Diamond Aircraft DA 40 NG Airplane Flight Manual Download

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DA 40 NG AFM

Airplane

Description

Doc. # 6.01.15-E

Rev. 3

01-Jul-2014

Page 7 - 1

CHAPTER 7

DESCRIPTION OF THE AIRPLANE

AND ITS SYSTEMS

Page

7.1

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2

7.2

AIRFRAME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2

7.3

FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3

7.4

INSTRUMENT PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-8

7.5

LANDING GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-14

7.6

SEATS AND SAFETY HARNESSES . . . . . . . . . . . . . . . . . . . . . . 7-16

7.7

BAGGAGE COMPARTMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-18

7.8

CANOPY, REAR DOOR, AND CABIN INTERIOR . . . . . . . 7-18

7.9

POWER PLANT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-21

7.9.1 ENGINE, GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-21

7.9.2 OPERATING CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . 7-22

7.9.3 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-25

7.9.4 FUEL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-27

7.9.5 COOLING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-35

7.9.6 TURBO CHARGER SYSTEM . . . . . . . . . . . . . . . . . . . . . . . 7-36

7.9.7 OIL SYSTEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-37

7.10

ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-38

7.10.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-39

7.10.2 ENGINE CONTROL UNIT / ECU . . . . . . . . . . . . . . . . . . . 7-46

7.11

PITOT-STATIC SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-48

7.12

STALL WARNING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-48

Summary of Contents for DA 40 NG

Page 1: ......

Page 2: ...DA 40 NG AFM Introduction Page 0 0a Rev 3 01 Jul 2014 Doc 6 01 15 E Intentionally left blank...

Page 3: ...lot must familiarize himself with the complete contents of this Airplane Flight Manual In the event that you have obtained your DIAMOND DA 40 NG second hand please let us know your address so that we...

Page 4: ...n number and date appearing at the bottom of the page If pages are revised which contain information valid for your particular serial number modification level of the airplane weighing data Equipment...

Page 5: ...0 314 40 316 40 321 40 326 40 327 40 329 40 330 40 331 40 333 Corrections all all except cover page 15 Mar 2011 Revision 1 of the AFM Doc No 6 01 15 E is approved with EASA Approval No 10034114 08 Mar...

Page 6: ...40 674 40 672 40 662 40 638 40 631 40 632 40 618 a O M 40 321 b 40 574 40 563 40 562 40 561 40 559 40 558 40 547 40 533 40 488 40 429 a 40 551 O M 40 321 b 40 237 40 183 40 334 a 40 314 d 40 316 d 40...

Page 7: ...01 Jul 2014 0 9 01 Jul 2014 0 10 01 Jul 2014 0 11 01 Jul 2014 0 12 01 Jul 2014 0 13 01 Jul 2014 0 14 01 Jul 2014 Ch Page Date 1 1 1 01 Jul 2014 1 2 01 Jul 2014 1 3 01 Jul 2014 1 4 01 Jul 2014 1 5 01 J...

Page 8: ...r 2 13 01 Jul 2014 appr 2 14 01 Jul 2014 appr 2 15 01 Jul 2014 appr 2 16 01 Jul 2014 appr 2 17 01 Jul 2014 appr 2 18 01 Jul 2014 appr 2 19 01 Jul 2014 appr 2 20 01 Jul 2014 appr 2 21 01 Jul 2014 appr...

Page 9: ...Jul 2014 3 18 01 Jul 2014 3 19 01 Jul 2014 3 20 01 Jul 2014 3 21 01 Jul 2014 3 22 01 Jul 2014 3 23 01 Jul 2014 3 24 01 Jul 2014 3 25 01 Jul 2014 3 26 01 Jul 2014 3 27 01 Jul 2014 3 28 01 Jul 2014 Ch...

Page 10: ...14 4A 14 01 Jul 2014 4A 15 01 Jul 2014 4A 16 01 Jul 2014 4A 17 01 Jul 2014 4A 18 01 Jul 2014 4A 19 01 Jul 2014 4A 20 01 Jul 2014 4A 21 01 Jul 2014 4A 22 01 Jul 2014 4A 23 01 Jul 2014 4A 24 01 Jul 2014...

Page 11: ...014 4B 9 01 Jul 2014 4B 10 01 Jul 2014 4B 11 01 Jul 2014 4B 12 01 Jul 2014 4B 13 01 Jul 2014 4B 14 01 Jul 2014 4B 15 01 Jul 2014 4B 16 01 Jul 2014 4B 17 01 Jul 2014 4B 18 01 Jul 2014 4B 19 01 Jul 2014...

Page 12: ...1 Jul 2014 5 15 01 Jul 2014 5 16 01 Jul 2014 5 17 01 Jul 2014 5 18 01 Jul 2014 5 19 01 Jul 2014 5 20 01 Jul 2014 5 21 01 Jul 2014 5 22 01 Jul 2014 5 23 01 Jul 2014 5 24 01 Jul 2014 5 25 01 Jul 2014 5...

Page 13: ...014 6 7 01 Jul 2014 6 8 01 Jul 2014 6 9 01 Jul 2014 6 10 01 Jul 2014 6 11 01 Jul 2014 6 12 01 Jul 2014 6 13 01 Jul 2014 6 14 01 Jul 2014 6 15 01 Jul 2014 6 16 01 Jul 2014 6 17 01 Jul 2014 6 18 01 Jul...

Page 14: ...1 Jul 2014 7 18 01 Jul 2014 7 19 01 Jul 2014 7 20 01 Jul 2014 7 21 01 Jul 2014 7 22 01 Jul 2014 7 23 01 Jul 2014 7 24 01 Jul 2014 7 25 01 Jul 2014 7 26 01 Jul 2014 7 27 01 Jul 2014 Ch Page Date 7 7 28...

Page 15: ...014 8 2 01 Jul 2014 8 3 01 Jul 2014 8 4 01 Jul 2014 8 5 01 Jul 2014 8 6 01 Jul 2014 8 7 01 Jul 2014 8 8 01 Jul 2014 8 9 01 Jul 2014 8 10 01 Jul 2014 8 11 01 Jul 2014 8 12 01 Jul 2014 8 13 01 Jul 2014...

Page 16: ...ROCEDURES a non approved chapter 3 NORMAL OPERATING PROCEDURES a non approved chapter 4A ABNORMAL OPERATING PROCEDURES a non approved chapter 4B PERFORMANCE a non approved chapter 5 MASS AND BALANCE E...

Page 17: ...ASIS 1 4 1 3 WARNINGS CAUTIONS AND NOTES 1 4 1 4 DIMENSIONS 1 5 1 5 DEFINITIONS AND ABBREVIATIONS 1 7 1 6 UNITS OF MEASUREMENT 1 15 1 6 1 CONVERSION FACTORS 1 15 1 6 2 CONVERSION CHART LITER US GALLON...

Page 18: ...serial number to serial number Therefore some of the information contained in this manual is applicable depending on the respective equipment and modification level The exact equipment of your serial...

Page 19: ...g Mass O M 40 334 9 yes 9 no Diesel Operation O M 40 370 9 yes 9 no This Airplane Flight Manual must be kept on board the airplane at all times Its designated place is the side bag of the forward left...

Page 20: ...ts in the Airplane Flight Manual concerning the safety or operation of the airplane are highlighted by being prefixed by one of the following terms WARNING means that the non observation of the corres...

Page 21: ...ns Span 11 63 m 38 ft 2 in Length 8 06 m 26 ft 5 in Height 1 97 m 6 ft 6 in Wing Airfoil Wortmann FX 63 137 20 W4 Wing area 13 244 m 142 6 sq ft Mean aerodynamic chord MAC 1 171 m 3 ft 10 in Aspect ra...

Page 22: ...2 sq ft Angle of incidence 3 0 relative to longitudinal axis of airplane Vertical Tail Area 1 60 m 17 2 sq ft Rudder area 0 47 m 5 1 sq ft Landing Gear Track 2 97 m 9 ft 9 in Wheelbase 1 68 m 5 ft 6...

Page 23: ...ane relative to the air TAS is CAS corrected for errors due to altitude and temperature vO Operating Maneuvering Speed Full or abrupt control surface movement is not permissible above this speed vFE M...

Page 24: ...an ideal dry gas The temperature at mean sea level is 15 C 59 F air pressure at MSL is 1 013 25 hPa 29 92 inHg the temperature gradient up to the altitude at which the temperature reaches 56 5 C 69 7...

Page 25: ...nual altimeter instrument errors are regarded as zero Wind The wind speeds which are shown as variables in the diagrams in this manual should be regarded as headwind or tailwind components of the meas...

Page 26: ...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...

Page 27: ...the tank which cannot be used for flight Useful Load The difference between take off mass and empty mass e Engine CT Coolant Temperature EECU Electronic Engine Control Unit GT Gearbox Temperature LOA...

Page 28: ...eiver AUTOPILOT Autopilot System COM COM Radio COM1 COM Radio No 1 COM2 COM Radio No 2 DG Directional Gyro DME Distance Measuring Equipment EECU A ECU A EECU B ECU B ENG INST Engine Instruments ESS TI...

Page 29: ...ceiver PFD Primary Flight Display PITOT Pitot Heating System POSITION Position Lights PWR Power START Starter STROBE Strobe Lights Anti Collision Lights T B Turn and Bank Indicator TAS Traffic Advisor...

Page 30: ...neous ACG Austro Control GmbH formerly BAZ Federal Office of Civil Aviation ATC Air Traffic Control CFRP Carbon Fiber Reinforced Plastic EASA European Aviation Safety Agency GFRP Glass Fiber Reinforce...

Page 31: ...7854 US gal l 0 9464 qts ml x 0 033814 oz Speed km h kilometer per hour m s meter per second kt knot mph mile per hour fpm feet per minute km h 1 852 kt km h 1 609 mph m s x 196 85 fpm Speed of rotat...

Page 32: ...G AFM Dimension SI Units US Units Conversion Page 1 16 Rev 3 01 Jul 2014 Doc 6 01 15 E Intensity of electric current A amp re Electric charge battery capacity Ah amp re hour Electric potential V volt...

Page 33: ...2 7 6 15 4 0 4 15 1 20 5 3 6 22 7 25 6 6 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...

Page 34: ...General DA 40 NG AFM Page 1 18 Rev 3 01 Jul 2014 Doc 6 01 15 E 8060 mm 26 ft 5 in 11630 mm 38 ft 2 in 1 7 THREE VIEW DRAWING...

Page 35: ...ndicates the respective publisher However only the information given in the Airplane Flight Manual is valid 1 8 1 ENGINE AND ENGINE INSTRUMENTS Address Austro Engine GmbH Rudolf Diesel Str 11 A 2700 W...

Page 36: ...ress mt propeller Airport Straubing Wallm hle D 94348 ATTING GERMANY Phone 49 9429 9409 0 E mail sales mt propeller com Internet www mt propeller de Documents E 124 Operation and Installation Manual H...

Page 37: ...ND STATUS LIGHTS 2 12 2 7 MASS WEIGHT 2 16 2 8 CENTER OF GRAVITY 2 18 2 9 APPROVED MANEUVERS 2 19 2 10 MANEUVERING LOAD FACTORS 2 20 2 11 OPERATING ALTITUDE 2 21 2 12 FLIGHT CREW 2 21 2 13 KINDS OF OP...

Page 38: ...light Manual includes operating limitations instrument markings and placards necessary for the safe operation of the airplane its power plant standard systems and standard equipment The limitations in...

Page 39: ...ace movement above this speed above 1080 kg 2381 lb to 1180 kg 2601 lb 108 KIAS above 1180 kg 2601 lb 113 KIAS vFE Max flaps extended speed LDG 98 KIAS Do not exceed these speeds with the given flap s...

Page 40: ...3 AIRSPEED INDICATOR MARKINGS Marking IAS Significance White arc 60 KIAS 98 KIAS Operating range with flaps fully extended Green arc 66 KIAS 130 KIAS Normal operating range Yellow arc 130 KIAS 172 KI...

Page 41: ...ximum take off RPM 2300 RPM max 5 min Max continuous power RPM 2100 RPM Max overspeed 2500 RPM max 20 sec d Engine power Max take off power 100 123 5 kW max 5 min Max continuous power 92 114 kW e Oil...

Page 42: ...manufacturer However there is a delay between power changes and gearbox temperature Therefore a cautionary range has been added to the gearbox temperature instrument solely to make the pilot attentive...

Page 43: ...w the limit Maximum 7 bar NOTE The fuel pressure is not indicated the fuel pressure caution ECU A B FAIL on the PFD if G1000 is installed or ECU A B on the White Wire annunciator panel if installed wi...

Page 44: ...30 G Energy F Synth 5W 30 5W 30 QUARTZ 9000 ENERGY 5W 30 5W 30 Gulf Formula GX 5W 30 AEROSHELL Oil Diesel Ultra 5W 30 CASTROL Edge 5W 30 A3 5W 30 CASTROL Edge Professional A3 5W 30 SHELL HELIX ULTRA...

Page 45: ...for operation NOTE It is not recommended to mix different SAE grades t Gearbox oil propeller gearbox SHELL SPIRAX GSX 75W 80 SHELL SPIRAX S6 GXME 75W 80 u Coolant Distilled water Cooler protection BAS...

Page 46: ...itations DA 40 NG AFM Page 2 10 Rev 3 01 Jul 2014 EASA approved Doc 6 01 15 E v Maximum restart altitude 16 400 ft pressure altitude for immediate restarts 10 000 ft pressure altitude for restarts wit...

Page 47: ...d range RPM up to 2100 RPM 2100 to 2300 RPM above 2300 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 to140 C...

Page 48: ...ING WARNING One of the warnings listed below is being indicated ENG TEMP Engine coolant temperature is in the upper red range too high 105 C OIL TEMP Engine oil temperature is in the upper red range t...

Page 49: ...speed input from the air data computer accompanied by a red X through the airspeed display ALTITUDE FAIL Display system is not receiving altitude input from the air data computer accompanied by a red...

Page 50: ...procedure during the Before Take Off Check ECU B FAIL ECU B A fault has occurred in the engine ECU B or ECU B is being tested during FADEC test procedure during the Before Take Off Check FUEL LOW LOW...

Page 51: ...ry Alerts White Meaning Cause G1000 installed SED MED White Wire installed GLOW ON GLOW Engine glow plug active FUEL XFER FUEL TRANS Fuel transfer from auxiliary to main tank is in progress PFD FAN FA...

Page 52: ...compartment between rear seats and baggage frame 30 kg 66 lb Max load in baggage tube compartment if installed 5 kg 11 lb Max load in short baggage extension if O M 40 331 is installed 15 kg 33 lb Ex...

Page 53: ...es the beginning of a flight is defined by starting the engine In those countries a maximum ramp mass 4 kg 9 lb above the maximum take off mass is approved At the time of lift off the maximum permitte...

Page 54: ...ly the Datum Plane is vertical The Datum Plane is located 2 194 meter 86 38 in forward of the most forward point of the root rib on the stub wing Center of Gravity Limitations The center of gravity CG...

Page 55: ...ed Maneuvers 1 All normal flight maneuvers 2 Stalling with the exception of dynamic stalling and 3 Lazy Eights Chandelles as well as steep turns and similar maneuvers in which an angle of bank of not...

Page 56: ...UVERING LOAD FACTORS WARNING The table below shows structural limitations Exceeding the maximum load factors will lead to an overstressing of the airplane CAUTION Intentional negative g maneuvers are...

Page 57: ...Doc 6 01 15 E Rev 3 01 Jul 2014 EASA approved Page 2 21 2 11 OPERATING ALTITUDE The maximum operating altitude is 16 400 ft 5 000 m pressure altitude 2 12 FLIGHT CREW Minimum crew 1 one person Maximum...

Page 58: ...to Instrument Flight Rules IFR Take off and landing on paved surfaces Take off and landing on unpaved surfaces Flights into known or forecast icing conditions are prohibited Flights into known thunde...

Page 59: ...ed by pilot in command Vertical speed indicator VSI Attitude gyro Turn bank indicator Directional gyro VHF radio COM VOR receiver Transponder XPDR GPS receiver part of G1000 if installed Second headse...

Page 60: ...Page 2 24 Rev 3 01 Jul 2014 EASA approved Doc 6 01 15 E Engine instru ments Fuel qty Oil press Oil temp Coolant temp Coolant level indicator Gearbox temp Load Prop RPM Fuel temp left right tank Fuel...

Page 61: ...al mini mum equip ment Stall warning system Alternate means for fuel quantity indication see Section 7 9 Safety belts for each occupied seat Airplane Flight Manual Pitot heating system Alternate stati...

Page 62: ...USA MIL DTL 83133G 2010 and blends of the above listed fuel grades NOTE A minimum cetane number of 37 determined acc to EN ISO 5165 ASTM D613 is recommended NOTE Use only uncontaminated fuel from rel...

Page 63: ...m of the airplane a higher dosage of the specified additive is allowed under consideration of the instructions of the additive supplier During cleaning the engine must not be operated NOTE The instruc...

Page 64: ...Long Range Tank if installed Configuration Total fuel quantity 2 x 20 5 US gal 2 x 77 6 liter Usable fuel 2 x 19 5 US gal 2 x 73 8 liter Max indicated fuel quantity 14 US gal 53 liter per tank Max pe...

Page 65: ...MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANE FLIGHT MANUAL IN THE NORMAL CATEGORY IN NON ICING CONDITIONS PROVIDEDTHATNATIONALOPERATIONALREQUIREMENTS ARE MET AND THE APPROPRIATE EQUIPMENT IS...

Page 66: ...M Page 2 30 Rev 3 01 Jul 2014 EASA approved Doc 6 01 15 E WARNING APPROVED FUEL JET A1 or see Airplane Flight Manual Next to Each of the Two Fuel Filler Necks Next to the Essential Bus Switch Ess Bus...

Page 67: ...approved Page 2 31 OIL SHELL HELIX ULTRA 5W30 or see Airplane Flight Manual max 98 KIAS max 110 KIAS NORMAL EMERGENCY FUEL VALVE CAUTION INTERMITTENT USE ONLY SEE AFM OFF In the Cowling on the Door fo...

Page 68: ...DA 40 NG AFM Page 2 32 Rev 3 01 Jul 2014 EASA approved Doc 6 01 15 E Max 5 kg 11 lb Next to the Baggage Compartment Baggage Tube Compartment Baggage Tray if O M 40 164 installed extended baggage compa...

Page 69: ...E COMPARTMENT MAX 45 kg 100 lb ARM 3 89 m 153 1 BAGGAGE EXTENSION MAX 18 kg 40 lb ARM 4 54 m 178 7 MAX BAGGAGE TOTAL COCKPIT BAGGAGE COMPARTMENT EXTENSION 45 kg 100 lb CAUTION OBSERVE WEIGHT AND BALAN...

Page 70: ...uring flight Remove at Outside Temperatures above 20 C 68 F Alternate Static OPEN CLOSED If Alternate Static is open Emergency Window and Cockpit Vent must be closed On the Left Sidewall Next to the I...

Page 71: ...below 30 C 22 F the coolant radiator inlet baffle O M 40 364 must be installed The airplane may only be operated with the coolant radiator inlet baffle if the outside air temperature at take off does...

Page 72: ...rable items of equipment are Mobile telephones Remote radio controls Video screens employing CRTs Minidisc recorders when in the record mode This list is not exhaustive The use of laptop computers inc...

Page 73: ...R FUEL TEMPERATURE 3 11 3 2 6 FUEL PRESSURE 3 12 3 2 7 ALTERNATOR AMPS 3 13 3 2 8 ALTERNATOR FAIL 3 14 3 3 ENGINE PROBLEMS 3 15 3 3 1 ENGINE PROBLEMS ON GROUND 3 15 3 3 2 ENGINE PROBLEMS DURING TAKE...

Page 74: ...ANDINGS 3 41 3 7 1 EMERGENCY LANDING WITH ENGINE OFF 3 41 3 7 2 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR 3 43 3 7 3 LANDING WITH DEFECTIVE BRAKES 3 44 3 8 RECOVERY FROM AN UNINTENTIONAL...

Page 75: ...his Airplane Flight Manual a thorough understanding of the airplane by the pilot is in addition to his knowledge and experience an essential factor in the solution of any problems which may arise WARN...

Page 76: ...ge 3 4 Rev 3 01 Jul 2014 Doc 6 01 15 E 3 1 2 CERTAIN AIRSPEEDS IN EMERGENCIES Event KIAS Airspeed for best glide angle Flaps UP 88 KIAS Airspeed for emergency landing with engine off Flaps UP 83 KIAS...

Page 77: ...o a total loss of power due to engine failure Check for COOL LVL if G1000 is installed or WATERLEV if SED is installed caution message low coolant level COOL LVL if G1000 is installed or WATERLEV if S...

Page 78: ...cooling system and that the abovementionedprocedurecandecreasethetemperature s This might not be the case if the coolant temperature does not return to the green range In this case perform a precautio...

Page 79: ...40 C can lead to a total loss of power due to engine failure Check oil pressure If the Oil Pressure Is Outside of the Green Range Lower Limit Reduce power Expect loss of engine oil WARNING A further i...

Page 80: ...med that there is no technical defect in the 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 t...

Page 81: ...the lower red range too low below 0 9 bar Oil pressures below the limit value of 0 9 bar can lead to a total loss of power due to engine failure Reduce power Expect loss of oil WARNING Land at the nea...

Page 82: ...airspeed CAUTION At high ambient temperature conditions and or at low airspeeds with high power settings it can be assumed that there is no technical defect in the gearbox and that the above mentioned...

Page 83: ...N At high ambient temperature conditions 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 I...

Page 84: ...l pumps ON If FUEL PRESS if G1000 is installed or FUELPRESS if SED is installed Warning Remains 4 Fuel valve EMERGENCY 5 Fuel pumps OFF If FUEL PRESS if G1000 is installed or FUELPRESS if SED is insta...

Page 85: ...red range too high above 70 A This warning is indicated when the consumption of electrical power is too high Possible reasons are A fault in wiring or equipment 1 Electrical equipment switch OFF as ne...

Page 86: ...gine operation needs electrical power It is recommended to switch off all electrical consumers and to land as soon as possible Be prepared for an engine failure and an emergency landing For a severe e...

Page 87: ...akes as required NOTE If considered necessary the engine must be shut down Otherwise the cause of the problem must be established in order to re establish engine performance CAUTION If the oil pressur...

Page 88: ...ke Off Can Still Be Aborted Sufficient Runway Length Available Land Straight Ahead 1 POWER lever IDLE On the Ground 2 Brakes as required WARNING If sufficient time is remaining the risk of fire in the...

Page 89: ...safe height has not been reached then a straight ahead emergency landing should be considered Do not attempt to turn back to the airfield Turning back can be fatal If Time Allows 2 POWER lever check...

Page 90: ...POWER lever you may adjust the friction lock and continue your flight If ECU A and ECU B Cautions Appear Simultaneously If the indicated LOAD remains unchanged and if the perceived thrust is reduced a...

Page 91: ...rovide up to 65 load at the maximum propeller speed of 1975 RPM 7 Land at the next suitable airfield Otherwise Depending on the situation the following attempts can be made to restore normal engine op...

Page 92: ...e operation is restored continue flight and land as soon as possible Remain within maximum allowable lateral imbalance Otherwise 7 Fuel valve NORMAL 8 Alternate air OPEN 9 POWER lever apply power as r...

Page 93: ...OTE As long as there is no major mechanical engine defect the propeller will continue to windmill 1 Airspeed 88 KIAS 2 Flaps UP If the Remaining Altitude is Sufficient for an Restart Attempt Try to re...

Page 94: ...Maximum restart altitude 16 400 ft pressure altitude for immediate restarts 10 000 ft pressure altitude for restarts within two minutes NOTE If the engine is allowed to cool down for more than two mi...

Page 95: ...oss the maximum horizontal distance traveled in still air is 1 59 NM 2 94 km During this the propeller will continue to windmill Carry out an emergency landing in accordance with 3 7 1 EMERGENCY LANDI...

Page 96: ...e RPM should be adjusted with the POWER lever CAUTION The POWER lever should be moved slowly in order to avoid over speeding and excessively rapid RPM changes The light wooden propeller blades produce...

Page 97: ...lower airspeed Climb and go around may not be possible under all conditions 1 POWER lever reduce to not exceed 2300 RPM 2 Airspeed 88 KIAS 3 Flaps check UP After RPM has Stabilized Below 2300 RPM 4 A...

Page 98: ...Rev 3 01 Jul 2014 Doc 6 01 15 E If the Problem Does Not Clear 7 Land on the nearest suitable airfield If an Increased Climb Rate is Required 8 Flaps T O position 9 Airspeed 72 KIAS 10 POWER lever asre...

Page 99: ...If the Problem Does Not Clear 2 VOTER switch swap between ECU A and B If the Problem Does Not Clear 3 VOTER switch AUTO 4 POWER lever as required WARNING Due to this problem the propeller RPM will dro...

Page 100: ...ndication reads zero Otherwise the engine will stop during flight when the auxiliary tank is empty WARNING When the fuel pump takes in air e g when the fuel valve is not switched back and the auxiliar...

Page 101: ...cedures Doc 6 01 15 E Rev 3 01 Jul 2014 Page 3 29 NOTE AUX tank quantity must not be less than 1 US gal and MAIN tank quantity must not be more than 14 US gal 6 Fuel valve NORMAL 7 Land as soon as pra...

Page 102: ...ding with flaps in the given position Refer to 4B 5 FAILURES IN FLAP OPERATING SYSTEM 6 Land on the nearest suitable airfield WARNING Engine stoppage may occur depending on the failure mode A backup b...

Page 103: ...CURRENT 70 A is indicated on the G1000 if installed or SED if installed 1 ESSENTIAL BUS ON 2 ENGINE SYSTEM DISPLAY if G1000 is installed select by pressing ENGINE and SYSTEM softkey on MFD 3 Circuit...

Page 104: ...from the engine after starting Starter engaged warning STARTER on the G1000 if installed or START on the White Wire annunciator if installed illuminates after the engine has started On Ground 1 POWER...

Page 105: ...3 3 5 SMOKE AND FIRE 3 5 1 SMOKE AND FIRE ON GROUND a Engine Fire When Starting on the Ground 1 Fuel valve OFF 2 Fuel transfer pump OFF 3 ENGINE MASTER OFF 4 Fuel pumps OFF 5 ELECTRIC MASTER OFF After...

Page 106: ...2014 Doc 6 01 15 E b Electrical Fire with Smoke on the Ground 1 ELECTRIC MASTER OFF If the Engine Is Running 2 POWER lever IDLE 3 ENGINE MASTER OFF 4 Fuel pumps OFF When the Engine Has Stopped 6 Cano...

Page 107: ...AKE OFF a If Take Off Can Still Be Aborted 1 POWER lever IDLE 2 Cabin heat OFF 3 Brakes apply bring the airplane to a stop 4 Fuel valve OFF 5 Fuel transfer pump OFF 6 ENGINE MASTER OFF 7 Fuel pumps OF...

Page 108: ...d emergency landing should be carried out Do not attempt to turn back to the airfield Turning back can be fatal Refer to 3 3 2 ENGINE PROBLEMS DURING TAKE OFF After Climbing to a Height FromWhich the...

Page 109: ...opment the front canopy may be unlatched during flight This allows it to partially open in order to improve ventilation The canopy will remain open in this position Flight characteristics will not be...

Page 110: ...ht 1 Cabin heat OFF 2 Select appropriate emergency landing area When it Seems Certain That the Landing Area Will Be Reached 3 Fuel valve OFF 4 POWER lever MAX 5 Emergency windows open if required 6 La...

Page 111: ...nic and electric equipment Also affected from this is the attitude gyro artificial horizon However by switching the EMERGENCY switch ON if installed the emergency battery if installed will supply powe...

Page 112: ...s the maximum horizontal distance traveled in still air is 1 59 NM 2 94 km During this the propeller will continue to windmill NOTE For operation without wheel fairings the glide ratio is reduced to 9...

Page 113: ...osition 1 Adjustable backrests if installed adjust to the upright position described by a placard on the roll over bar and verify proper fixation 2 ENGINE MASTER check OFF 3 Fuel transfer pump OFF 4 F...

Page 114: ...able below Flaps 940 kg 2072 lb 1000 kg 2205 lb 1080 kg 2381 lb 1160 kg 2557 lb 1216 kg 2681 lb up to 1280 kg 2822 lb T O 68 KIAS 70 KIAS 73 KIAS 76 KIAS 77 KIAS 78 KIAS LDG 66 KIAS 69 KIAS 72 KIAS 74...

Page 115: ...lane at the edge of the runway that is located on 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...

Page 116: ...landing on grass is recommended in order to reduce the landing run due to the greater rolling resistance WARNING If sufficient time is remaining the risk of fire in the event of a collision can be red...

Page 117: ...simultaneously 1 POWER lever IDLE 2 Ailerons neutral 3 Rudder full deflection against direction of spin 4 Elevator control stick fully forward When Rotation Has Stopped 5 Flaps UP 6 Rudder neutral 7 E...

Page 118: ...a higher ambient temperature 2 Pitot heating ON 3 Cabin heat ON 4 Cabin air DEFROST 5 POWER lever increase power in order to prevent ice build up on the propeller blades apply power changes periodica...

Page 119: ...only due to a defect If a smell similar to exhaust gases is noticed in the cabin the following measures should be taken 1 Cabin heat OFF 2 Ventilation open 3 Emergency windows open 4 Forward canopy un...

Page 120: ...ow 140 KIAS 5 Land at next suitable airfield END OF CHECKLIST Rear Door Unlocked 4 Airspeed below 140 KIAS 5 Land at the next suitable airfield WARNING Do not try to lock the rear door in flight The s...

Page 121: ...PECTION 4A 4 4A 5 2 BEFORE STARTING ENGINE 4A 12 4A 5 3 STARTING ENGINE 4A 14 4A 5 4 BEFORE TAXIING 4A 17 4A 5 5 TAXIING 4A 19 4A 5 6 BEFORE TAKE OFF 4A 20 4A 5 7 TAKE OFF 4A 25 4A 5 8 CLIMB 4A 27 4A...

Page 122: ...ions apply linear variations between weights Flight Mass 940 kg 2072 lb 1000 kg 2205 lb 1100 kg 2425 lb 1200 kg 2646 lb 1280 kg 2822 lb and above Airspeed for rotation Take off run vR Flaps T O 56 KIA...

Page 123: ...rations shall be supported by dedicated use of the rudder and ailerons together 4A 4 DAILY CHECK Before the first flight of a day it must be ensured that the following checks are performed On conditio...

Page 124: ...tion g Front canopy rear door clean undamaged check locking mechanism function h All electrical equipment OFF i Circuit breakers check all IN if one has popped investigate j POWER lever check conditio...

Page 125: ...Page 4A 5 n Position lights strobe lights ACL check OFF o Taxi lights landing lights check OFF p ELECTRIC MASTER OFF q Foreign objects check r Controls and trim free and correct s Emergency axe if in...

Page 126: ...ces should be checked for freedom of movement CAUTION In low ambient temperatures the airplane should be completely cleared of ice snow and similar accumulations CAUTION Prior to flight remove such it...

Page 127: ...fuel may spill over through the tank vent f Tank drain drain to check for water and sediment drain until free of contamination g Stall warning check function suction h Tank filler check closed for fu...

Page 128: ...installed check for improper mounting or obvious damage 3 Fuselage Left Side a Canopy left side visual inspection b Door lock if installed unlocked key removed c Rear cabin door window visual inspect...

Page 129: ...bjects in aileron paddle visual inspection f Wing let visual inspection g Position light strobe light ACL visual inspection h Tie down check clear i Entire wing surface visual inspection j 2 stall str...

Page 130: ...oil level check dipstick inspection door on left side b Gearbox oil level check visually inspection door on left side c Cowling visual inspection d 4 air intakes on front cowling check e 2 air intake...

Page 131: ...o Chocks remove p Exhaust visual inspection WARNING The exhaust can cause burns when it is hot 9 Underside a Antennas visual inspection b Gascolator pull down on drain to check for water and sediment...

Page 132: ...usted and locked 3 Passengers instructed 4 Adjustable backrests if installed adjusttothe upright position described on theroll over bar and verify proper fixation 5 Safety harnesses all fastened 6 Rea...

Page 133: ...OSED 17 VOTER switch check AUTO 18 Fuel pumps check OFF 19 AVIONIC MASTER check OFF 20 ELECTRIC MASTER ON 21 G1000 if installed wait until power up completed Press ENT on MFD to acknowledge NOTE If th...

Page 134: ...econds because of possible overheating of the starter motor If the STARTER annunciation on the G1000 if installed or START on the White Wire annunciator panel if installed comes on after the engine ha...

Page 135: ...re annunciator panel is installed is indicated only when the engine is cold 4 Annunciations engine indications check WARNING Before starting the engine the pilot must ensure that the propeller area is...

Page 136: ...7 Annunciations STARTER if G1000 is installed or START if White Wire annunciator panel is installed check OFF 8 Annunciations Oil pressure check OK 9 Circuit breakers check all IN 10 Idle RPM check 71...

Page 137: ...heckannunciationand observe an increase in alternator load 7 Pitot heating OFF 8 Strobe lights ACLs check ON 9 Position lights landing and taxi lights as required CAUTION When taxiing at close range t...

Page 138: ...onnect 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 if G...

Page 139: ...rrect indications 4 Fuel pumps check OFF CAUTION When taxiing on a poor surface select the lowest possible RPM to avoid damage to the propeller from stones or similar items CAUTION Avoid prolonged per...

Page 140: ...ots operators must ensure that there are no obstructions between the canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight...

Page 141: ...ce there is a malfunction in the engine control system Terminate flight preparation The whole test procedure must be completed without any error ECU A B FAIL if G1000 is installed or ECU A B if White...

Page 142: ...PM check below 1000 RPM 3 Fuel pumps check OFF 4 VOTER switch check AUTO NOTE If the VOTER switch is not in the AUTO position the ECU test will not start 5 All engine temperatures check in the green r...

Page 143: ...al fuel pumps are switched over as well 10 VOTER switch ECU A 11 Engine check running without a change shake may occur 12 VOTER switch AUTO 13 Engine check running without a change shake may occur 14...

Page 144: ...icated 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 OAT Altitude ft 35 C 31 F 20...

Page 145: ...l 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 genera...

Page 146: ...wind conditions operation on unpaved surfaces and gusty conditions may occur 6 Airspeed for initial climb see table below 940 kg 2072 lb 1000 kg 2205 lb 1100 kg 2425 lb 1200 kg 2646 lb 1280 kg 2822 lb...

Page 147: ...ure and or coolant temperature reaches the yellow range during climb flight should be continued with an airspeed increased by 5 kt and power reduced by 10 reduced climb rate for better engine cooling...

Page 148: ...Trim as required 4 Fuel transfer repeat as required in accordance with 4A 5 10 FUEL TRANSFER NOTE The engine manufacturer recommends a cruise power setting of 75 NOTE Proper operation of the transfer...

Page 149: ...iter h 1 Fuel transfer switch ON NOTE The transfer pump turns off automatically to avoid overfilling the main tank The switch remains in its position If the pump is not turned off it will continue pum...

Page 150: ...ng Procedures DA 40 NG AFM Page 4A 30 Rev 3 01 Jul 2014 Doc 6 01 15 E 4A 5 11 DESCENT 1 POWER lever as required 2 Airspeed as required 3 Trim as required 4 Annunciations engine indications monitor END...

Page 151: ...Section 4B 7 LANDING WITH HIGH LANDING MASS CAUTION For landing the adjustable backrests if installed must be fixed in the upright position 1 Adjustable backrests if installed adjust to the upright po...

Page 152: ...6 KIAS 76 KIAS 77 KIAS 9 FLAPS as required 10 POWER lever as required 11 Trim as required 12 Final approach speed see table below Flaps 940 kg 2072 lb 1000 kg 2205 lb 1100 kg 2425 lb 1200 kg 2646 lb 1...

Page 153: ...AFM Normal Operating Procedures Doc 6 01 15 E Rev 3 01 Jul 2014 Page 4A 33 4A 5 13 GO AROUND 1 POWER lever MAX 2 Airspeed 72 KIAS 3 Flaps T O Above a Safe Height 4 Airspeed 88 KIAS 5 Flaps UP END OF C...

Page 154: ...M Page 4A 34 Rev 3 01 Jul 2014 Doc 6 01 15 E 4A 5 14 AFTER LANDING 1 POWER lever IDLE 2 Brakes as required 3 Transponder OFF STBY 4 Pitot heating OFF 5 Avionics as required 6 Lights as required 7 Flap...

Page 155: ...ait until the engine indications on the G1000 MFD if installed or MED if installed disappear prior to switching the ELECTRIC MASTER OFF This ensures that engine and flight data can be written to non v...

Page 156: ...NSPECTION 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 5 17 PARKING 1 Parking brake re...

Page 157: ...ted to electrical ground Grounding points unpainted areas on steps left and right Use of Fuel Additives CAUTION Only approved fuel additives not exceeding the approved concentrations may be used refer...

Page 158: ...fuel additives in the airplane log every time fuel additives are added Typical Dosing Quantities a KATHON FP 1 5 Fuel Quantity Fuel Additive KATHON FP 1 5 100 ppm Liter US gal kg lb ml oz 50 13 2 40 2...

Page 159: ...2 88 68 58 9 1 99 100 26 4 80 4 177 37 117 9 3 99 150 39 6 120 6 266 05 176 8 5 98 Densities used for calculation Fuel 0 804 kg l PRIST Hi Flash 1 05 kg l Do not batch blend 4A 5 20 FLIGHT AT HIGH AL...

Page 160: ...Normal Operating Procedures DA 40 NG AFM Page 4A 40 Rev 3 01 Jul 2014 Doc 6 01 15 E Intentionally left blank...

Page 161: ...4B 9 4B 2 7 VOLTAGE 4B 10 4B 2 8 CURRENT 4B 11 4B 3 CAUTION ALERTS 4B 12 4B 3 1 ECU A FAILURE 4B 12 4B 3 2 ECU B FAILURE 4B 14 4B 3 3 FUEL QUANTITY LOW 4B 16 4B 3 4 COOLANT LEVEL 4B 18 4B 3 5 PITOT HE...

Page 162: ...controlled landing in a field represents a lower risk than the attempt to reach the nearest airfield under all circumstances NOTE If no level landing area is available a landing on an upward slope sh...

Page 163: ...E Rev 3 01 Jul 2014 Page 4B 3 CAUTION If sufficient 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 OFF...

Page 164: ...RPM 1 Reduce power 2 Keep RPM within the green range using the POWER lever NOTE An RPM in the yellow range is permissible for up to 5 minutes if required e g for go around or take off If the above men...

Page 165: ...ge low coolant level NOTE During an extended descent 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...

Page 166: ...ERATURE a High Oil Temperature Proceed according to Section 3 2 2 OIL TEMPERATURE b Low Oil Temperature NOTE During an extended descent from high altitudes with a low power setting oil temperature may...

Page 167: ...itoring temperatures If the temperature is outside of the green range Reduce power on engine WARNING Land at the nearest suitable airfield Prepare for an engine failure in accordance with 3 7 1 EMERGE...

Page 168: ...imposed by the engine manufacturer However there is a delay between power changes and gearbox temperature Therefore a cautionary range has been added to the G1000 if installed or MED if installed gea...

Page 169: ...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...

Page 170: ...b Low Voltage During Flight 1 Circuit breakers check 2 Electrical equipment OFF if not needed If Low Voltage Condition Still Exists Follow procedure in Section 3 2 8 ALTERNATOR FAIL NOTE This procedur...

Page 171: ...4 Page 4B 11 4B 2 8 CURRENT This caution is indicated when the consumption of electric power exceeds 60 A 1 Electrical equipment switch OFF as necessary and possible to reduce electric load If the pro...

Page 172: ...massage remains until 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...

Page 173: ...itable airfield After landing you may use a ECU A Caution on the ground as ECU caution clearing procedure NOTE An ECU FAIL caution is caused by various types of malfunctions These include internal ECU...

Page 174: ...s until 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 v...

Page 175: ...itable airfield After landing you may use a ECU B Caution on the ground as ECU caution clearing procedure NOTE An ECU FAIL caution is caused by various types of malfunctions These include internal ECU...

Page 176: ...The caution message may be triggered during turns which are flown with slip or while taxiing in curves If FUEL LOW if G1000 is installed or LOW FUEL if White Wire Annunciator Panel is installed Cauti...

Page 177: ...the Caution Does Not Extinguish Be prepared for an emergency landing Proceed in accordance with Section 3 7 1 EMERGENCYLANDING WITHENGINE OFF WARNING If air enters the high pressure fuel pump e g empt...

Page 178: ...oolant This will subsequently lead to decreased engine cooling capability loss of engine power due to engine failure 1 Annunciations engine instruments monitor Refer to Section 4B 2 2 COOLANT TEMPERAT...

Page 179: ...GINE CAUTION IF WHITE WIRE ANNUNCIATOR PANEL IS INSTALLED Engine limit exceeded 1 Engine indications check 2 Acknowledge button press NOTE If an indication is near the end of the green range it may ha...

Page 180: ...20 Rev 3 01 Jul 2014 Doc 6 01 15 E 4B 4 CANOPY IN COOLING GAP POSITION CAUTION If take off was inadvertently done with the canopy in the cooling gap position do not attempt to close the canopy in flig...

Page 181: ...Modified Approach Procedure Depending on the Available Flap Setting NOTE For landing distances with an abnormal flap position refer to 5 3 12 LANDING DISTANCE ABNORMAL FLAP POSITION a Only UP Availabl...

Page 182: ...table below 940 kg 2072 lb 1000 kg 2205 lb 1100 kg 2425 lb 1200 kg 2646 lb 1216 kg 2681 lb 1280 kg 2822 lb and above 68 KIAS 70 KIAS 74 KIAS 77 KIAS 77 KIAS 78 KIAS Land at a flat approach angle use...

Page 183: ...PFD if G1000 is installed backup instruments verify periodically 5 Continue flight below vO refer to Section 2 2 6 Land on the next suitable airfield CAUTION Due to possible damage to the airplane ob...

Page 184: ...5 12 APPROACH AND LANDING for landings with a mass up to 1216 kg 2681 lb and if M M 40 574 is carried out for landings with a mass up to 1280 kg 2822 lb Perform landing approach and landing according...

Page 185: ...locked key removed 7 Front canopy Position 1 or 2 cooling gap 8 Canopy lock if installed unlocked key removed CAUTION When operating the canopy pilots operators are to ensure that there are no obstruc...

Page 186: ...nal power connect 21 ELECTRIC MASTER ON 22 G1000 if installed wait until power up completed Press ENT on MFD to acknowledge NOTE If the G1000 avionics system is installed the engine instruments are on...

Page 187: ...unciator panel if installed comes on after the engine has started and the START KEY has been released set the ENGINE MASTER to OFF and investigate the problem WARNING If the oil pressure has not moved...

Page 188: ...4 Annunciations engine indications check WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered After the GLOW ON if G1000 is instal...

Page 189: ...B 29 8 Annunciations Oil pressure check OK 9 Circuit breakers check all IN 10 Idle RPM check 710 30 RPM above 7 000 ft pressure altitude idle RPM might be higher 11 External power disconnect 12 Extern...

Page 190: ...Abnormal Operating Procedures DA 40 NG AFM Page 4B 30 Rev 3 01 Jul 2014 Doc 6 01 15 E Intentionally left blank...

Page 191: ...DENSITY ALTITUDE 5 6 5 3 4 INTERNATIONAL STANDARD ATMOSPHERE 5 7 5 3 5 STALLING SPEEDS 5 8 5 3 6 WIND COMPONENTS 5 10 5 3 7 TAKE OFF DISTANCE 5 11 5 3 8 CLIMB PERFORMANCE TAKE OFF CLIMB 5 17 5 3 9 CLI...

Page 192: ...orly maintained airplane The performances given can be attained if the procedures quoted in this manual are applied and the airplane has been well maintained Whereappropriate anyflightperformancedegra...

Page 193: ...e 5 3 For operation at outside air temperatures lower than provided in these tables use data for lowest temperature shown Use extreme caution for operation at outside air temperatures higher than prov...

Page 194: ...BRATION Airspeed Indicator Calibration Indicated Airspeed KIAS Calibrated Airspeed KCAS at Various Flap Settings UP T O LDG 65 Not applicable 64 64 70 70 69 69 75 75 74 74 80 79 79 78 85 84 84 83 90 8...

Page 195: ...re 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 Fue...

Page 196: ...6000 4000 2000 0 0 500 1000 1500 2000 2500 3000 3500 4000 0 500 1000 1500 2000 2500 3000 3500 4000 20 10 0 10 20 30 500 32 50 68 86 14 4 C F 5 3 3 PRESSURE ALTITUDE DENSITY ALTITUDE Conversion from pr...

Page 197: ...DA 40 NG AFM Performance Doc 6 01 15 E Rev 3 01 Jul 2014 Page 5 7 5 3 4 INTERNATIONAL STANDARD ATMOSPHERE...

Page 198: ...KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 58 56 59 60 64 66 76 79 T O 54 53 58 57 63 63 75 74 LDG 55 52 56 55 61 61 72 73 1100 kg 2425 lb Bank Angle 0 30 45 60 Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIA...

Page 199: ...formance Doc 6 01 15 E Rev 3 01 Jul 2014 Page 5 9 1310 kg 2888 lb Bank Angle 0 30 45 60 Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 66 63 68 68 74 75 88 89 T O 62 59 65 63 71 70 84 83 LDG 60 58 6...

Page 200: ...110 120 130 160 180 0 10 20 16 30 40 Crosswind Component kts 10 20 10 20 30 40 Headwind Component kts Flight Direction 0 Maximum demonstrated Crosswind Component 5 3 6 WIND COMPONENTS Example Flight d...

Page 201: ...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 30 Grass runway dry 25 cm 9 8 in long Increase the ground roll by 45 Grass runway longe...

Page 202: ...ION The factors in the above corrections are typical values On wet ground or wet soft grass covered runways the take off roll may become significantly longer than stated In any case the pilot must all...

Page 203: ...30 780 830 646 3000 914 Ground Roll 440 470 500 540 580 625 463 15 m 50 ft 650 680 720 780 840 890 677 4000 1219 Ground Roll 470 500 540 590 630 680 490 15 m 50 ft 690 720 780 840 900 960 708 5000 152...

Page 204: ...20 770 820 636 3000 914 Ground Roll 435 465 495 535 580 620 460 15 m 50 ft 640 670 710 770 820 880 668 4000 1219 Ground Roll 470 495 535 585 625 675 486 15 m 50 ft 680 720 770 830 890 950 701 5000 152...

Page 205: ...0 650 700 740 576 3000 914 Ground Roll 390 415 445 485 520 560 413 15 m 50 ft 580 610 650 700 750 800 602 4000 1219 Ground Roll 420 445 480 525 565 610 438 15 m 50 ft 610 640 700 750 800 860 633 5000...

Page 206: ...530 570 600 650 498 3000 914 Ground Roll 340 360 385 415 450 480 356 15 m 50 ft 500 530 560 610 650 690 523 4000 1219 Ground Roll 360 385 415 455 490 525 377 15 m 50 ft 530 560 600 650 700 750 549 50...

Page 207: ...Airspeed 72 KIAS NOTE The tables on the following pages show the rate of climb The gradient of climb can be calculated using the following formulae NOTE For operation without wheel fairings a climb ra...

Page 208: ...0 475 580 8000 2438 580 570 555 540 525 480 435 557 10000 3048 555 540 525 510 480 435 533 12000 3658 525 510 495 480 435 400 509 14000 4267 500 485 475 460 425 360 492 16000 4877 490 470 440 385 325...

Page 209: ...5 600 545 500 633 10000 3048 630 615 600 585 550 500 607 12000 3658 595 580 565 550 505 460 581 14000 4267 575 560 545 530 490 420 564 16000 4877 560 540 510 450 380 560 16400 4999 545 520 490 430 360...

Page 210: ...ditions POWER lever 92 or max 2100 RPM Flaps UP Airspeed 88 KIAS NOTE The graph on the following page shows the rate of climb The gradient of climb cannot easily be determined with a graph but it can...

Page 211: ...540 621 8000 2438 620 615 605 600 590 550 505 609 10000 3048 605 600 590 580 555 510 596 12000 3658 590 580 570 560 520 480 581 14000 4267 575 565 555 540 500 445 568 16000 4877 560 550 520 470 405 56...

Page 212: ...675 630 585 697 10000 3048 695 685 680 670 640 590 684 12000 3658 680 665 655 645 600 560 668 14000 4267 660 650 640 625 585 520 655 16000 4877 650 640 605 550 480 648 16400 4999 635 620 585 525 455 6...

Page 213: ...OAT Example OAT at take off 11 C 52 F Airfield pressure altitude 2000 ft 1200 m Initial climb weight 1310 kg 2888 lb OAT at cruise 17 C 2 F Cruise altitude 16000 ft 4900 m Time fuel and distance to cl...

Page 214: ...6 0 9 9 6000 1829 3 38 91 640 3 2 9 1 3 14 8000 2438 1 30 92 630 3 2 13 1 8 19 10000 3048 5 23 94 625 3 2 16 2 2 25 12000 3658 9 16 95 620 3 2 19 2 7 31 14000 4267 13 9 97 615 3 1 23 3 1 37 16000 4877...

Page 215: ...5 0 8 8 6000 1829 3 38 91 725 3 7 8 1 1 13 8000 2438 1 30 92 720 3 7 11 1 5 17 10000 3048 5 23 94 715 3 6 14 1 9 22 12000 3658 9 16 95 710 3 6 17 2 3 27 14000 4267 13 9 97 700 3 6 20 2 8 32 16000 4877...

Page 216: ...FORMANCE NOTE For operation without wheel fairings a performance reduction of 4 TAS at all power settings must be expected Conditions Flaps UP Landing gear retracted Weight 1310 kg 2888 lb Forconversi...

Page 217: ...000 2438 92 8 3 142 92 8 3 143 92 8 3 145 92 8 3 146 89 8 0 146 75 6 6 130 75 6 6 131 75 6 6 133 75 6 6 134 75 6 6 135 60 5 1 117 60 5 1 118 60 5 1 119 60 5 1 120 60 5 1 121 45 4 0 99 45 4 0 99 45 4 0...

Page 218: ...headwind Tailwind Increase 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 30 Grass runway dry longer than 5 cm 2 in I...

Page 219: ...han 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 slo...

Page 220: ...0 810 670 3000 914 Ground Roll 335 350 365 385 410 435 345 15 m 50 ft 670 690 710 750 800 840 681 4000 1219 Ground Roll 350 360 380 405 430 455 356 15 m 50 ft 680 700 740 780 830 870 692 5000 1524 Gro...

Page 221: ...50 800 657 3000 914 Ground Roll 330 340 355 375 400 425 338 15 m 50 ft 650 670 700 740 780 830 667 4000 1219 Ground Roll 340 355 375 395 420 445 348 15 m 50 ft 670 690 720 770 810 860 679 5000 1524 Gr...

Page 222: ...740 780 639 3000 914 Ground Roll 310 320 335 355 375 400 319 15 m 50 ft 630 650 680 720 760 800 649 4000 1219 Ground Roll 320 335 350 375 395 420 329 15 m 50 ft 650 670 700 740 790 830 657 5000 1524 G...

Page 223: ...710 750 617 3000 914 Ground Roll 285 295 310 330 345 370 294 15 m 50 ft 610 630 650 690 730 770 623 4000 1219 Ground Roll 295 305 325 345 365 385 302 15 m 50 ft 620 640 670 710 750 800 630 5000 1524 G...

Page 224: ...01 15 m 50 ft 810 850 900 950 1010 1060 849 3000 914 Ground Roll 400 430 455 485 515 545 425 15 m 50 ft 840 890 940 1000 1060 1120 881 4000 1219 Ground Roll 430 460 490 520 550 580 450 15 m 50 ft 880...

Page 225: ...80 930 980 1040 829 3000 914 Ground Roll 395 420 445 475 505 535 416 15 m 50 ft 820 870 930 980 1040 1090 863 4000 1219 Ground Roll 420 450 480 510 540 570 441 15 m 50 ft 860 920 970 1030 1090 1150 89...

Page 226: ...860 910 960 1020 811 3000 914 Ground Roll 375 400 420 450 475 505 394 15 m 50 ft 800 850 900 950 1010 1060 837 4000 1219 Ground Roll 400 425 455 480 510 540 416 15 m 50 ft 840 890 940 1000 1060 1110 8...

Page 227: ...80 830 880 930 980 783 3000 914 Ground Roll 345 370 390 415 440 465 364 15 m 50 ft 760 810 860 920 970 1020 804 4000 1219 Ground Roll 370 395 420 445 470 500 386 15 m 50 ft 800 850 900 950 1010 1060 8...

Page 228: ...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 3 0 for Ma...

Page 229: ...5 360 350 340 315 285 364 6000 1829 365 360 350 345 335 315 285 351 8000 2438 350 345 335 320 310 280 250 336 10000 3048 330 320 310 295 275 240 315 1280 2822 SL 425 415 410 400 395 385 370 345 400 20...

Page 230: ...Alt m Rate of Climb ft min Outside Air Temperature C F 20 10 0 10 20 30 40 50 ISA 4 14 32 50 68 86 104 122 Page 5 40 Rev 3 01 Jul 2014 Doc 6 01 15 E 1100 2425 SL 615 615 610 605 605 595 575 535 607 20...

Page 231: ...s Windmilling propeller 1 9 7 1 59 NM 2 94 km Conditions Flaps UP Airspeed 88 KIAS CAUTION The propeller will keep windmilling under all expected conditions Do not attempt to stop the propeller intent...

Page 232: ...Mass 1280 kg 2825 lb ICAO Annex 16 Chapter X 74 5 dB A CS 36 Subpart C 74 5 dB A If the Exhaust Pipe with Muffler M M 40 434 or O M 40 310 is installed ICAO Annex 16 Chapter X 71 5 dB A CS 36 Subpart...

Page 233: ...CTION 6 2 6 2 DATUM PLANE 6 3 6 3 MASS AND BALANCE REPORT 6 3 6 4 FLIGHT MASS AND CENTER OF GRAVITY 6 5 6 4 1 MOMENT ARMS 6 7 6 4 2 LOADING DIAGRAM 6 8 6 4 3 CALCULATION OF LOADING CONDITION 6 9 6 4 4...

Page 234: ...s CG position is described in this Chapter Over and above this there is a comprehensive list of the equipment approved for this airplane Equipment List as also a list of that equipment installed when...

Page 235: ...t forward point of the root rib on the stub wing 6 3 MASS AND BALANCE REPORT The empty mass and the corresponding CG position established before delivery are the first entries in the Mass and Balance...

Page 236: ...eport on structural or equipment changes DA 40 NG Serial No Registration Page No Date Entry No Description of Part or Modification Changes in Mass Current Empty Mass Addition Subtraction Mass Moment A...

Page 237: ...indicators to determine the fuel quantity If an indicator shows 14 US gal up to 19 5 US gal can be in the Long Range Tank In this case the exact quantity must be determined with the alternate means fo...

Page 238: ...asses and moments for the individual items 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 admissibl...

Page 239: ...90 6 in Rear seats 3 25 m 128 0 in Wing tank Standard Long Range 2 63 m 103 5 in Baggage in standard compartment 3 65 m 143 7 in Baggage in baggage tube 4 32 m 170 1 in Baggage in short baggage extens...

Page 240: ...Mass Balance DA 40 NG AFM Page 6 8 Rev 3 01 Jul 2014 Doc 6 01 15 E 6 4 2 LOADING DIAGRAM...

Page 241: ...180 8 189 253 2 Front seats Lever arm 2 30 m 90 6 in 150 331 345 0 29 989 3 Rear seats Lever arm 3 25 m 128 0 in 0 0 0 0 4 Standard baggage comp Lever arm 3 65 m 143 7 in 20 44 73 0 6 323 5 Baggage t...

Page 242: ...m 2 63 m 103 5 in 89 196 234 1 20 286 11 Total mass and total moment with full fuel tanks Total 9 plus 10 1 159 2 555 2 832 9 245 851 12 The total moments from rows 9 and 11 2 598 8 and 2 832 9 kgm 22...

Page 243: ...ront seats Lever arm 2 30 m 90 6 in 150 331 345 0 29 989 3 Rear seats Lever arm 3 25 m 128 0 in 0 0 0 0 4 Standard baggage comp Lever arm 3 65 m 143 7 in 20 44 73 0 6 323 5 Baggage tube Lever arm 4 32...

Page 244: ...2 63 m 103 5 in 124 273 326 1 28 256 11 Total mass and total moment with full fuel tanks Total 9 plus 10 1 194 2 632 2 924 9 253 821 12 The total moments from rows 9 and 11 2 598 8 and 2 924 9 kgm 22...

Page 245: ...1 The flight CG position must be within the following limits Most forward CG 2 40 m 94 5 in aft of DP from 940 kg to 1080 kg 2072 lb to 2381 lb 2 46 m 96 9 in aft of DP at 1280 kg 2822 lb If M M 40 66...

Page 246: ...ss Moment kgm 2800 3000 3200 Flight Mass kg 2500 2400 2300 2200 2100 2000 Flight Mass lb 200 000 220 000 240 000 260 000 Flight Mass Moment in lb Max Zero Fuel Mass 2600 2700 2800 2900 280 000 Example...

Page 247: ...ow The items of equipment installed in your particular airplane are indicated in the appropriate column The set of items marked as installed constitutes the Equipment Inventory NOTE The equipment list...

Page 248: ...ch servo GSA 81 011 00878 20 Garmin Pitch servo mount GSM 85 011 00894 07 Garmin Pitch servo mount GSM 86 011 01904 03 Garmin Pitch clutch cartridge 011 02147 15 Garmin Roll servo GSA 81 011 00878 00...

Page 249: ...nnector DA4 2443 10 00 Diamond Aircraft Additional alternator ES 10024B 2 Kelly Aerospace Alternator pulley D44 2416 00 34X03 Diamond Aircraft Alternator pulley D44 2416 00 70_1 Diamond Aircraft Gear...

Page 250: ...00 3 220 Safety belt RH pax 5 01 Series 5 01 2H0710 Schroth 2 250 1 020 126 800 3 220 Safety belt pilot 5 01 Series 5 01 2G0701 Schroth 2 110 0 960 92 520 2 350 Safety belt co pilot 5 01 Series 5 01 2...

Page 251: ...warning horn assy A DA4 2739 10 00 Diamond Aircraft Stall warning horn assy B DA4 2739 10 00X01 Diamond Aircraft Stall warning horn assy C DA4 2739 10 00X02 Diamond Aircraft Stall warning horn assy D...

Page 252: ...72 03 Garmin 6 400 2 900 70 080 1 780 Multi function display MFD GDU 1040 011 00972 10 Garmin 6 400 2 900 70 080 1 780 Flight timer 85094 12 Hobbs Digital chronometer with OAT M803 28V Davtron Annunci...

Page 253: ...D1 24V 37776 Newark Ballast GEN5 D1 24V 37776 Newark Taxi light HID Lamp D1S 39663 Newark Landing light HID Lamp D1S 39663 Newark LED Taxi light 71125 01 0771125 23 Whelen 0 300 0 140 79 920 2 030 LE...

Page 254: ...TRA 62800 001 Telex Pitot Static probe heated AN5814 2 PST 305 Aeroinstruments Alternate static valve DA4 3111 51 00 Diamond Aircraft Backup altimeter 5934PD 3 United Instruments 0 496 0 225 70 080 1...

Page 255: ...800 1 270 154 900 3 935 Magnetometer GMU 44 011 00870 00 Garmin 0 350 0 160 103 800 2 638 Magnetometer GMU 44 011 00870 10 Garmin 0 350 0 160 103 800 2 638 VOR LOC GS antenna CI 157P Comant Dual VOR d...

Page 256: ...II 11922 PS Engineering Transponder GTX 328 011 01684 00 Garmin Altitude digitizer SAE5 35 305154 00 Sandia Aerospace P S probe heater fail sensor DA4 3031 01 00 Diamond Aircraft Altimeter inHg mbar p...

Page 257: ...0NG 002 Austro Engine ENGINE STARTING Glow plug control unit E4A 94 200 000 Austro Engine Starter E4A 93 000 000 Austro Engine ELECTRICAL POWER Alternator E4A 91 000 000 Austro Engine Alternator E4A 9...

Page 258: ...ipe with muffler D44 7806 20 00_2 Diamond Aircraft PROPELLER Propeller MTV 6 R 190 69 mt propeller Governor P 853 16 mt propeller FUEL TANK SYSTEM Fuel probe assy LH inboard D4D 2817 13 00x01 Diamond...

Page 259: ...Amerex A620T is UL approved and can be used in aircraft registered in Canada and the USA For aircraft registered in other countries contact the local airworthiness authority Place ___________________...

Page 260: ...DA 40 NG AFM Mass and Balance Doc No 6 01 15 E Rev 3 01 Jul 2014 Page 6 28 Intentionally left blank...

Page 261: ...TS AND SAFETY HARNESSES 7 16 7 7 BAGGAGE COMPARTMENT 7 18 7 8 CANOPY REAR DOOR AND CABIN INTERIOR 7 18 7 9 POWER PLANT 7 21 7 9 1 ENGINE GENERAL 7 21 7 9 2 OPERATING CONTROLS 7 22 7 9 3 PROPELLER 7 25...

Page 262: ...esistant matting which is covered on the engine side by stainless steel cladding The two main bulkheads are GFRP CFRP items Wings The wings have a front and rear spar each wing has a top shell and a b...

Page 263: ...which are hinge pins mounted in an aluminum bracket They are secured in position by a roll pin The absence of this roll pin can lead to the loss of the hinge pin and a consequent loss of flight safet...

Page 264: ...tube The torsion tube is located in the fuselage creating a connection between the left and right flaps Operation A rod end bearing is screwed into a steel push rod and locked by means of a jam nut wh...

Page 265: ...tected by a limit switch to guard against over running the end positions The electrical flap drive has an automatic circuit breaker which can also be operated manually Flap Position Indicator The curr...

Page 266: ...well as the connection to the push rod can be visually inspected at the upper end of the rudder Rudder Construction GFRP sandwich Hinges Upper hinge One bolt Lower hinge Bearing bracket including rud...

Page 267: ...e down Turn wheel to the rear nose up Pedal Adjustment NOTE The pedals may only be adjusted on the ground The pedals are unlocked by pulling the black handle which is located behind the rear attachmen...

Page 268: ...t a t i c i s o p e n C o n d u c t AP a n d t rim c h e c k p ri o r to e a ch fl i g ht se e AF M A u to p i lo t O F F d u r i n g t ak e o ff a n d la n d i n g M a xi m u m s pe e d f o r a u to...

Page 269: ...FR and IFR Al l aer obatics maneuvers inc luding spinning ar e prohibited For fur ther opera ti o n al limitations refer to the A irplane Flight M anu al No smoking V V A A Limitations for GFC 70 0 Au...

Page 270: ...Airplane Description DA 40 NG AFM Page 7 10 Rev 3 01 Jul 2014 Doc 6 01 15 E Instrument Panel with SED MED and White Wire Annunciator Panel...

Page 271: ...switches 31 Directional Gyro 12 Emergency switch 32 Turn Bank indicator 13 Circuit breakers 33 Intercom 14 Flap selector switch 34 Annunciator panel 15 Alternate static valve 35 Main Engine Display ME...

Page 272: ...wisting Unconditioned ambient air is supplied to the interior through an inlet on the bottom surface of the left wing To increase cabin temperatures when operating at low outside air temperatures a ve...

Page 273: ...on Doc 6 01 15 E Rev 3 01 Jul 2014 Page 7 13 NACA Air Inlet NACA Air Inlet Cabin Air Control Cabin Air Control RH Rear Cabin Air Control Cabin Air Control LH Cabin Air Exhaust Cabin Air Exhaust Sealed...

Page 274: ...of performance see Chapter 5 Wheel Brakes Hydraulically operating disk brakes act on the wheels of the main landing gear The wheel brakes are individually operated by means of toe pedals Parking Brake...

Page 275: ...g Pilot s Pedals Master Cylinders Co Pilot s Pedals Vented Plug Brake Fluid Reservoir Fluid Level LOCK PARKING BRAKE RELEASE Flexible Hose Parking Brake Valve Brake Disc Brake Caliper Pressure Plate B...

Page 276: ...laid forward after pulling upwards on the knob of the locking bolt If front seats with adjustable backrests are installed O M 40 252 the angle of the backrests can be adjusted for best comfort The bac...

Page 277: ...umbar Support Lever Lumbar Support in the upright position If possible set the backrest lever to the locked position The mechanism must be repaired at the next scheduled inspection The lumbar support...

Page 278: ...front canopy is closed by pulling down on the canopy frame and locking it with the handle on the left hand side of the canopy frame On locking steel bolts catch into mating holes in polyethylene block...

Page 279: ...per prevents the door from dropping in strong winds the assembly must be held The rear door is protected against unintentional opening by an additional lever The door can be locked by a locking mechan...

Page 280: ...installed on the floor panel under the co pilot s seat see Figure below If the canopy can not be opened in case of an emergency use the emergency axe to break through the canopy WARNING Make sure not...

Page 281: ...Turbo charger with intercooler Displacement Max power 123 5 kW 165 6 DIN HP at 2300 RPM at sea level and ISA Max continuous power 114 0 kW 152 8 DIN HP at 2100 RPM at sea level and ISA Theindicationsf...

Page 282: ...ower LOAD Lever forward MAX Full power Lever to rear IDLE Idle The ECU controls manifold pressure injected fuel quantity and propeller speed according to the desired engine power preselected with the...

Page 283: ...be cranked with the ENGINE MASTER switched to ON To shut down the engine the ENGINE MASTER is switched to OFF ECU VOTER For normal operation the switch is set to AUTO The engine is controlled by eithe...

Page 284: ...the other a slight shake of the engine may occur Finally the ECU switches back After that both caution lights must extinguish and the engine must run without a change Alternate Air In the event of pow...

Page 285: ...ades combine the lowest weight whilst minimizing vibration Propeller Control The propeller pitch is controlled by the P 853 16 mt propeller governor The pitch is set by the ECU via an electro mechanic...

Page 286: ...ration CAUTION Operation on the ground at high RPM should be avoided as far as possible as the blades could suffer stone damage For this reason a suitable site for engine runs should be selected where...

Page 287: ...DA 40 NG AFM Airplane Description Doc 6 01 15 E Rev 3 01 Jul 2014 Page 7 27 7 9 4 FUEL SYSTEM Standard Tank Schematic...

Page 288: ...Airplane Description DA 40 NG AFM Page 7 28 Rev 3 01 Jul 2014 Doc 6 01 15 E Long Range Tank Schematic...

Page 289: ...ter Fuel Pumps Normal Off Main Tank Auxiliary Tank Transfer Pump Fuel Valve Normal Fuel Supply Normal Fuel Transfer Emergency Emergency Fuel Supply Emergency Fuel Return Fuel Return Engine Fuel Filter...

Page 290: ...not injected into the combustion chambers is routed through the AUX fuel tank right wing and fed back into the MAIN fuel tank left wing This way hot fuel from the rail is cooled and cold fuel in both...

Page 291: ...iliary tank is empty Fuel Pumps The engine is supplied with fuel by two parallel installed independent low pressure electrically driven fuel pumps During normal operation one of the two fuel pumps is...

Page 292: ...a fuel transfer failure The check valve with capillary allows air to enter the tank but prevents flow of fuel to the outside The capillary equalizes the air pressure during climb The hose termination...

Page 293: ...can be found in Chapter 5 PERFORMANCE Long Range Tank if installed The tank chamber has a capacity of approx 5 US gal 19 liter The ventilation system of the main and the auxiliary tank remains unchan...

Page 294: ...measuring device has a recess which fits the airfoil of the wing With this recess the device is held against the stall strip at the leading edge of the wing The exact position is marked by a bore in...

Page 295: ...changer and a bypass circuit cabin heat exchanger The radiator circuit is only open during hot coolant temperatures This assures that a cold engine will warm up quickly Upon reaching approximately 80...

Page 296: ...er through the higher density of cold air The exhaust system contains a manifold which collects exhaust gases from the outlets of the cylinders and feeds them to the turbine of the turbo charger Behin...

Page 297: ...on the LH side of the upper cowling If required oil can also be filled in there for specified oil types refer to 2 4 POWER PLANT LIMITATIONS Gearbox and Propeller Governor System The second oil circu...

Page 298: ...Airplane Description DA 40 NG AFM Page 7 38 Rev 3 01 Jul 2014 Doc 6 01 15 E 7 10 ELECTRICAL SYSTEM Electrical System Schematic...

Page 299: ...ovides an indication of the power being supplied to the electrical system by the alternator including the current for battery charging In the event of a main battery failure the field of the alternato...

Page 300: ...l Unit ECU B only Under normal operating conditions the ECU backup batteries are charged by the ECU bus In the event of an alternator failure and a depleted main battery the ECU backup batteries autom...

Page 301: ...us 2 and heavy duty power to the starter The battery bus 1 is also connected to the power input line of the external power plug Battery Bus 2 The battery bus 2 is connected to the battery bus 1 via a...

Page 302: ...wer Essential Bus Under normal operating conditions the essential bus is connected to the main bus via the essential tie relay The essential bus provides power to the consumers connected to the essent...

Page 303: ...xi lights are built into the left wing and are each operated by means of a switch LANDING TAXI on the row of switches on the instrument panel Position and Strobe Lights Combined position and strobe li...

Page 304: ...Assy Reading Lights 3 off Instrument Panel Flood Light Strip Left Wing Tip Light Assy Landing Taxi Light Assy Instrument Lighting With a rotary button INSTRUMENT in the left hand section of the instru...

Page 305: ...lly kept constant by means of a thermal switch on the Pitot probe and as an additional safety measure a thermal fuse is built in If this thermal fuse is activated the Pitot heating can no longer be sw...

Page 306: ...ubrication system engine OIL TEMP G1000 if installed OT MED if installed Oil pressure lubrication system engine OIL PRES G1000 if installed OP MED if installed Coolant temperature COOLANT TEMP G1000 i...

Page 307: ...splayed on the PFD of the G1000 if installed or White Wire annunciator panel if installed Glow sparks active Status ECU A Status ECU B Low fuel pressure warning on the G1000 if installed The Electrica...

Page 308: ...ith 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 static system 7 12 STALL WARNING SYSTEM If airspeed drops suction...

Page 309: ...IRS 8 3 8 4 GROUND HANDLING ROAD TRANSPORT 8 3 8 4 1 GROUND HANDLING WITHOUT TOW BAR 8 3 8 4 2 GROUND HANDLING WITH TOW BAR 8 4 8 4 3 PARKING 8 6 8 4 4 MOORING 8 9 8 4 5 JACKING 8 9 8 4 6 ALIGNMENT 8...

Page 310: ...be performed every year The respective inspection checklists are prescribed in the Airplane Maintenance Manual Chapter 05 For maintenance work on engine and propeller the currently effective Operator...

Page 311: ...onnel 8 4 GROUND HANDLING ROAD TRANSPORT 8 4 1 GROUND HANDLING WITHOUT TOW BAR During forward traversing the nose wheel will follow the movement of the airplane Change in direction is achieved by pull...

Page 312: ...BAR 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 bent apart and engaged in the appropriate holes in t...

Page 313: ...ved before starting the engine CAUTION The tow bar may only be used for moving the airplane on the ground by hand After moving the airplane the tow bar must be removed NOTE When moving the airplane re...

Page 314: ...s below 38 C 36 4 F make sure that the distilled water coolant mixture ratio is 40 to 60 If the battery heating system O M 40 363 is installed it is recommended to use the system when the airplane is...

Page 315: ...ap straps around stick once 4 Attach the locks and tighten the straps For removal reverse the sequence NOTE It is recommended to cover the canopy when the airplane is parkedoutdoors indirectsunlight a...

Page 316: ...Handling DA 40 NG AFM Page 8 8 Rev 3 01 Jul 2014 Doc 6 01 15 E...

Page 317: ...CKING The airplane can be jacked at the two jackpoints located on the lower side of the fuselage s LH and RH root ribs as well as at the tail fin 8 4 6 ALIGNMENT For alignment push down on the tail se...

Page 318: ...at it cannot be damaged due to fuselage movement during transportation 2 Wings For transportation both wings must be removed from the fuselage To avoid any damage the wings must be stored in an uprigh...

Page 319: ...r alone and if necessary with a mild detergent 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...

Page 320: ...e cleaning is part of the scheduled inspections 8 5 5 INTERIOR SURFACES The interior should be cleaned using a vacuum cleaner All loose items pens bags etc should be removed or properly stored and sec...

Page 321: ...ed de icing fluids are Manufacturer Name Kilfrost TKS 80 Aeroshell Compound 07 Any source AL 5 DTD 406B 1 Remove any snow from the airplane using a soft brush 2 Spray de icing fluid onto ice covered s...

Page 322: ...Handling DA 40 NG AFM Page 8 14 Rev 3 01 Jul 2014 Doc 6 01 15 E Intentionally left blank...

Page 323: ...DA 40 NG AFM Supplements Doc 6 01 15 E Rev 3 01 Jul 2014 Page 9 1 CHAPTER 9 SUPPLEMENTS Page 9 1 INTRODUCTION 9 2 9 2 LIST OF SUPPLEMENTS 9 3...

Page 324: ...upplements 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 Airplan...

Page 325: ...nciator Panel 0 15 Mar 2011 9 9 A13 Autopilot System KAP 140 Bendix King 1 15 Mar 2011 9 9 A29 Garmin Transponder GTX 328 0 15 Mar 2011 9 9 A30 Garmin COM NAV SL 30 0 15 Mar 2011 9 9 A33 Integrated Av...

Page 326: ...No Title Rev No Date applicable YES NO Page 9 4 Rev 3 01 Jul 2014 Doc 6 01 15 E O02 Landing Gear with Large Tyres and 1280 kg Maximum Landing Mass 2 01 Jul 2014 9 9 O03 Cold Weather Operation 1 01 Jul...

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