000 1219 Ground Roll 450 480 510 570 640 730 466 15 m 50 ft 650 680 730 810 930 1060 668 5000 1524 Ground Roll 480 510 540 610 700 492 15 m 50 ft 690 730 780 880 1000 704 6000 1829 Ground Roll 520 550 590 670 760 524 15 m 50 ft 740 790 840 960 1090 751 7000 2134 Ground Roll 560 590 640 730 830 559 15 m 5...

Page 294: ...4500 2984 3000 914 Ground Roll 1750 1850 1950 2150 2450 2800 1821 15 m 50 ft 3000 3150 3350 3700 4250 4850 3121 4000 1219 Ground Roll 1850 1950 2100 2350 2650 3050 1909 15 m 50 ft 3150 3350 3550 4000 4550 5250 3268 5000 1524 Ground Roll 2000 2100 2250 2550 2900 2011 15 m 50 ft 3350 3550 3800 4300 4900 3434 6000 1829 Ground Roll 2150 2250 2400 2750 3150 2148 15 m 50 ft 3650 3850 4100 4700 5400 3665...

Page 295: ...Ground Roll 1650 1750 1850 2050 2350 2650 1729 15 m 50 ft 2800 3000 3150 3500 3950 4550 2936 4000 1219 Ground Roll 1750 1850 2000 2200 2550 2900 1819 15 m 50 ft 3000 3150 3350 3750 4250 4900 3076 5000 1524 Ground Roll 1900 2000 2150 2400 2750 1916 15 m 50 ft 3150 3350 3550 4050 4600 3227 6000 1829 Ground Roll 2050 2150 2300 2600 3000 2046 15 m 50 ft 3400 3600 3850 4400 5050 3439 7000 2134 Ground R...

Page 296: ...Ground Roll 1600 1700 1800 1950 2250 2550 1644 15 m 50 ft 2650 2800 2950 3250 3700 4250 2759 4000 1219 Ground Roll 1700 1800 1900 2100 2400 2750 1729 15 m 50 ft 2800 2950 3150 3500 4000 4600 2884 5000 1524 Ground Roll 1800 1900 2000 2300 2600 1820 15 m 50 ft 2950 3150 3350 3800 4300 3035 6000 1829 Ground Roll 1950 2050 2200 2500 2850 1943 15 m 50 ft 3200 3400 3600 4150 4700 3229 7000 2134 Ground R...

Page 297: ...Ground Roll 1400 1500 1600 1750 2000 2250 1456 15 m 50 ft 2300 2400 2550 2800 3200 3650 2383 4000 1219 Ground Roll 1500 1600 1700 1900 2150 2450 1534 15 m 50 ft 2400 2550 2700 3000 3450 3950 2490 5000 1524 Ground Roll 1600 1700 1800 2050 2300 1617 15 m 50 ft 2550 2700 2900 3250 3700 2614 6000 1829 Ground Roll 1700 1800 1950 2200 2500 1722 15 m 50 ft 2750 2900 3100 3550 4050 2781 7000 2134 Ground R...

Page 298: ...Ground Roll 1350 1400 1500 1650 1850 2150 1377 15 m 50 ft 2100 2250 2350 2650 3000 3400 2191 4000 1219 Ground Roll 1400 1500 1600 1750 2000 2300 1449 15 m 50 ft 2250 2350 2550 2850 3200 3700 2306 5000 1524 Ground Roll 1500 1600 1700 1900 2200 1526 15 m 50 ft 2400 2550 2700 3050 3450 2445 6000 1829 Ground Roll 1600 1700 1850 2100 2400 1632 15 m 50 ft 2600 2750 2900 3300 3750 2603 7000 2134 Ground R...

Page 299: ...Ground Roll 1250 1350 1400 1550 1750 2000 1303 15 m 50 ft 1900 2000 2150 2350 2700 3150 1979 4000 1219 Ground Roll 1350 1400 1500 1650 1900 2150 1363 15 m 50 ft 2000 2150 2250 2550 2950 3450 2070 5000 1524 Ground Roll 1400 1500 1600 1800 2050 1435 15 m 50 ft 2150 2250 2450 2800 3250 2185 6000 1829 Ground Roll 1550 1600 1750 1950 2250 1533 15 m 50 ft 2300 2450 2650 3100 3500 2338 7000 2134 Ground R...

Page 300: ...d Roll 1850 1950 2050 2250 2600 2950 1914 15 m 50 ft 2950 3100 3300 3600 4100 4700 3068 4000 1219 Ground Roll 1950 2050 2200 2450 2800 3150 2005 15 m 50 ft 3100 3300 3500 3900 4450 5100 3217 5000 1524 Ground Roll 2050 2200 2350 2650 3000 2110 15 m 50 ft 3300 3500 3700 4200 4800 3369 6000 1829 Ground Roll 2250 2350 2550 2900 3300 2252 15 m 50 ft 3550 3750 4000 4600 5250 3592 7000 2134 Ground Roll 2...

Page 301: ...d Roll 1750 1850 1950 2150 2450 2800 1821 15 m 50 ft 2800 2950 3100 3400 3900 4400 2896 4000 1219 Ground Roll 1850 1950 2100 2300 2650 3000 1907 15 m 50 ft 2950 3100 3300 3650 4150 4750 3021 5000 1524 Ground Roll 2000 2100 2250 2500 2850 2006 15 m 50 ft 3100 3300 3500 3950 4500 3173 6000 1829 Ground Roll 2100 2250 2400 2750 3150 2140 15 m 50 ft 3350 3550 3750 4300 4900 3378 7000 2134 Ground Roll 2...

Page 302: ...d Roll 1650 1750 1850 2050 2350 2650 1728 15 m 50 ft 2600 2750 2900 3200 3650 4150 2722 4000 1219 Ground Roll 1750 1850 2000 2200 2500 2850 1808 15 m 50 ft 2750 2900 3100 3450 3900 4500 2848 5000 1524 Ground Roll 1900 2000 2100 2400 2700 1909 15 m 50 ft 2950 3100 3300 3700 4200 2985 6000 1829 Ground Roll 2000 2150 2300 2600 2950 2036 15 m 50 ft 3150 3300 3550 4050 4600 3172 7000 2134 Ground Roll 2...

Page 303: ...d Roll 1600 1650 1750 1950 2200 2500 1642 15 m 50 ft 2350 2450 2600 2850 3250 3700 2419 4000 1219 Ground Roll 1700 1750 1900 2100 2400 2700 1716 15 m 50 ft 2450 2600 2750 3050 3500 3950 2528 5000 1524 Ground Roll 1800 1900 2000 2250 2550 1803 15 m 50 ft 2600 2750 2950 3300 3750 2654 6000 1829 Ground Roll 1900 2050 2150 2450 2800 1930 15 m 50 ft 2800 2950 3150 3600 4050 2818 7000 2134 Ground Roll 2...

Page 304: ...d Roll 1500 1600 1700 1850 2100 2350 1547 15 m 50 ft 2200 2300 2450 2700 3050 3450 2277 4000 1219 Ground Roll 1600 1650 1800 2000 2250 2550 1623 15 m 50 ft 2300 2450 2600 2850 3250 3700 2380 5000 1524 Ground Roll 1700 1800 1900 2150 2450 1704 15 m 50 ft 2450 2600 2750 3100 3500 2491 6000 1829 Ground Roll 1800 1900 2050 2350 2650 1824 15 m 50 ft 2650 2750 2950 3350 3800 2653 7000 2134 Ground Roll 1...

Page 305: ...nd Roll 1400 1500 1600 1750 1950 2250 1459 15 m 50 ft 2050 2150 2250 2500 2850 3250 2087 4000 1219 Ground Roll 1500 1600 1700 1850 2100 2400 1529 15 m 50 ft 2150 2250 2400 2700 3050 3500 2190 5000 1524 Ground Roll 1600 1700 1800 2000 2300 1612 15 m 50 ft 2250 2400 2550 2900 3300 2310 6000 1829 Ground Roll 1700 1800 1950 2200 2500 1717 15 m 50 ft 2450 2600 2750 3150 3550 2462 7000 2134 Ground Roll ...

Page 306: ...imb can be calculated using the following formula NOTE Rate of climbat MTOM 2300kg 5071 lb with a power setting of 100 at MSL and ISA conditions 1075 ft min 5 5 m s with flaps UP 1018 ft min 5 2 m s with flaps T O Rate of climb at 1999 kg 4407 lb with a power setting of 100 at MSL and ISA conditions 1317 ft min 6 7 m s with flaps UP 1250 ft min 6 4 m s with flaps T O Doc No 11 01 05 E Rev 0 11 Jan...

Page 307: ...0 839 12000 3658 820 810 790 760 660 560 806 14000 4267 750 730 690 630 510 400 733 16000 4877 650 630 590 490 390 642 18000 5486 540 510 470 370 270 540 20000 6096 440 410 350 240 447 2 4 2 8 0 5 0 0 SL 1060 1050 1050 1040 1030 1030 980 870 1037 2000 610 1040 1030 1020 1020 1010 1000 920 820 1015 4000 1219 1010 1010 1000 990 980 950 870 770 990 6000 1829 990 980 970 960 950 900 810 966 8000 2438 ...

Page 308: ...1100 1090 1080 1080 1000 890 1092 4000 1219 1090 1080 1070 1060 1060 1030 940 830 1067 6000 1829 1060 1050 1050 1040 1030 970 880 1043 8000 2438 1040 1030 1020 1000 980 900 790 1017 10000 3048 1010 990 980 960 910 800 986 12000 3658 970 950 930 900 800 680 952 14000 4267 890 870 830 760 630 510 874 16000 4877 790 760 720 610 490 777 18000 5486 670 640 600 480 370 667 20000 6096 560 530 470 340 569...

Page 309: ...0 1063 12000 3658 1050 1030 1010 980 870 740 1030 14000 4267 970 940 910 830 700 580 950 16000 4877 860 830 790 690 560 851 18000 5486 740 720 670 550 430 741 20000 6096 630 610 540 410 644 1 4 9 1 0 8 0 9 SL 1290 1290 1280 1280 1280 1270 1210 1090 1278 2000 610 1270 1270 1270 1260 1250 1240 1150 1030 1257 4000 1219 1250 1250 1240 1230 1220 1190 1090 970 1230 6000 1829 1230 1220 1210 1200 1190 112...

Page 310: ...40 1330 1240 1110 1349 4000 1219 1350 1340 1330 1320 1310 1280 1170 1040 1322 6000 1829 1320 1310 1300 1290 1280 1210 1100 1295 8000 2438 1290 1280 1270 1260 1240 1130 1000 1266 10000 3048 1250 1240 1230 1220 1150 1020 1237 12000 3658 1220 1200 1180 1140 1020 880 1202 14000 4267 1130 1110 1070 990 840 700 1115 16000 4877 1020 990 950 830 690 1008 18000 5486 890 860 810 680 540 889 20000 6096 770 7...

Page 311: ... 901 12000 3658 890 870 860 820 730 620 872 14000 4267 810 790 760 690 570 460 801 16000 4877 720 690 650 550 450 708 18000 5486 600 580 540 430 330 604 20000 6096 500 480 420 300 513 2 4 2 8 0 5 0 0 SL 1110 1110 1100 1100 1090 1080 1030 930 1092 2000 610 1090 1090 1080 1070 1070 1060 980 880 1073 4000 1219 1070 1060 1060 1050 1040 1020 930 820 1052 6000 1829 1050 1040 1030 1020 1010 960 870 1031 ...

Page 312: ...1150 1150 1140 1060 950 1152 4000 1219 1150 1140 1140 1130 1120 1090 1000 890 1130 6000 1829 1130 1120 1110 1100 1090 1030 940 1109 8000 2438 1100 1090 1080 1070 1050 960 850 1081 10000 3048 1070 1060 1050 1030 980 860 1052 12000 3658 1040 1020 1010 970 870 740 1021 14000 4267 960 940 900 830 700 570 945 16000 4877 860 830 790 680 560 846 18000 5486 730 710 670 550 430 734 20000 6096 630 610 540 4...

Page 313: ...133 12000 3658 1120 1100 1080 1050 940 810 1101 14000 4267 1040 1020 980 910 770 630 1022 16000 4877 930 910 860 750 620 924 18000 5486 810 780 740 620 490 809 20000 6096 700 680 610 470 709 1 4 9 1 0 8 0 9 SL 1360 1350 1350 1340 1340 1330 1270 1150 1340 2000 610 1340 1330 1330 1320 1310 1310 1220 1090 1320 4000 1219 1320 1310 1300 1290 1290 1260 1150 1030 1297 6000 1829 1290 1280 1280 1270 1260 1...

Page 314: ... 1400 1300 1170 1414 4000 1219 1410 1400 1400 1390 1380 1350 1240 1110 1390 6000 1829 1380 1380 1370 1360 1350 1280 1170 1368 8000 2438 1360 1350 1340 1330 1310 1200 1070 1343 10000 3048 1330 1320 1300 1290 1220 1090 1310 12000 3658 1290 1280 1260 1220 1100 950 1276 14000 4267 1210 1190 1150 1060 910 760 1192 16000 4877 1090 1070 1020 890 750 1085 18000 5486 960 930 880 750 610 960 20000 6096 840 ...

Page 315: ...IMB Conditions Power lever both 95 Flaps UP Landing gear retracted Airspeed according table The climb performance tables show the rate of climb The gradient of climb can be calculated using the following formula Page 5 44 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 316: ...9 12000 3658 890 880 860 820 730 610 877 14000 4267 820 790 760 690 570 450 799 16000 4877 710 690 640 540 430 702 18000 5486 590 570 520 420 310 594 20000 6096 490 470 400 280 498 2 4 2 8 0 5 0 0 SL 1120 1110 1110 1100 1100 1090 1040 930 1100 2000 610 1100 1090 1090 1080 1070 1060 990 880 1080 4000 1219 1080 1070 1060 1050 1050 1020 930 820 1056 6000 1829 1050 1040 1040 1020 1020 960 870 1032 800...

Page 317: ...0 1150 1140 1060 950 1158 4000 1219 1160 1150 1140 1130 1120 1090 1000 880 1133 600 1829 1130 1120 1110 1100 1090 1030 940 1108 8000 2438 1100 1090 1080 1070 1050 960 850 1082 10000 3048 1070 1060 1050 1040 970 860 1055 12000 3658 1040 1020 1000 970 860 730 1022 14000 4267 960 930 890 820 680 550 939 16000 4877 840 820 770 660 540 835 18000 5486 720 690 650 530 410 719 20000 6096 600 580 510 380 6...

Page 318: ...2000 3658 1120 1110 1090 1050 940 800 1110 14000 4267 1040 1020 980 900 760 620 1024 16000 4877 930 900 850 740 610 917 18000 5486 800 770 730 600 470 799 20000 6096 680 660 590 450 695 1 4 9 1 0 8 0 9 SL 1360 1360 1350 1350 1340 1340 1280 1150 1346 2000 610 1340 1340 1330 1330 1320 1310 1220 1090 1327 4000 1219 1320 1320 1310 1300 1290 1260 1150 1030 1305 6000 1829 1300 1290 1280 1270 1260 1200 1...

Page 319: ...0 1310 1170 1420 4000 1219 1410 1410 1400 1390 1390 1350 1240 1100 1398 6000 1829 1390 1380 1370 1360 1350 1280 1170 1370 8000 2438 1360 1350 1340 1330 1310 1200 1070 1341 10000 3048 1330 1320 1310 1300 1220 1090 1312 12000 3658 1290 1280 1260 1220 1090 940 1282 14000 4267 1210 1180 1140 1050 890 740 1189 16000 4877 1080 1050 1010 880 730 1072 18000 5486 940 920 860 720 580 943 20000 6096 820 800 ...

Page 320: ... Landing gear retracted Airspeed vYSE Sideslip one ball out max 5 bank NOTE With respect to handling and performance the left hand engine pilots view is considered the critical engine The climb performance tables show the rate of climb The gradient of climb can be calculated using the following formula Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 5 49 ...

Page 321: ...00 3048 85 70 60 45 20 15 65 12000 3658 55 40 25 0 35 75 41 14000 4267 10 10 35 70 120 160 5 16000 4877 55 75 105 145 190 61 18000 5486 125 145 175 215 255 124 20000 6096 190 210 240 285 181 2 4 2 8 0 5 0 0 SL 240 230 220 210 200 190 170 130 204 2000 610 220 210 200 190 180 170 145 105 187 4000 1219 200 190 175 165 155 140 110 75 170 6000 1829 175 165 155 145 130 110 80 151 8000 2438 155 140 130 1...

Page 322: ... 247 2000 610 265 250 240 230 220 210 185 145 231 4000 1219 245 230 220 210 200 185 155 110 213 6000 1829 220 210 200 185 175 150 120 196 8000 2438 200 185 175 160 145 115 75 174 10000 3048 175 160 145 130 105 60 151 12000 3658 145 130 115 90 45 5 128 14000 4267 95 75 50 10 45 95 81 16000 4877 30 5 20 70 120 22 18000 5486 45 65 95 140 185 44 20000 6096 115 130 165 220 103 For the rate of climb in ...

Page 323: ...000 3048 220 205 190 180 150 105 199 12000 3658 190 175 160 135 90 40 175 14000 4267 140 120 95 55 0 55 127 16000 4877 75 55 25 25 75 69 18000 5486 0 20 50 100 145 2 20000 6096 65 85 120 175 58 1 4 9 1 0 8 0 9 SL 375 365 355 345 335 330 300 255 342 2000 610 360 345 335 325 315 305 275 225 326 4000 1219 335 325 315 305 295 280 240 190 308 6000 1829 315 305 295 285 270 245 205 290 8000 2438 295 280 ...

Page 324: ...3 2000 610 410 400 390 380 370 360 320 270 377 4000 1219 390 380 365 355 345 330 290 235 360 6000 1829 365 355 345 335 325 295 250 342 8000 2438 345 335 320 310 295 250 200 323 10000 3048 320 305 295 280 245 195 300 12000 3658 290 275 260 235 180 125 276 14000 4267 240 220 195 150 85 20 226 16000 4877 170 150 115 60 0 164 18000 5486 90 70 40 20 75 93 20000 6096 20 0 40 100 29 For the rate of climb...

Page 325: ... tables Example OAT at take off 11 C 52 F Airfield pressure altitude 2000 ft 600 m Initial climb weight 1900 kg 4189 lb OAT at cruise 17 C 2 F Cruise altitude 16000 ft 4900 m Time fuel and distance to climb at airfield 2 min 0 5 US gal and 2 NM 1 Time fuel and distance to climb at cruise 14 min 4 2 US gal and 22 NM 2 Subtract 1 from 2 to obtain time fuel and distance to climb from airfield to crui...

Page 326: ...58 9 16 104 955 4 8 13 4 1 21 14000 4267 13 9 105 940 4 7 15 4 8 26 16000 4877 17 2 107 915 4 6 18 5 6 31 18000 5486 21 5 109 885 4 5 21 6 4 36 20000 6096 25 12 111 850 4 3 24 7 3 43 2 4 2 8 0 5 0 0 SL 15 59 95 1100 5 6 0 0 0 0 2000 600 11 52 96 1090 5 5 2 0 6 2 4000 1219 7 45 97 1075 5 4 4 1 2 6 6000 1829 3 38 99 1065 5 4 6 1 9 9 8000 2438 1 30 100 1055 5 3 8 2 5 12 10000 3048 5 23 102 1040 5 2 1...

Page 327: ...95 1175 6 0 0 0 0 0 2000 600 11 52 96 1165 5 9 2 0 6 2 4000 1219 7 45 97 1155 5 8 4 1 2 5 6000 1829 3 38 99 1140 5 8 6 1 7 8 8000 2438 1 30 100 1130 5 7 8 2 3 11 10000 3048 5 23 102 1115 5 6 9 2 9 15 12000 3658 9 16 104 1105 5 6 11 3 5 18 14000 4267 13 9 105 1085 5 5 13 4 2 22 16000 4877 17 2 107 1060 5 4 16 4 9 26 18000 5486 21 5 109 1030 5 2 18 5 5 31 20000 6096 25 12 111 995 5 0 21 6 2 37 Page ...

Page 328: ... 9 16 100 1190 6 0 11 3 3 16 14000 4267 13 9 102 1170 5 9 12 3 9 20 16000 4877 17 2 104 1145 5 8 14 4 5 24 18000 5486 21 5 105 1115 5 6 17 5 1 28 20000 6096 25 12 107 1075 5 4 19 5 8 33 1 4 9 1 0 8 0 9 SL 15 59 92 1345 6 8 0 0 0 0 2000 600 11 52 93 1335 6 7 2 0 5 2 4000 1219 7 45 94 1325 6 7 4 1 0 4 6000 1829 3 38 96 1315 6 6 5 1 5 7 8000 2438 1 30 97 1300 6 6 7 2 0 9 10000 3048 5 23 99 1285 6 5 8...

Page 329: ...9 92 1440 7 3 0 0 0 0 2000 600 11 52 93 1425 7 2 2 0 5 2 4000 1219 7 45 94 1415 7 2 3 1 0 4 6000 1829 3 38 96 1405 7 1 5 1 4 6 8000 2438 1 30 97 1390 7 0 6 1 9 9 10000 3048 5 23 99 1380 7 0 8 2 4 11 12000 3658 9 16 100 1365 6 9 9 2 9 14 14000 4267 13 9 102 1345 6 8 11 3 4 17 16000 4877 17 2 104 1320 6 7 13 3 9 21 18000 5486 21 5 105 1285 6 5 15 4 4 24 20000 6096 25 12 107 1245 6 3 17 5 0 28 Page 5...

Page 330: ...ISE PERFORMANCE Conditions Flaps UP Landing gear retracted Weight up to1999 kg above 1999 kg ForconversionofOATtodelta ISAtemperaturesrefertoChapter5 3 3 INTERNATIONAL STANDARD ATMOSPHERE Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 5 59 ...

Page 331: ...142 50 9 8 144 50 9 8 145 10000 3048 95 19 3 185 95 19 3 188 95 19 3 190 95 19 3 191 95 18 8 192 75 14 8 169 75 14 8 171 75 14 8 173 75 14 8 175 75 14 8 176 60 11 8 154 60 11 8 156 60 11 8 157 60 11 8 159 60 11 8 161 45 8 9 135 50 9 8 144 50 9 8 145 50 9 8 146 50 9 8 148 12000 3658 95 19 3 189 95 19 3 191 95 19 2 193 95 18 8 194 95 18 1 194 75 14 8 172 75 14 8 174 75 14 8 176 75 14 8 178 75 14 8 1...

Page 332: ...128 50 9 8 137 50 9 8 139 50 9 8 140 10000 3048 95 19 3 183 95 19 3 185 95 19 3 187 95 19 3 189 95 18 8 189 75 14 8 166 75 14 8 168 75 14 8 170 75 14 8 171 75 14 8 173 60 11 8 150 60 11 8 152 60 11 8 153 60 11 8 155 60 11 8 156 45 8 9 129 50 9 8 138 50 9 8 140 50 9 8 141 50 9 8 142 12000 3658 95 19 3 187 95 19 3 189 95 19 2 191 95 18 8 191 95 18 1 191 75 14 8 169 75 14 8 171 75 14 8 173 75 14 8 17...

Page 333: ...ncrease by 10 for each 3 kt 1 5 m s tailwind Paved runway wet Increase by 15 Grass runway dry 5 cm 2 in long Increase the ground roll by 10 Grass runway dry 5 cm 2 in to 10 cm 3 9 in long Increase the ground roll by 15 Grass runway dry longer than 10 cm 3 9 in Increase the ground roll at least by 25 Grass runway wet or soft runway Increase the ground roll by 10 Downhill slope Increase the ground r...

Page 334: ...nways the landing distance may become significantly longer than stated above In any case the pilot must allow for the condition of the runway to ensure a safe landing The above corrections for runway slope should be used with caution since published runway slope data is usually the net slope from one end of the runway to the other Runways may have positions along their length at greater or lesser ...

Page 335: ...817 3000 914 Ground Roll 510 530 550 580 640 700 526 15 m 50 ft 860 890 910 960 1050 1150 879 4000 1219 Ground Roll 570 590 610 650 720 790 577 15 m 50 ft 920 950 970 1040 1140 1250 936 5000 1524 Ground Roll 610 640 660 720 790 621 15 m 50 ft 970 1000 1030 1120 1220 985 6000 1829 Ground Roll 660 680 700 770 850 659 15 m 50 ft 1020 1050 1080 1190 1300 1029 7000 2134 Ground Roll 720 740 770 860 940 ...

Page 336: ...nd Roll 490 510 530 560 620 680 504 15 m 50 ft 850 870 900 940 1040 1130 867 4000 1219 Ground Roll 540 560 580 630 690 760 553 15 m 50 ft 910 930 960 1020 1120 1230 922 5000 1524 Ground Roll 590 610 630 690 760 595 15 m 50 ft 960 990 1010 1100 1210 969 6000 1829 Ground Roll 630 650 670 740 810 632 15 m 50 ft 1010 1040 1070 1170 1280 1012 7000 2134 Ground Roll 690 710 740 820 900 688 15 m 50 ft 107...

Page 337: ...ound Roll 470 490 500 530 590 640 482 15 m 50 ft 840 860 880 930 1020 1110 854 4000 1219 Ground Roll 520 540 550 590 660 720 529 15 m 50 ft 890 920 940 1010 1100 1200 907 5000 1524 Ground Roll 560 580 600 650 720 564 15 m 50 ft 940 970 990 1080 1180 950 6000 1829 Ground Roll 600 620 640 710 780 600 15 m 50 ft 990 1020 1040 1150 1260 991 7000 2134 Ground Roll 660 680 710 780 860 655 15 m 50 ft 1050...

Page 338: ... Ground Roll 450 460 480 500 560 610 456 15 m 50 ft 780 800 820 860 950 1040 793 4000 1219 Ground Roll 490 510 530 560 620 680 500 15 m 50 ft 830 850 880 940 1030 1120 842 5000 1524 Ground Roll 530 550 570 620 680 537 15 m 50 ft 880 900 930 1000 1100 885 6000 1829 Ground Roll 570 590 610 670 740 570 15 m 50 ft 920 950 970 1070 1170 923 7000 2134 Ground Roll 620 650 670 750 820 622 15 m 50 ft 980 1...

Page 339: ...14 Ground Roll 430 440 460 480 530 580 435 15 m 50 ft 770 790 810 850 930 1020 781 4000 1219 Ground Roll 470 490 500 530 590 650 477 15 m 50 ft 820 840 860 920 1010 1100 828 5000 1524 Ground Roll 510 520 540 590 650 512 15 m 50 ft 860 880 910 980 1080 869 6000 1829 Ground Roll 540 560 580 640 700 539 15 m 50 ft 900 930 950 1040 1140 904 7000 2134 Ground Roll 590 610 640 710 780 590 15 m 50 ft 960 ...

Page 340: ...914 Ground Roll 400 410 430 460 500 550 410 15 m 50 ft 750 770 790 840 920 1000 767 4000 1219 Ground Roll 440 460 470 510 560 610 449 15 m 50 ft 800 820 840 900 990 1080 811 5000 1524 Ground Roll 480 490 510 550 610 482 15 m 50 ft 840 870 890 960 1050 851 6000 1829 Ground Roll 510 520 540 600 660 513 15 m 50 ft 880 910 930 1020 1120 886 7000 2134 Ground Roll 560 580 610 670 740 559 15 m 50 ft 940 ...

Page 341: ...000 914 Ground Roll 710 730 760 800 880 970 725 15 m 50 ft 1090 1120 1150 1210 1330 1450 1110 4000 1219 Ground Roll 800 830 860 920 1020 1120 818 15 m 50 ft 1190 1220 1260 1350 1480 1620 1209 5000 1524 Ground Roll 890 920 950 1030 1140 898 15 m 50 ft 1280 1320 1360 1470 1610 1295 6000 1829 Ground Roll 960 990 1030 1140 1250 967 15 m 50 ft 1360 1400 1440 1590 1740 1370 7000 2134 Ground Roll 1070 11...

Page 342: ...000 914 Ground Roll 680 700 720 760 840 930 694 15 m 50 ft 1070 1100 1130 1190 1310 1430 1094 4000 1219 Ground Roll 770 800 820 880 970 1070 783 15 m 50 ft 1170 1200 1240 1320 1450 1590 1190 5000 1524 Ground Roll 850 870 900 990 1090 860 15 m 50 ft 1260 1290 1330 1440 1580 1272 6000 1829 Ground Roll 910 950 980 1080 1190 920 15 m 50 ft 1330 1370 1410 1560 1710 1342 7000 2134 Ground Roll 1020 1060 ...

Page 343: ...3000 914 Ground Roll 650 660 690 730 800 880 659 15 m 50 ft 1050 1080 1110 1170 1290 1410 1076 4000 1219 Ground Roll 730 760 780 840 920 1020 743 15 m 50 ft 1150 1180 1220 1300 1430 1560 1167 5000 1524 Ground Roll 800 830 860 940 1030 816 15 m 50 ft 1230 1270 1300 1410 1550 1246 6000 1829 Ground Roll 870 900 930 1030 1130 880 15 m 50 ft 1310 1340 1380 1520 1670 1317 7000 2134 Ground Roll 970 1010 ...

Page 344: ...3000 914 Ground Roll 610 630 650 690 770 840 627 15 m 50 ft 990 1020 1050 1100 1210 1320 1012 4000 1219 Ground Roll 690 720 740 800 880 960 706 15 m 50 ft 1080 1110 1140 1220 1340 1460 1097 5000 1524 Ground Roll 760 790 820 890 980 774 15 m 50 ft 1160 1190 1230 1330 1460 1171 6000 1829 Ground Roll 830 860 880 980 1080 834 15 m 50 ft 1230 1270 1300 1430 1570 1237 7000 2134 Ground Roll 920 960 1000 ...

Page 345: ... 3000 914 Ground Roll 580 600 620 660 730 790 597 15 m 50 ft 980 1000 1030 1090 1190 1300 997 4000 1219 Ground Roll 660 680 700 760 830 910 667 15 m 50 ft 1060 1090 1120 1200 1310 1440 1075 5000 1524 Ground Roll 720 750 780 840 930 732 15 m 50 ft 1130 1170 1200 1300 1430 1146 6000 1829 Ground Roll 780 810 840 920 1010 789 15 m 50 ft 1200 1240 1270 1400 1530 1209 7000 2134 Ground Roll 880 910 950 1...

Page 346: ...98 3000 914 Ground Roll 550 570 590 620 680 750 563 15 m 50 ft 960 990 1010 1070 1170 1280 979 4000 1219 Ground Roll 620 640 660 710 780 860 629 15 m 50 ft 1040 1070 1100 1170 1290 1410 1053 5000 1524 Ground Roll 680 710 730 790 870 690 15 m 50 ft 1110 1140 1170 1270 1390 1120 6000 1829 Ground Roll 740 760 790 870 960 744 15 m 50 ft 1170 1210 1240 1360 1500 1181 7000 2134 Ground Roll 830 860 900 9...

Page 347: ...3000 914 Ground Roll 1700 1750 1800 1900 2100 2300 1723 15 m 50 ft 2850 2900 3000 3150 3450 3750 2882 4000 1219 Ground Roll 1850 1950 2000 2150 2350 2600 1893 15 m 50 ft 3050 3100 3200 3400 3750 4100 3069 5000 1524 Ground Roll 2000 2100 2150 2350 2600 2036 15 m 50 ft 3200 3300 3400 3650 4050 3231 6000 1829 Ground Roll 2150 2250 2300 2550 2800 2162 15 m 50 ft 3350 3450 3550 3900 4300 3375 7000 2134...

Page 348: ...l 1600 1700 1750 1850 2050 2250 1652 15 m 50 ft 2800 2850 2950 3100 3400 3700 2842 4000 1219 Ground Roll 1800 1850 1900 2050 2250 2500 1814 15 m 50 ft 3000 3050 3150 3350 3700 4050 3022 5000 1524 Ground Roll 1950 2000 2100 2250 2500 1952 15 m 50 ft 3150 3250 3350 3600 3950 3178 6000 1829 Ground Roll 2050 2150 2200 2450 2700 2073 15 m 50 ft 3300 3400 3500 3850 4200 3319 7000 2134 Ground Roll 2250 2...

Page 349: ...l 1550 1600 1650 1750 1950 2100 1580 15 m 50 ft 2750 2850 2900 3050 3350 3650 2801 4000 1219 Ground Roll 1700 1800 1800 1950 2150 2350 1735 15 m 50 ft 2950 3000 3100 3300 3650 3950 2974 5000 1524 Ground Roll 1850 1900 1950 2150 2350 1850 15 m 50 ft 3100 3200 3250 3550 3900 3116 6000 1829 Ground Roll 1950 2050 2100 2350 2550 1966 15 m 50 ft 3250 3350 3450 3750 4150 3252 7000 2134 Ground Roll 2150 2...

Page 350: ...l 1450 1500 1550 1650 1850 2000 1494 15 m 50 ft 2550 2650 2700 2850 3100 3400 2602 4000 1219 Ground Roll 1600 1700 1750 1850 2050 2250 1638 15 m 50 ft 2750 2800 2900 3100 3400 3700 2763 5000 1524 Ground Roll 1750 1800 1900 2050 2250 1760 15 m 50 ft 2900 2950 3050 3300 3600 2902 6000 1829 Ground Roll 1850 1950 2000 2200 2450 1868 15 m 50 ft 3000 3100 3200 3500 3850 3028 7000 2134 Ground Roll 2050 2...

Page 351: ...l 1400 1450 1500 1600 1750 1900 1425 15 m 50 ft 2500 2600 2650 2800 3050 3350 2562 4000 1219 Ground Roll 1550 1600 1650 1750 1950 2150 1562 15 m 50 ft 2700 2750 2850 3000 3300 3600 2716 5000 1524 Ground Roll 1650 1700 1800 1950 2150 1679 15 m 50 ft 2850 2900 3000 3250 3550 2851 6000 1829 Ground Roll 1750 1850 1900 2100 2300 1766 15 m 50 ft 2950 3050 3150 3450 3750 2963 7000 2134 Ground Roll 1950 2...

Page 352: ...l 1300 1350 1400 1500 1650 1800 1342 15 m 50 ft 2500 2550 2600 2750 3000 3300 2514 4000 1219 Ground Roll 1450 1500 1550 1700 1850 2000 1471 15 m 50 ft 2650 2700 2800 2950 3250 3550 2661 5000 1524 Ground Roll 1600 1650 1700 1850 2000 1581 15 m 50 ft 2750 2850 2900 3150 3450 2789 6000 1829 Ground Roll 1700 1750 1800 2000 2200 1681 15 m 50 ft 2900 3000 3050 3350 3700 2907 7000 2134 Ground Roll 1850 1...

Page 353: ...297 3000 914 Ground Roll 2350 2400 2500 2650 2900 3200 2376 15 m 50 ft 3550 3650 3800 4000 4350 4800 3640 4000 1219 Ground Roll 2650 2750 2850 3050 3350 3700 2683 15 m 50 ft 3900 4000 4150 4400 4850 5300 3966 5000 1524 Ground Roll 2900 3000 3100 3400 3750 2946 15 m 50 ft 4200 4350 4450 4850 5300 4248 6000 1829 Ground Roll 3150 3250 3400 3750 4100 3173 15 m 50 ft 4500 4600 4750 5200 5750 4495 7000 ...

Page 354: ...260 3000 914 Ground Roll 2250 2300 2400 2500 2750 3050 2276 15 m 50 ft 3500 3600 3700 3900 4300 4700 3589 4000 1219 Ground Roll 2550 2600 2700 2900 3200 3500 2569 15 m 50 ft 3850 3950 4050 4350 4750 5200 3902 5000 1524 Ground Roll 2800 2850 2950 3250 3600 2820 15 m 50 ft 4150 4250 4350 4750 5200 4173 6000 1829 Ground Roll 3000 3100 3250 3550 3950 3018 15 m 50 ft 4400 4500 4650 5100 5600 4401 7000 ...

Page 355: ...222 3000 914 Ground Roll 2150 2200 2250 2400 2650 2900 2160 15 m 50 ft 3450 3550 3650 3850 4250 4650 3529 4000 1219 Ground Roll 2400 2500 2550 2750 3050 3350 2437 15 m 50 ft 3750 3900 4000 4250 4700 5100 3828 5000 1524 Ground Roll 2650 2750 2850 3100 3400 2676 15 m 50 ft 4050 4150 4300 4650 5100 4087 6000 1829 Ground Roll 2900 2950 3050 3400 3700 2886 15 m 50 ft 4300 4400 4550 5000 5500 4319 7000 ...

Page 356: ...026 3000 914 Ground Roll 2000 2100 2150 2300 2500 2750 2055 15 m 50 ft 3250 3350 3450 3650 4000 4350 3320 4000 1219 Ground Roll 2300 2350 2450 2650 2900 3150 2315 15 m 50 ft 3550 3650 3750 4000 4400 4800 3599 5000 1524 Ground Roll 2500 2600 2700 2900 3200 2538 15 m 50 ft 3800 3900 4050 4350 4800 3842 6000 1829 Ground Roll 2750 2850 2900 3200 3550 2734 15 m 50 ft 4050 4150 4300 4700 5150 4058 7000 ...

Page 357: ...989 3000 914 Ground Roll 1900 2000 2050 2150 2400 2600 1958 15 m 50 ft 3200 3300 3400 3550 3900 4300 3269 4000 1219 Ground Roll 2150 2250 2300 2500 2750 3000 2188 15 m 50 ft 3500 3600 3700 3950 4300 4700 3527 5000 1524 Ground Roll 2400 2450 2550 2750 3050 2399 15 m 50 ft 3700 3850 3950 4250 4700 3758 6000 1829 Ground Roll 2600 2650 2750 3050 3350 2586 15 m 50 ft 3950 4050 4200 4600 5050 3966 7000 ...

Page 358: ...945 3000 914 Ground Roll 1800 1900 1950 2050 2250 2450 1846 15 m 50 ft 3150 3250 3350 3500 3850 4200 3210 4000 1219 Ground Roll 2050 2100 2200 2350 2600 2850 2062 15 m 50 ft 3400 3500 3600 3850 4250 4650 3454 5000 1524 Ground Roll 2250 2350 2400 2600 2850 2261 15 m 50 ft 3650 3750 3850 4200 4600 3674 6000 1829 Ground Roll 2450 2500 2600 2850 3150 2439 15 m 50 ft 3850 3950 4100 4500 4900 3874 7000 ...

Page 359: ...nded Airspeed vREF The climb performance charts show the rate of climb The gradient and angle of climb can be calculated using the following formula NOTE The angles of climb at MSL and ISA condition are 2 7 for Maximum Take Off Mass 2300 kg 5071 lb 4 3 for 1999 kg 4407 lb Page 5 88 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 360: ...300 280 240 195 145 70 261 2 4 2 8 0 5 0 0 SL 505 490 480 465 440 400 350 275 459 2000 610 480 465 450 435 410 365 305 240 432 4000 1219 450 435 415 400 370 320 255 180 405 6000 1829 415 400 380 365 330 270 205 375 8000 2438 380 360 345 320 265 200 130 345 10000 3048 345 320 280 240 185 105 305 2 4 1 6 0 3 0 0 SL 555 540 530 515 485 445 395 315 507 2000 610 530 515 500 480 455 410 350 275 480 4000...

Page 361: ...525 505 465 425 370 280 489 1 4 9 1 0 8 0 9 SL 735 720 710 695 670 630 575 485 691 2000 610 710 695 685 670 650 605 530 445 670 4000 1219 685 670 660 640 610 555 475 380 646 6000 1829 660 640 620 605 570 495 415 616 8000 2438 620 600 585 555 505 425 340 584 10000 3048 580 560 520 480 420 320 545 1 3 8 9 0 6 0 8 SL 795 785 770 760 735 695 635 535 754 2000 610 775 760 745 735 710 665 585 490 733 400...

Page 362: ...nce 5 3 14 APPROVED NOISE DATA Max Flight Mass 1999 kg 4407 lb ICAO Annex 16 Chapter X App 6 73 9 dB A Max Flight Mass 2300 kg 5071 lb ICAO Annex 16 Chapter X App 6 77 5 dB A Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 5 91 ...

Page 363: ...Performance DA 62 AFM Intentionally left blank Page 5 92 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 364: ...REPORT 6 4 6 4 FLIGHT MASS AND CENTER OF GRAVITY 6 6 6 4 1 MOMENT ARMS 6 9 6 4 2 LOADING DIAGRAMS 6 10 6 4 3 CALCULATION OF LOADING CONDITION 6 12 6 4 4 PERMISSIBLE CENTER OF GRAVITY RANGE 6 15 6 4 5 PERMISSIBLE MOMENT RANGE 6 17 6 5 EQUIPMENT LIST AND EQUIPMENT INVENTORY 6 18 Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 6 1 ...

Page 365: ...ed in this chapter Additionally a comprehensive list of the equipment approved for this airplane exists Equipment List The set of items marked as installed constitutes the Equipment Inventory Before the airplane is delivered the empty mass and the corresponding CG position are determined and entered in Section 6 3 MASS AND BALANCE REPORT NOTE Following equipment changes the new empty mass and the ...

Page 366: ...axis and in front of the airplane as seen from the direction of flight The airplane s longitudinal axis is parallel with the floor of the nose baggage compartment When the floor of the nose baggage compartment is aligned horizontally the Datum Plane is vertical The Datum Plane is located 2 196 meters 86 46 in forward of the most forward point of the root rib on the stub wing Doc No 11 01 05 E Rev ...

Page 367: ...ment thecurrent emptymassand the corresponding CG position ormoment in accordance with the Mass and Balance Report must always be used Condition of the airplane for establishing the empty mass Equipment as per Equipment Inventory see Section 6 5 Including the following operating fluids brake fluid hydraulic fluid for the retractable landing gear engine oil 2 x 7 liters 2 x 7 4 qts coolant 2 x 7 5 ...

Page 368: ...empty mass Mo ment Mo ment Arm Mass Registration Changes in mass Subtraction Mo ment Mo ment Arm Mass Serial No Addition Mo ment Mo ment Arm Mass D A 62 Description of part or Modification Upon delivery Entry No OUT IN Date Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 6 5 ...

Page 369: ...NG CONDITION 2 Read the fuel quantity indicators to determine the fuel quantity in the main fuel tanks 3 Determine the fuel quantity in the auxiliary fuel tanks If MÄM 62 254 is NOT installed To verify an empty auxiliary fuel tank set the ELECT MASTER switch and the AUX PUMP switch to ON and check the PFD for the L R AUX FUEL E caution message To verify a full auxiliary fuel tank open the auxiliar...

Page 370: ... 254 is NOT installed 4 Multiply the individual masses by the moment arms quoted to obtain the moment for every item of loading and enter these moments in the appropriate boxes in Table 6 4 3 CALCULATION OF LOADING CONDITION 5 Add up the masses and moments in the respective columns The CG position is calculated bydividingthe totalmomentbythetotalmass usingrow11 forthe condition with empty fuel tan...

Page 371: ...of loading are added Then Diagram 6 4 5 PERMISSIBLE MOMENT RANGE is used to check whether the total moment associated with the total mass is in the permissible range The result found with the graphical method is however inaccurate In doubtful cases the result must be verified using the exact method given above Page 6 8 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 372: ...0 126 0 De Icing fluid tank in LH nose baggage compartment 0 90 35 4 Baggage in compartments LH Nose baggage compartment 0 47 18 5 RH Nose baggage compartment 0 05 2 0 Rear baggage compartment Section A if OÄM 62 019 is NOT installed 4 06 159 8 Rear baggage compartment Sections B C D if OÄM 62 019 is NOT installed 4 18 164 4 Rear baggage compartment Section E if OÄM 62 019 is installed 4 41 173 6 ...

Page 373: ...G DIAGRAMS Page 6 10 Rev 0 11 Jan 2019 Doc No 11 01 05 E 25 50 100 125 150 175 200 225 250 75 lb kg Load Mass 10 000 20 000 30 000 40 000 50 000 60 000 70 000 100 200 300 400 500 600 700 800 kgm in lb Load Moment Fuel Quantity US gal liters ...

Page 374: ...DA 62 AFM Mass and Balance Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 6 11 Load Mass lb kg 25 50 50 kgm 10 000 Load Moment in lb 20 000 100 200 0 0 ...

Page 375: ...oading condition is allowable Our example shows allowable loading conditions NOTE If the optional de icing system OÄM 62 002 is installed the following must be observed The consumption of fuel causes a forward movement of the CG The consumption of de icing fluid causes a rearward movement of the CG Dependingon thefuelflowandde icing fluid flow the overall movement of the CG can be a forward or a r...

Page 376: ...Lever arm 0 47 m 18 5 in 30 66 14 1 1 224 6 RH Nose baggage compt Lever arm 0 05 m 2 0 in 30 66 1 5 130 7 Rear baggage compt Section A Lever arm 4 06 m 159 8 in 0 0 0 0 0 8 Rear baggage compt Sections B C D F Lever arm 4 18 m 164 5 in 0 0 0 0 0 9 Rear baggage compt Section E Lever arm 4 41 m 173 6 in 5 11 22 05 1 914 10 De Icing fluid 1 1 kg L 9 02 lb US gal Lever arm 0 90 m 35 4 in 10 22 9 0 781 ...

Page 377: ...auxiliary tanks if installed 0 84 kg liter 7 01 lb US gal Lever arm 3 2 m 126 in 116 256 371 2 32 219 14 Total mass total moment with fuel Total of 11 13 2241 4940 5611 55 487 061 The CG s shown in the following diagrams are those from the example in Section 6 4 3 CALCULATION OF LOADING CONDITION rows 11 and 14 Page 6 14 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 378: ...ev 0 11 Jan 2019 Page 6 15 Flight Mass kg 1550 1600 1650 1700 1750 1800 2 40 2 45 Center of Gravity Position m 2 35 2 50 Flight Mass lb Center of Gravity Position in 94 93 92 95 96 97 98 1850 1900 2000 1950 2050 2100 2150 2200 2250 2300 2350 99 100 101 91 2 55 If MÄM 62 001 is carried out ...

Page 379: ...968 lb 2 460 m 96 85 in aft of datum plane at max take off mass see Section 2 7 linear variation in between Most rearward flight CG 2 460 m 96 85 in aft of datum plane at 1600 kg 3527 lb 2 510 m 98 82 in aft of datum plane at 1900 kg 4189 lb to 1999 kg 4407 lb 2 530 m 99 61 in aft of datum plane at MTOM linear variation in between Page 6 16 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 380: ...F LOADING CONDITION rows 11 and 14 Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 6 17 2050 1600 1650 1700 1750 1800 Flight Mass lb Flight Mass Moment kg m Flight Mass Moment in lb 1850 1900 4300 4400 4500 4200 4100 4000 3900 3800 3700 5300 5200 5100 4600 4700 4800 4900 5000 1950 2000 2150 2100 2200 2300 2250 5800 5700 5600 5400 5500 If MÄM 62 001 is carried out ...

Page 381: ...not be installed in any arbitrary combination The airplane manufacturer must be contacted before removing or installing equipment with the exception of replacing a unit by an identical unit The itemsof equipment installedin yourparticularairplane are indicatedin the appropriate column The set of items marked as installed constitutes the Equipment Inventory Page 6 18 Rev 0 11 Jan 2019 Doc No 11 01 ...

Page 382: ...pace AUTOPILOT SYSTEM Pitch servo GSA 81 011 00878 20 Garmin Pitch servo mount GSM 86 011 01904 03 Garmin Pitch clutch cartridge 011 02147 11 Garmin Roll servo GSA 81 011 00878 20 Garmin Roll servo mount GSM 86 011 01904 03 Garmin Roll clutch cartridge 011 02147 09 Garmin Pitch trim servo GSA 81 011 00878 20 Garmin Pitch trim servo mount GSM 86 011 01904 03 Garmin Pitch trim clutch cartridge 011 0...

Page 383: ...4184 XPZL987 Diamond Aircraft Additional Alternator Regulator VR2000_28 1 Electrosystems Inc OXYGEN SYSTEM Oxygen cylinder empty incl pressure regulator 4110 122 3 11 Aerox 13 76 6 24 31 9 0 81 Oxygen cylinder 50 cuft empty incl pressure regulator 4110 136 02 5 Aerox 8 60 3 90 27 8 0 70 Single outlet manifold Pax row I 4110 401 2 01 Aerox 0 22 0 10 111 0 2 82 Double outlet manifold Pilot copilot 4...

Page 384: ...26 800 3 220 Safety belt Center pax row I 5 02 Series 5 02 BL57 Schroth 2 250 1 020 126 800 3 220 Safety belt LH pax row II 5 02 Series 5 02 BP57 Schroth 2 250 1 020 126 800 3 220 Safety belt RH pax row II 5 02 Series 5 02 BP07 Schroth 2 250 1 020 126 800 3 220 ELT unit 406 AF Compact S1840501 01 Kannad 1 874 0 874 179 700 4 565 ELT remote switch RC 200 S1820513 11 Kannad ELT antenna ANT300 012422...

Page 385: ...raulic cylinder RH X11 0006 00 00 00 1R0 Hydraulik Mayer NLG hydraulic cylinder X11 0006 00 00 00 3 Hydraulik Mayer Brake master cylinder 4 pcs 10 54A Cleveland Parking valve 60 5D Cleveland Brake assembly 30 233 E Cleveland INDICATING REC SYSTEM Primary flight display PFD GDU 1040 011 00972 03 Garmin Multi function display MFD GDU 1045 011 00819 04 Garmin Primary flight display PFD GDU 1040 011 0...

Page 386: ...1 Birk Aerosystems Strobe Pos light assy RH D67 5732 29 01 Birk Aerosystems Map Reading lights 4 pcs RL6961 1 Birk Aerosystems Cabin Light RL6980 1 Birk Aerosystems Taxi light Xenon D1S Aero Vision Int Taxi light power supply XV4D 35 XeVision Landing light Xenon D1S Aero Vision Int Landing light power supply XV4D 35 XeVision Glareshield lamp assy DA4 3311 10 02 Diamond Aircraft Glareshield light i...

Page 387: ...str Standby Attitude Module MD302 6420302 1 Mid Continent Instr Magnetic compass PG2C 28V SIRS Navigation Magnetic compass NV2C 28V SIRS Navigation OAT probe GTP 59 011 00978 00 Garmin Digital air data system GDC74A 011 00882 00 Garmin Digital air data system GDC 74A 011 00882 10 Garmin Digital air data system GDC 72 011 03734 00 Garmin Integrated avionics 1 GIA 63 W 011 01105 20 Garmin Integrated...

Page 388: ...1 00870 10 Garmin Dual VOR dual GS duplexer CI 1125 Comant LH VOR LOC GS antenna CI120 1 Comant RH VOR LOC GS antenna CI120 1 Comant VOR LOC GS PWR combiner CI120 3 Comant Transponder antenna KA 61 071 00221 0010 Bendix King Marker antenna CI 102 Comant GPS 1 antenna GA 36 013 00244 00 Garmin GPS 2 antenna Cl 2580 200 Comant DME KN 63 066 1070 01 Bendix King DME antenna KA 61 071 00221 0010 Bendix...

Page 389: ...V Aerospace Porous Panel horizontal tail RH 15502 10 CAV Aerospace Porous Panel vertical tail 15502 11 CAV Aerospace Inlet strainer D67 9030 03 01_01 FTEU Spray bar 12124 10 CAV Aerospace Metering pump 1 9513T 1 CAV Aerospace 4 16 1 89 41 5 1 05 Metering pump 2 9513U 1 CAV Aerospace 4 16 1 89 35 7 0 91 De icing fluid tank D67 3003 13 01 Diamond Aircraft 7 72 3 50 37 4 0 95 Fluid filter F932 Diamon...

Page 390: ...200 000 Austro Engine Starter LH RH E4A 93 000 000 Austro Engine ELECTRICAL POWER LH alternator E4A 91 400 000 Austro Engine RH alternator E4A 91 400 000 Austro Engine LH alternator regulator E4A 91 200 000 Austro Engine RH alternator regulator E4A 91 200 000 Austro Engine ENGINE FUEL PUMPS LH fuel pumps 2x 0 580 054 001 Bosch RH fuel pumps 2x 0 580 054 001 Bosch ENGINE FIRE WARNING LH overheat de...

Page 391: ...eathering accumulator LH P 893 3 mt propeller Unfeathering accumulator RH P 893 3 mt propeller Governor LH P 877 16 mt propeller Governor RH P 877 16 mt propeller FUEL TANK SYSTEM Fuel probe assy LH inboard D60 2817 13 00_1 Diamond Aircraft Fuel probe assy RH inboard D60 2817 13 00_1 Diamond Aircraft Fuel probe assy LH outboard D60 2817 14 00_1 Diamond Aircraft Fuel probe assy RH outboard D60 2817...

Page 392: ...dair RH fuel inline filter FX375 MK Adair LH solenoid valve VE 131 4 GV Parker RH solenoid valve VE 131 4 GV Parker Aux tank fuel probe D67 2814 70 00 Diamond Aircraft AIRPLANE FLIGHT MANUAL Doc No 11 01 05 E Diamond Aircraft Place _______________________ Date ___________________________ Signature ______________________________ Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 6 29 ...

Page 393: ...S 7 21 7 7 2 REAR BAGGAGE COMPARTMENT 7 21 7 8 FRONT DOORS REAR DOOR AND CABIN INTERIOR 7 27 7 9 POWER PLANT 7 31 7 9 1 ENGINES GENERAL 7 31 7 9 2 PROPELLER 7 32 7 9 3 OPERATING CONTROLS 7 35 7 9 4 ENGINE INSTRUMENTS 7 39 7 9 5 FUEL SYSTEM 7 42 7 9 6 COOLING SYSTEM 7 58 7 9 7 OIL SYSTEMS 7 59 7 9 8 TURBO CHARGER SYSTEM 7 60 7 9 9 FIRE DETECTION SYSTEM 7 61 7 10 ELECTRICAL SYSTEM 7 62 7 10 1 GENERA...

Page 394: ... 7 80 7 13 3 MULTI FUNCTION DISPLAY MFD 7 82 7 13 4 AUDIO PANEL 7 83 7 13 5 ATTITUDE AND HEADING REFERENCE SYSTEM AHRS 7 83 7 13 6 AIR DATA COMPUTER ADC 7 83 7 13 7 GWX 70 WEATHER RADAR 7 83 7 13 8 PFD MFD CONTROL UNIT KEYPAD 7 84 7 14 AVIONICS 7 85 7 14 1 AUTOPILOT SYSTEM 7 85 7 14 2 AUTOMATIC FLIGHT CONTROL SYSTEM ANNUNCIATIONS AND ALERTS 7 91 7 15 MID CONTINENT MD302 STANDBY ATTITUDE MODULE 7 9...

Page 395: ...rated from the other structure with a firewall The fire protection on the firewall is of a special fire resistant matting which is covered on the engine side by stainless steel cladding Wings The wings have a front and rear spar each wing has a top shell and a bottom shell the whole wing is fail safe design The wings as well as the ailerons and flaps are made of GFRP CFRP and are principally of sa...

Page 396: ...ence of this roll pin can lead to the loss of the hinge pin and a consequent loss of flight safety Operation Each aileron is connected with a aileron control horn to the push rods of the aileron control system A rod end bearing is screwed into a steel push rod and locked by means of a jam nut which has locking varnish applied to it Damage to this varnish can indicate a twisting and thus a change t...

Page 397: ...ed with a flap control horn to the push rods of the flap control system A rod end bearing is screwed into a steel push rod and locked by means of a jam nut which has locking varnish applied to it Damage to this varnish can indicate a twisting and thus a change to the adjustment The connection between the rod end bearing and the control horn is a bolt the nut of which is likewise sealed with lockin...

Page 398: ...nning the end positions The electrical flap drive has an automatic circuit breaker which can also be operated manually Flap Position Indicator The current flap position is indicated by means of three lights beside the flap selector switch When the upper light green is illuminated the flaps are in the Cruise position UP when the center light white is illuminated the flaps are in Take Off position T...

Page 399: ...teel pushrods Two of the bellcrank bearings are accessible for visual inspection next to the lower hinge of the rudder The elevator horn and its bearing as well as the connection to the pushrod can be visually inspected at the upper end of the rudder Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 7 ...

Page 400: ...der stops held by 4 screws to the rear web of the vertical stabilizer The mating part on the rudder is a bracket which is attached to the rudder by 2 bolts The bolts and nuts are accessible to visual inspection Operation Steelcables the eyes of which are connected to the boltson thebracket Page 7 8 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 401: ...evice A mark on the wheel shows the take off T O position Turn wheel to the front nose down Turn wheel to the rear nose up Rudder Trim The trim control isa blackwheelin the center console below the instrument panel A mark on the wheel shows the center position and the direction of movement Turn wheel to the right right turn Turn wheel to the left left turn Doc No 11 01 05 E Rev 0 11 Jan 2019 Page ...

Page 402: ...e of the instrument panel Forward Adjustment To move the pedals forward depress upper side of switch When pedals are in correct position release switch Rearward Adjustment To move the pedals in the rearward direction depress lower side of switch When pedals are in correct position release switch Locking Upon release the switch moves automatically to the power off position so locking the pedals in ...

Page 403: ...h operation bring the switch back to the desired position typically AUTO Cockpit Ventilation Ventilation in the front is provided by spherical ventilation nozzles 16 in the instrument panel Furthermore there are spherical nozzles on the central console above the pilot s and passengers heads The spherical nozzles are opened and closed by twisting Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 11 ...

Page 404: ...t lighting and flood light 25 Multi function display MFD 10 Light switches 26 De Ice control panel 11 27 Autopilot control unit part of MFD 12 Flap selector switch 28 Alt air lever 13 Landing gear switch 29 Landing gear emergency extension lever 14 Alternate static valve 30 Oxygen pressure indicator 15 Microphone socket 31 16 Ventilation nozzles 32 Fuel pump switches Designations and abbreviations...

Page 405: ... retracted position A pressurized gas container actsasan accumulatorwhich keepsthesystempressureconstantbyreplacingthe volume lost due to the normal actuator leakages This prevents a permanent starting of the hydraulic pump in flight Springs assist the hydraulic system in gear extension and locking the gear in the down position After the gears are down and the downlock hooks engage springs maintai...

Page 406: ...ty will allow the gear to extend if the system fails for any reason To extend and lock the gears in the event of failure it is only necessary to relieve the hydraulic pressure by means of the emergency gear extension lever which is located under the instrument panel to the left of the center console Pulling this lever releases the hydraulic pressure and allows the gear to fall free Before pulling ...

Page 407: ...em conditions for each operating mode The first figure below shows the extension of the landing gear is shown Toreduce the amount of pumpedhydraulic fluid during this operation the return flowispartlyledintothefeeding flow of the system The figure belowshowsthesystem statuswhen the landinggearisextended Allhydraulic cylinders are under high pressure Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 15 ...

Page 408: ...ydraulic system is started due to different piston areas of the landing gear cylinders although thepressureonbothsides of the system is equal While the landing gear is retracted both valves are energized and excess hydraulic fluid on one side is drained into the tank This configuration of the system is shown in the following figure Page 7 16 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 409: ...gency extension of the landing gear the hydraulic fluid can pass through an emergency extension valve so that the gear is extended by gravity The condition of the system is shown in the figure below Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 17 ...

Page 410: ...ver is located on the small center console under the instrument panel and is in the upper position when the brakes are released To operate the parking brake pull the lever downwards until it catches Brake pressure is built up by multiple operation of the toe brake pedals and is maintained until the parking brake is released To release the lever is pushed upwards Page 7 18 Rev 0 11 Jan 2019 Doc No ...

Page 411: ...installed the two passenger seats of row II may be installed The backrest of the passenger seats row II can be laid forward after pulling the release lever upwards In case of an emergency the LH seat backrest can be released by pulling the red handle on the back side of the seat pan of the LH passenger seat of row I The front seats have adjustable backrests installed The angle of the backrests and...

Page 412: ...hanism may result Foradjustment pressthebuttonandbend thebackrest forwardorbackward tothe desired backrest angle For fixing the position release the button In case of a malfunction of the release button the backrest can be moved into the upright position by pulling the backrest 480 N in flight FWD direction Page 7 20 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 413: ...the floor level up to the upper edge of the forward compartment bulkhead Forward shifting of items is prevented by the bulkhead Place heavy items in Zone C Zone D is the volume above Zone C up to the ceiling Baggage must be secured at all times by means of the approved baggage net Only baggage net attachment configuration in accordance with Figures 1 through 3 may be used Always use the most suita...

Page 414: ...Airplane Description DA 62 AFM Figure 1 Rear Baggage Compartment I Page 7 22 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 415: ...DA 62 AFM Airplane Description Figure 2 Rear Baggage Compartment II Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 23 ...

Page 416: ...Airplane Description DA 62 AFM Figure 3 Rear Baggage Compartment III Page 7 24 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 417: ...DA 62 AFM Airplane Description Figure 4 Rear Baggage Compartment IV if OÄM 62 019 is carried out Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 25 ...

Page 418: ...Airplane Description DA 62 AFM Figure 5 Rear Baggage Compartment V if OÄM 62 019 is carried out Page 7 26 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 419: ... holes in polyethylene blocks A gas pressure damper prevents each pilot door from dropping in strong winds the assemblies must be securely held The pilot doors can be blocked by a locking device on the each side near the opening levers by turning the key clockwise The closed and blocked doors can be opened from inside by pulling the levers inside the opening handle A window on the each pilot door ...

Page 420: ...nger door is protected against unintentional opening by an additional lever The door can be blocked by a locking device on the left side near the external door opening lever by turning the key clockwise The closed and blocked door can be opened from inside by pulling the lever inside the opening handle WARNING Do not block the door with the locking key before flight in order to assure emergency ac...

Page 421: ...creen The air inlet for the ventilation system is placed on the underside of the RH wing inboard of the engine nacelle The air is distributed within the cabin via 4 nozzles 2 on the instrument panel LH RH side 2 on the overhead panel The jet direction of each cone can be changed easily and the jet intensity can be regulated by rotation of the nozzle CAUTION Do not inadvertently operate the VOTER s...

Page 422: ...co pilot s seat If the doors can not be openedincase of an emergency use the Egress Hammer to break through the door windows WARNING Make sure not to harm other persons by using the Egress Hammer WARNING Beware of sharp edges and fragments of the broken window Page 7 30 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 423: ...with intercooler Displacement Max power 132 0 kW 177 0 DIN HP at 2300 RPM at sea level and ISA Max continuous power 126 kW 169 0 DIN HP at sea level and ISA The indicationsformonitoringimportantengineparametersduringoperationareintegrated within the Garmin G1000 display Each engine can only be operated with the ENGINE MASTER switch ON Each engine has anown ECU ElectricalEngine ControlUnit which re...

Page 424: ...lst minimizing vibration Propeller Control The propeller pitch control system consists of the P 877 16 mt Propeller governor valve The pitch isset bythe ECUvia an electro mechanicalactuatoronthe governor To change the blade pitch angle gearbox oil is pumped into the propeller hub Increasing the oil pressure leads to a decrease of pitch and a higher RPM Decreasing the pressure leads to higher pitch...

Page 425: ...t lock position or moves the propeller blades beyond the start lock position Feathering To feather the propeller the engine must be shut down with the appropriate ENGINE MASTER switch This will open the electric governor valve All oil will flow back from the propeller hub allowing the blades to move into the feathered pitch position At the same time the electricvalve atthe pressure accumulatorclos...

Page 426: ...to a low pitch position As soon as the propeller starts turning and the gearbox oil operates the accumulator will be refilled Ground Operation CAUTION Operation on the ground at high RPM should be avoided as faraspossible asthe blades could suffer stone damage For this reason a suitable site forenginerunsshould be selected where there are no loose stones or similar items WARNING Never move the pro...

Page 427: ...ever is in a low power position as for a landing approach while the landing gear is retracted an aural warning alerts the pilot to the retracted landing gear Additionally a CHECK GEAR caution is indicated on the PFD A propeller governor which is controlled by the ECU is flanged onto the front of each engine The propeller governor oilcircuit issupplied with oil by the gearbox oil pump also see Sect...

Page 428: ... MASTER The ELECT MASTER switch has two positions OFF disconnecting battery power ON connecting battery power to the power distribution system ENGINE MASTER Each engine can only be cranked with its ENGINE MASTER switched to ON When activated the ENGINE MASTER provides the power supply for the preheat system the unfeathering accumulator valve and the engine itself To shut down the engine the approp...

Page 429: ...for each engine Power Lever at IDLE and RPM Below Approximately 900 By pushing and holding the button until the end of the procedure the self test of each engine control unit is started The procedure is possibleon the ground only Otherwise the test will not start During the procedure the ECU performs a switch from ECU A to ECU B or ECU B to ECU A whichever is active at the moment with the propelle...

Page 430: ...s both engines simultaneously is located under the instrument panel to the right of the center console To open the alternate air source the lever is pulled to the rear Normally the alternate air source is closed with the lever in the forward position Placard on the lever forward position ALTERNATE AIR Placard on the lever visible when lever is in the rearward position ALTERNATE AIR ON Page 7 38 Re...

Page 431: ...7 13 3 MULTI FUNCTION DISPLAY MFD Indications for the LH engine are on the left side indications for the RH engine are on the right side Default page Display when pushing Display when pushing Engine the SYSTEM button the FUEL button If MÄM 62 254 is If MÄM 62 254 is NOT installed NOT installed Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 39 ...

Page 432: ...Airplane Description DA 62 AFM Display when pushing the ENGINE button if MÄM 62 254 is installed Page 7 40 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 433: ...wn are numbers which are calculated from the last fuel quantity update done by the pilot and actual fuel flow data Therefore the endurance and range data is for information only and must not be used for flight planning Designation Indication Unit LOAD Available power RPM Propeller RPM 1 min VOLTS Volts V AMPS Ampères A COOLANT TEMP Coolant temperature C GEARBOX Gearbox temperature C OIL TEMP Engin...

Page 434: ...Airplane Description DA 62 AFM 7 9 5 FUEL SYSTEM General Page 7 42 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 435: ... of the fuel system are interconnected by crossfeed lines In each engine nacelle an auxiliary fuel tank may be installed Fuel Pumps Each engine is feed bytwo parallel installed independent electricallydriven lowpressure fuel pumps During normal operation one of the two fuel pumps is working In case of a low fuel pressure failure the ECU switches automatically to the second fuel pump During landing...

Page 436: ...during single engine operation With the fuel selector valve both the feeding and the return line are switched The desired position is reached by pulling the lever back To reach the OFF position a safety guard must be twisted This is to ensure that this selection is not made unintentionally NOTE If one engine is inoperative the fuel selector valve for this engine must be in the OFF position CAUTION...

Page 437: ...erred to the LH engine Depending on the position of the RH fuel selector valve the RH tank then feeds both engines as shown in Figure 4 below or only the LH engine when the fuel selector valve of the RH engine is in shut off position as shown in Figure 5 below Figure 1 Normal Operation Figure 2 Crossfeed Operation Figure 3 Shut off Figure 4 Fuel selector valve RH normal operation position fuel sel...

Page 438: ...Airplane Description DA 62 AFM Page 7 46 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 439: ... tankbut prevents flow of fuel to the outside The capillary equalizes the air pressure during climb The hose terminals are located on the underside of the wing approximately 2 meters 7 ft from the wing tip In each tank a coarse filter finger filter is fitted before the outlet To allow draining of the tank a drain valve is located at the lowest point of the fuel tank At the lowest point on each sid...

Page 440: ... to enter the tank but prevents flow of fuel to the outside The capillary equalizes the air pressure during climb A fuel drain valve is located at the rear of each auxiliary tank Operation Two AUX PUMP switches in the cockpit are used to activate the auxiliary pumps The switches are located behind the elevator trim wheel on the center console Both switches are intended to be used simultaneously to...

Page 441: ...und in Chapter 5 PERFORMANCE When one auxiliary pump is defective the fuel stored in the related auxiliary fuel tank is not available For use of the remaining fuel pump refer to to Section 4B 12 L R FUEL TRANSFER FAIL The flight plan must be amended accordingly The auxiliary pumps are electrically connected to the LH MAIN BUS and protected by a 7 5 A circuit breaker Doc No 11 01 05 E Rev 0 11 Jan ...

Page 442: ...as a recess which fits the airfoil of the wing in front of the fuel tank drain which lies approximately 10 cm 4 in outboard of the engine nacelle The metal connector is pressed against the drain of the tank The amount of fuel in the tank can now be read off from the vertical ascending pipe Foran exactindication the airplane must stand on level ground and the measuring device must be held verticall...

Page 443: ...indicator II must be supported bythe nose baggage compartment for the entire length Read and record the pitch angle Standard Tanks Unfold the fuel indicator II and center it at the nose of wing Read the fuel level on the scale and refer to the tables provided in order to determine the exact fuel quantity Auxiliary Tanks if installed Unfold the fuel indicator II and place it on the trailing edge of...

Page 444: ...Airplane Description DA 62 AFM Fuel Quantity Indicator II Pitch Angle Measurement in Baggage Compartment Page 7 52 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 445: ...DA 62 AFM Airplane Description Fuel Quantity Indicator II Main Tank Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 53 ...

Page 446: ...Airplane Description DA 62 AFM Fuel Quantity Indicator II Aux Tank Page 7 54 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 447: ...7 26 5 186 178 170 161 152 8 30 3 198 190 180 174 165 9 34 1 212 205 198 185 175 10 37 9 220 215 210 200 195 11 41 6 240 230 221 212 205 12 45 4 250 245 239 232 225 13 49 2 270 261 252 245 235 14 53 0 280 275 265 260 252 15 56 8 300 292 285 275 265 16 60 6 315 305 298 290 282 17 64 4 330 320 312 305 290 18 68 1 340 335 325 320 312 19 71 9 357 348 340 330 320 20 75 7 370 362 352 345 338 21 79 5 390...

Page 448: ...00 110 100 2 7 6 120 123 125 127 130 3 11 4 135 135 140 142 145 4 15 1 150 150 155 158 163 5 18 9 160 167 170 175 185 6 22 7 170 175 180 185 190 7 26 5 185 190 195 205 210 8 30 3 200 210 215 220 230 9 34 1 217 220 225 235 245 10 37 9 230 235 245 250 260 11 41 6 235 245 255 265 275 12 45 4 250 260 270 280 290 13 49 2 260 270 285 300 310 14 53 0 270 285 300 315 325 15 56 8 Page 7 56 Rev 0 11 Jan 201...

Page 449: ...e 60 C 140 F Fuel Grade Approved fuel grades are listed in Section 2 14 FUEL NOTE In order to provide information about the fuel grade it is recommended to enter the fuel grade in the airplane log each time fuel is refilled Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 57 ...

Page 450: ...he second cooling circuit large includes an integral engine oil heat exchanger and a large maincoolantcooler Thesecondcoolingcircuit activatesthrough a thermostat when the coolant reaches approximately 75 C 167 F The flow through the heat exchanger isindependent of thecoolant temperature Anexpansion tankhelpsto adjust the pressure in the system The system is protected against overpressure by means...

Page 451: ...ades refer to Section 2 4 POWER PLANT LIMITATIONS Gearbox and Propeller Governor System The second oil circuit lubricates the gearbox and serves the governor system and the regulation of the propeller The gearbox oil is also cooled via an integral oil coolant heat exchanger The gearbox oil quantity can be checked with the help of an inspection glass which can be reached through an inspection door ...

Page 452: ...ass the turbine The bypass is controlled by the ECU through the waste gate valve A manifold pressure sensor behind the compressorallowsthe ECU to calculate the correct position of the waste gate valve This prevents excessive manifold pressures at low density altitudes The intake air is compressed in the compressor which is driven by the turbine and is subsequently cooled down in the intercooler to...

Page 453: ... electric circuit and a warning message appears in the annunciation window of the G1000 PFD To test the fire detectors refer to Section 4A 6 1 PREFLIGHT INSPECTION push the test button located next to the gear selector switch An aural alert and the fire warning message for the LH and RH engine should appear in the annunciation window of the G1000 PFD CAUTION If the warning does not appear unschedu...

Page 454: ...Airplane Description DA 62 AFM 7 10 ELECTRICAL SYSTEM Page 7 62 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 455: ...circuit breaker Both main busses are connected to the BATTERY BUS via a 90 Ampère circuit breaker Both generator power output lines also run through a current sensor for each alternator which provides an indication of the power being supplied to the electrical system by an alternator including the current for battery charging on the G1000 In the event of a main battery failure the field of each al...

Page 456: ...lleling between the alternators The alternator control unit includes a comprehensive set of diagnostic functions that will warn the operator using a caution message L R ALTN FAIL on the G1000 PFD in case of over or undervoltage as well as a couple of other internal warning levels Storage Main battery power is stored in a 24 V 13 6 Ah lead acid battery mounted on the right aft side of the front ele...

Page 457: ...d connected to the power output line of the alternator via diode and a 30 Ampère circuit breaker and provides power directly to ECU A and its fuel pump ECU B and its fuel pump derive their electrical power from their associated ECU BUS via an additional diode and fuse Additionally each ECU B and its fuel pump is supplied with electrical power from the opposite engine side ECU BUS via a diode and f...

Page 458: ...appropriate bus via automatic circuit breakers Designations and abbreviations used to identify the circuit breakers are explained in Section 1 5 DEFINITIONS AND ABBREVIATIONS Voltmeter The voltmeter displays the voltage of the electrical system Under normal operating conditions the alternator voltageisshown otherwise it displays the main battery voltage Ammeter The ammeter displays the intensity o...

Page 459: ... button INSTRUMENT in the center section of the instrument panel the internal lighting of the instruments and placards is switched on and its brightness is adjusted Pitot Heating The Pitot probe which provides measurement for the Pitot static system is electrically heated The heating is activated with a switch PITOT HEAT located on the row of switches on the instrument panel The temperature is aut...

Page 460: ...62 has an external 28 Volt DC power socket located on the lower surface of the fuselage nose section When external power is connected the control relay is energized and the external power comes online The socket itself has three pins a large negative pin a large positive pin a small positive pin A diode protects the system from reverse polarity 28V Power Outlet Option if OÄM 62 1002 is installed T...

Page 461: ...he installed sensors are Oil temperature lubrication system engine OIL TEMP Oil pressure lubrication system engine OIL PRES Coolant temperature COOLANT TEMP Gearbox temperature GEARBOX Camshaft RPM twice Crankshaft RPM twice Fuel pressure in the common rail Manifold pressure Manifold air temperature Ambient air pressure Propeller governor oil pressure Power lever position twice Voltage Starter swi...

Page 462: ...onic ECU consists of two ECUs per engine A VOTER switch is integrated in the electronic ECU and proposes if set to AUTO an ECU to control the engine regarding the ECU operating hours or in case of a failure the ECU with better engine control capability If the VOTER switch is set to A or B the related EECU is forced to control the corresponding engine with ECU A respectively ECU B A fault detected ...

Page 463: ...right corner of the display there is a MSG message soft key The MSG key provides two functions in the CAS 1 Pressing the MSG key acknowledges a new master warning caution advisory indication 2 An additional MSG key press with no master alert indication active will open a pop up auxiliary flight display AFD page that contains information for all active alerts This structure allows the crew to scrol...

Page 464: ...rrective action Warning chime tone which repeats without delay until acknowledged by the crew Caution Amber May require future corrective action Single warning chime tone Annunciation Advisory White None Message Advisory White None Safe Operation Annunciation Green Lowest None Page 7 72 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 465: ...he annunciation is active when the engine fuel pressure is low L R ALTN AMPS The annunciation is active when the alternator load is greater than 70 Amps L R ENG FIRE The annunciation is active when an engine fire is detected L R STARTER This annunciation is used to indicate to the pilot that the starter is engaged when it should not be L R DOOR OPEN Left Right pilot door is not closed and locked R...

Page 466: ...receiving vertical speed input from the air data computer HDG The annunciation is active when the display system is not receiving valid heading input from the AHRS WARN This annunciation constitutes a RAIM position warning The nav deviation bar is removed Audible Warning Alerts Warning Alerts Meaning Cause Landing gear retracted A warning chime tone which repeats without delay is active when the l...

Page 467: ...itot heater is failed PITOT HT OFF The annunciation is active when the Pitot heat is off STAL HT FAIL The annunciation is active when the stall heater is failed STAL HT OFF The annunciation is active when the stall heater is off L R AUX FUEL E This annunciation can only occur when the auxiliary fuel tank system optional equipment is installed The annunciation is active when the L R auxiliary fuel ...

Page 468: ...active when fuel transfer from auxiliary to main tank is in progress if installed Message Advisory Alerts on the G1000 Advisory Alerts Meaning Cause PFD FAN FAIL The annunciation is active when the PFD fan is inoperative MFD FAN FAIL The annunciation is active when the MFD fan is inoperative GIA FAN FAIL The annunciation is active when the GIA fan is inoperative Page 7 76 Rev 0 11 Jan 2019 Doc No ...

Page 469: ...ing With the alternate static valve the static pressure in the cabin can be used as static pressure source in the event of a failure of the Pitot static system 7 12 STALL WARNING SYSTEM The lift detector of the DA 62 is located on the front edge of the left wing below the wing chord line It issuppliedelectricallyand provides a stall warning before the angle of attack becomes critical The stall sta...

Page 470: ...ed on the end of each control stick There are connection facilitiesforup to5 oroptionally7 headsets The connections for the pilot copilot and 1st passenger row are located between the pilot s and copilot s seat The connectionsforthe 2nd passenger roware located on the left and right outboard side of each seat As the audio panel is limited to a maximum of 6 microphones a switch is optionally instal...

Page 471: ...ng retraction and extension of the landing gear the ADF indication may be inaccurate NOTE The airplane electrical system slightly interferes with the WX500 stormscope causing strikes to be displayed beyond the 100NMrange ring Thus it isrecommended to use range settings below 100 NM or carefully verify if the indicated strikes are real It is also recommended not to display Strike data on the Map pa...

Page 472: ...ction is equal to a standard rate turn The following controls areavailable on the PFD clockwise from top right Communications frequency volume and squelch knob Communications frequency set knobs Communications frequency transfer button Altimeter setting knob baro set Course knob Map range knob and cursor control FMS control buttons and knob PFD softkey buttons including master warning caution ackn...

Page 473: ...companied by an aural tone A warning is accompanied by a repeating tone and a caution is accompaniedbya single tone Acknowledgingthealert willcanceltheflashingand provide a text description of the message Refer to Chapter 3 EMERGENCY PROCEDURES Chapter4B ABNORMALOPERATINGPROCEDURES andSection7 10 3 WARNING CAUTION AND ADVISORY MESSAGES Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 7 81 ...

Page 474: ...omposite mode the full crew alerting function remains but no map functions are available 7 13 3 MULTI FUNCTION DISPLAY MFD The multi function display MFD typicallydisplays engine data maps terrain traffic and topography displays and flight planning and progress information The display unit is nearlyidenticaltothe PFDand containsthe samecontrolsaspreviouslylisted Additionally the MFD incorporates t...

Page 475: ...alert the crew of the loss of any of these inputs The AHRS will align while the airplane is in motion but will align quicker if the wings are kept level during the alignment process 7 13 6 AIR DATA COMPUTER ADC The air data computer ADC provides airspeed altitude vertical speed and air temperature to the display system In addition to the primary displays this information is used by the FMS and TIS...

Page 476: ...se of data entry PFD MFD operation and NAV COM tuning The PFD MFD control unit is installed in the center armrest Access to the control unit is accomplished by a folding mechanism The control unit must be stowed during take off and landing all emergencies and abnormal operating procedures For more information refer to the Garmin G1000 Pilot s Guide P N 190 01895 or the latest effective issue Page ...

Page 477: ...WS control wheel steering switch a power lever mounted GA go around switch and PFD MFD mounted altitude preselect heading and course knobs The GFC700 autopilotcontains an electric pitchtrim system which isused bythe autopilot for automatic pitch trim during autopilot operation and bythepilot formanualelectricpitch trim when the autopilot is not engaged The manual electric pitch trim is operated by...

Page 478: ...light controlsaslongasthe CWS switch is depressed Powerto theGFC700 autopilot and electric trim system is supplied through the AVIONIC MASTERswitchand the AFCS ESP USP 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 pilot s control stick will interrupt power to the manual electric trim for ...

Page 479: ...operative Lossof GIA 2 will also prevent autopilot and manual electric trim operation but flight director will be available Loss of the standby attitude module or compass will have no effect on the autopilot 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 imp...

Page 480: ...WS control wheel steering switch Remote mounted go around switch on the left side of the power lever knob PFD MFD mounted altitude preselect knob ALT PFD MFD mounted heading select knob HDG Flight director commands and autopilot modes are displayed on the PFD Full AFCS functionalityisonlyavailable with both displaysoperating and willdisconnectundercertain reversionary conditions Upon initial syste...

Page 481: ...onnects 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 if ESP USP is NOT installed Abnormal disconnects will be accompanied by a red flashing 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 ...

Page 482: ... the radio circuit breakers and the AFCS ESP USP circuit breaker The following circuit breaker is used to protect the following element of the GFC 700 autopilot Circuit Breaker Function AFCS ESP USP Supplies power to the autopilot pitch roll yaw and pitch trim servos Page 7 90 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 483: ... Warning Alerts Meaning Cause PFT PREFLIGHT TEST Preflight system test failed aural alert sounds at failure AFCS SYSTEM FAILURE AP and MET are unavailable FD may still be available PTCH PITCH FAILURE Pitch axis control failure AP inoperative ROL ROLL FAILURE Roll axis control failure AP inoperative YAW YAW DAMPER FAILURE Yaw damper control failure AP inoperative PTRM PITCH TRIM FAILURE or stuck AP...

Page 484: ...indicated direction 7RUD RUDDER MISTRIM LEFT Yaw servo providing sustained force in the indicated direction RUD6 RUDDER MISTRIM RIGHT Yaw servo providing sustained force in the indicated direction Advisory Alerts on the Automatic Flight Control System AFCS Advisory Meaning Cause PFT PREFLIGHT TEST Performing preflight system test aural alert sounds at completion Do not press the AP DISC switch dur...

Page 485: ...on and the lower display as airspeed indicator and altimeter The user interface of the Standby Attitude Module allows for simple intuitive operation using a single push and turn control knob Refer to the Mid Continent MD302 Standby Attitude Module Pilot s Guide P N 9017846 in the latest effective issue for more information The MD302 Standby Attitude Module is not connected to an external ARINC 429...

Page 486: ...Airplane Description DA 62 AFM Intentionally left blank Page 7 94 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 487: ...E OIL LEVEL CHECK 8 4 8 4 3 GEARBOX OIL LEVEL CHECK 8 4 8 4 4 TIRE INFLATION PRESSURE CHECK 8 5 8 5 GROUND HANDLING ROAD TRANSPORT 8 6 8 5 1 GROUND HANDLING 8 6 8 5 2 PARKING 8 8 8 5 3 MOORING 8 11 8 5 4 JACKING 8 11 8 6 CLEANING AND CARE 8 12 8 6 1 PAINTED SURFACES 8 12 8 6 2 FRONT AND REAR DOOR 8 13 8 6 3 PROPELLER 8 13 8 6 4 ENGINE 8 13 8 6 5 INTERIOR SURFACES 8 13 8 7 GROUND DE ICING 8 15 Doc ...

Page 488: ...formed on new engines after 3 to 6 hours The respective inspection checklists are prescribed in the Airplane Maintenance Manual Chapter 05 Formaintenance workon engineandpropeller thecurrentlyeffectiveOperator sManuals Service Instructions Service Letters and Service Bulletins of Austro Engine and mt Propeller must be followed For airframe inspections the currently effective checklists manuals Ser...

Page 489: ...ersons and damage to the airplane WARNING Do not get fuel on your skin Fuel can cause skin disease WARNING Connect the airplane and the fuel supply vehicle to electrical ground before refueling If you do not ground the airplane static electricity can cause fire during refueling WARNING Make sure that a suitable fire extinguisher is available at all times during refueling WARNING Turn off all groun...

Page 490: ...CK 1 Open the inspection door on the bottom of the upper left cowling 2 Remove the filler cap 3 Clean the oil dip stick 4 Install the filler cap 5 Remove the filler cap again 6 Read the oil level from the dip stick 7 If necessary add engine oil and repeat steps 3 to 6 8 Install the filler cap 9 Close the inspection door 10 Repeat steps 1 to 9 for the other engine 8 4 3 GEARBOX OIL LEVEL CHECK 1 Op...

Page 491: ...ust cap from valve stem by turning counterclockwise 2 Connect tire gauge to valve stem read pressure 3 Correct pressure if necessary nose wheel 3 2 bar 46 psi main wheels 3 8 bar 55 psi 4 Install dust cap on valve stem by turning clockwise Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 8 5 ...

Page 492: ...ING For pushing or pulling the airplane on the ground it is recommended to use the tow bar which is available from the manufacturer The tow bar is engaged in the appropriate hole in the nose wheel as shown on the picture Tow Bar Variants WARNING Page 8 6 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 493: ...e landing gear The maximum steering angle of 40 degrees to either side must not be exceeded WARNING The tow bar must be removed before starting the engine In the event that the airplane must be pulled out of soft ground or deep snow towing lines must be used The towing lines should be attached to the main landing gear struts as high aspossible without interfering with the brake lines The ropes sho...

Page 494: ...recommended NOTE If the engine is not used for more than 4 weeks an engine ground run must be performed Refer to AE Operation Manual Doc No E4 01 01 latest revision The manufacturer offers a control surfaces gust lock which can be used to block the primary controls It is recommended that the control surfaces gust lock is used when parking outdoors because otherwise the control surfaces can hit the...

Page 495: ...ntrol surfaces gustlock with the pedals 3 Engage the stick wrap straps around stick once 4 Attach the locks 5 Wrap the strap under the lower rail of the rudder pedal assy and attach the lock on the gust lock CAUTION Do not wrap the strap around the spindle 6 Tighten all straps For removal reverse the sequence Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 8 9 ...

Page 496: ...Handling Care Maintenance DA 62 AFM Page 8 10 Rev 0 11 Jan 2019 Doc No 11 01 05 E 1 4 5 2 3 ...

Page 497: ...n the airplane to the ground Also on each wing near the wing tip an eyelet with a metric M8 thread can be installed and used as tie down points 8 5 4 JACKING The airplane can be jacked at the two jackpoints located on the lower side of the center wing s LH and RH root ribs as well as at the tail fin Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 8 11 ...

Page 498: ...ommended not to store the airplane outside for long periods of time Dirt insects etc can be removed with wateralone andif necessary with a milddetergent An automotive paint cleaner can be used for stubborn spots For best results clean the airplane after the day s flying is ended so that the dirt will not become ingrained Oil stains exhaust stains etc on the lower fuselage skin can be removed with ...

Page 499: ...aint which is resistant to almost any solvent The bladesmaybe treated with commercial automotive cleaningagentsorpreservatives The penetration of moisture into the wooden core must be avoided by all means Should doubts arise an appropriately rated inspector must be consulted 8 6 4 ENGINE Engine cleaning is part of the scheduled inspections 8 6 5 INTERIOR SURFACES The interior should be cleaned usi...

Page 500: ...hin 3 months since new and then at intervals of 3to 6months Clean theleatherinteriorwith an appropriate mild leather cleaning agent and a soft cleaning brush for leather Note that the acrylic glass windows transmit the ultraviolet radiation from the sun Page 8 14 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 501: ...urer Name Kilfrost TKS 80 Aeroshell Compound 07 AL 5 DTD 406B 1 Remove any snow from the airplane using a soft brush 2 Spray deicing fluid onto ice covered surfaces using a suitable spray bottle 3 Use a soft piece of cloth to wipe the airplane dry Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 8 15 ...

Page 502: ...Handling Care Maintenance DA 62 AFM Intentionally left blank Page 8 16 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 503: ...DA 62 AFM Supplements CHAPTER 9 SUPPLEMENTS Page 9 1 INTRODUCTION 9 2 9 2 LIST OF SUPPLEMENTS 9 3 Doc No 11 01 05 E Rev 0 11 Jan 2019 Page 9 1 ...

Page 504: ...ents must be applied in addition to the procedures given in the main part of the Airplane Flight Manual All approved supplements are listed in the List of Supplements in this Chapter The Airplane Flight Manual contains exactly those supplements which correspond to the installed equipment according to the Equipment Inventory of Section 6 5 Page 9 2 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

Page 505: ...015 9 9 M15 On Top Exhaust System 0 18 Aug 2017 9 9 O04 Operation without Unfeathering Accumulator 0 14 Nov 2015 9 9 O08 Pilot s Removable Stick 0 30 Jan 2016 9 9 S02 Ice Protection System 1 15 Nov 2015 9 9 S03 Ice Protection System for Flight into Known Icing 2 05 May 2017 9 9 S04 Continuous Flow Oxygen System 1 14 Nov 2015 9 9 S06 G1000 Synthetic Vision Technology 1 20 Sep 2016 9 9 S07 Recircula...

Page 506: ...Supplements DA 62 AFM Airplane S N Registration Date Sup No Title Rev No Date applicable YES NO 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 Page 9 4 Rev 0 11 Jan 2019 Doc No 11 01 05 E ...

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