Diamond Aircraft DA 40 D, Flight Manual

Page 1: ...p Date of approval This Flight Manual has been verified for EASA by the Austrian Civil Aviation Authority Austro Control ACG as Primary Certification Authority PCA in accordance with the valid Certifi...

Page 2: ...DA40 DAFM Diamond T4P AIRCRAFT Introduction Intentionally left blank Page 0 Oa Revision 6 31 Jul 2013 Doe 6 01 05 E...

Page 3: ...ed herein either supplement or in the case of conflict override those in the Airplane Flight Manual or its previous Temporary Revisions The technical information contained in this document has been ap...

Page 4: ...TRANS ORT CANADA Date of approval t Ne _ 2 If 15 November 2017 This temporary revision is prepared to identify that the type design holder for the DA 400 has been transferred to Diamond Aircraft Indus...

Page 5: ...1560 Crumlin Sideroad London Ontario Canada N5V 1S2 http www diamondair com For more information contact Diamond Aircraft Industries Inc Technical Publications 1 519 457 4000 techpubs diamondair com...

Page 6: ...ane Flight Manual until this temporary revision has been incorporated into the Airplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict over...

Page 7: ...rplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual The technical information contained in t...

Page 8: ...nto the Airplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual or its previous Temporary Revi...

Page 9: ...Airplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual The technical information contained in...

Page 10: ...into the Airplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual or its previous Temporary Rev...

Page 11: ...ated into the Airplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual The technical informatio...

Page 12: ...light Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual or its previous Temporary Revisions The technica...

Page 13: ...nto the Airplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual The technical information cont...

Page 14: ...ted into the Airplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual or its previous Temporary...

Page 15: ...e included in the AFM or that AFM revision must be used in which the TR is incorporated The limitations and information contained herein either supplement or in the case of conflict override those in...

Page 16: ...Airplane Flight Manual The limitations and information contained herein either supplement or in the case of conflict override those in the Airplane Flight Manual or its previous Temporary Revisions T...

Page 17: ...complete contents of this Airplane Flight Manual In the event that you have obtained your DIAMOND DA 40 D second hand please let us know your address so that we can supply you with the publications ne...

Page 18: ...ion 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 Equipmen...

Page 19: ...y 2003 OAM 40 130 7 6 1 6 5 6 8 6 9 Winkler for 10 11 12 13 14 ACGI 15 16 17 18 7 1 7 26 7 27 7 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 OAM 40 099 OAM 40 118 0 3thru0 8 1 13 OAM 40 132 1 14...

Page 20: ...1 I 101 122 I 123 e 124 133 137 144 147 151 155 169 174 176 207 210 246 a 253 256 b 336 343 I I i i i rRevision No 51 I i I ii I DAM 40 I of the AFM I I I I Doe No 100 c 124 6 01 05 E is 5 132 a 136 a...

Page 21: ...01 Jun 2008 approved 18 Jul 2008 247 250 a cover page underthe 267 268 authority of DOA No 271 275 EASA 21J 052 277 278 293 294 297 corrections MJIM40 354 356 366 378 399 401 415 428 440 529 Revision...

Page 22: ...nserted Signature No Revision Note Approval Revision No 7 of the AFM MAM 40 701 Doe No 0 Slluu0 16 1 3 6 01 05 E is 7 0 1 3 3 11 thru 3 14 27 Sep 2013 approved 27 Sep 2013 corrections underthe authori...

Page 23: ...013 1 7 31 Jul 2013 0 6 27 Sep 2013 1 8 31 Jul 2013 0 7 27 Sep 2013 1 9 31 Jul 2013 0 8 27 Sep 2013 1 10 31 Jul 2013 0 9 27 Sep 2013 1 11 31 Jul 2013 0 10 27 Sep 2013 1 12 31 Jul 2013 0 11 27 Sep 2013...

Page 24: ...Jui 2013 appr 2 8 31 Jul 2013 appr 2 9 31 Jul 2013 appr 2 10 31 Jul 2013 appr 2 11 31 Jul 2013 appr 2 12 31 Jul 2013 appr 2 13 31 Jul 2013 appr 2 141 3 1 jui 20 13 i appr 2 15 31 Jul 2013 appr 2 16 31...

Page 25: ...31 Jul 2013 3 34 31 Jul 2013 3 7 31 Jul 2013 3 8 31 Jul 2013 3 9 31 Jul 2013 3 10 31 Jul 2013 3 11 27 Sep 2013 3 12 27 Sep 2013 3 13 27 Sep 2013 3 14 27 Sep 2013 3 15 31 Jul 2013 3 16 31 Jul 2013 3 17...

Page 26: ...48 8 31 Jul 2013 4A 12 31 Jul 2013 48 9 31 Jul 2013 4A 13 31 Jul 2013 48 10 31 Jul 2013 4A i4 I 4B i i 3i jui 20 i3 4A 15 48 12 31 Jul 2013 4A 16 31 Jul 2013 48 13 31 Jul 2013 4A 17 31 Jul 2013 48 14...

Page 27: ...2013 6 11 31 Jul 2013 5 12 31 Jul 2013 6 12 31 Jul 2013 5 13 31 Jul 2013 6 13 31 Jul 2013 5 14 31 Jul 2013 6 14 31 Jul 2013 5 15 31 Jul 2013 6 15 31 Jul 2013 5 16 31 Jul 2013 6 16 31 Jul 2013 5 17 31...

Page 28: ...31 Jul 2013 7 39 31 Jul 2013 7 12 31 Jul 2013 7 40 31 Jul 2013 7 13 31 Jul 2013 7 41 31 Jul 2013 7 i4 i 3i Jui 20i3 i 7 42 3 1 ju 20 13 7 151 31 Jul 20131 7 43 31 Jul 2013 7 16 31 Jul 2013 7 44 31 Jul...

Page 29: ...31 Jul 2013 9 2 31 Jul 2013 8 3 31 Jul 2013 9 3 31 Jul 2013 8 4 31 Jul 2013 9 4 31 Jul 2013 8 5 31 Jul 2013 9 5 31 Jul 2013 8 6 31 Jul 2013 9 6 31 Jul 2013 8 7 31 Jul 2013 8 8 31 Jul 2013 8 9 31 Jul...

Page 30: ...Introduction Diamond w AIRCRAFT DA40 DAFM inieni1onaiiy iefi biank Page 0 14 Revision 7 27 Sep 2013 Doe 6 01 05 E...

Page 31: ...MAL OPERATING PROCEDURES a non approved chapter 4A ABNORMAL OPERATING PROCEDURES a non approved chapter 4B PERFORMANCE a non approved chapter 5 MASS AND BALANCE I EQUIPMENT LIST a non approved chapter...

Page 32: ...Introduction 9Diamond AIRCRAFT DA40 DAFM intentionaiiy ieft biank Page 0 16 Revision 7 27 Sep 2013 Doe 6 01 05 E...

Page 33: ...ES 1 5 1 4 DIMENSIONS 1 6 1 5 DEFINITIONS AND ABBREVIATIONS 1 8 1 6 UNITS OF MEASUREMENT 1 17 1 6 1 CONVERSION FACTORS 1 17 1 6 2 CONVERSION CHART LITERS I US GALLONS 1 19 1 7 THREE VIEW DRAWING 1 20...

Page 34: ...ails of the airplane may vary from serial number to serial number Therefore some of the information contained in this manual is applicable depending on the respective equipment and modification level...

Page 35: ...1 1 INTRODUCTION The following entry must be added to the Modification List Modification Firmware m2 32 for 19 1 engine Doe No 6 01 05 E TR RAM 40 056 Source RAM 40 056 10 Jan 2006 Temporary Revision...

Page 36: ...DA40 DAFM ADiamond AIRCRAFT 1 1 INTRODUCTION Die following is added to the Modifaction List Concorde RG 35AXC Doe 6 01 05 E TR OAM 40 384 02 Sep 2014 Temporary Revision RG 35AXC Main Battery Page 1 3a...

Page 37: ...RODUCTION The following is added to the Modification List Modification Emergency Egress Hammer I Doe No 6 01 05 E TR OAM 40 401 Source OAM 40 401 06 Dec 2016 Temporary Revision Emergency Egress Hammer...

Page 38: ...s___ t _no l o f AED CED in Combination with TAE 125 02 99 Engine Muffler Long Range Tank Winter Baffle Fresh Air Inlet Nose Landing Gear Tie down ELT Artex ME 406 Autopilot Static Source Garmin G100...

Page 39: ...n engine failure is not completely impossible For this reason flights during the night on top under instrument meteorological conditions IMC or above terrain which is unsuitable for a landing constitu...

Page 40: ...RNING 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 procedur...

Page 41: ...incidence Page 1 6 Revision 6 Diamond T w AIRCRAFT appr 11 94 m appr 8 06 m appr 1 97 m appr 39 ft 2 in appr 26 ft 5 in appr 6ft 6 in Wortmann FX 63 137 20 W4 appr 13 54 m2 appr 145 7 sq ft appr 1 121...

Page 42: ...m2 appr 0 47 m2 appr 2 97 m appr 17 2 sq ft appr 5 1 sq ft appr 9ft 9 in appr 1 68 m appr 5 ft 6 in 5 00 5 6 PR 120 mph a 6 00 6 6 PR 120 mph b 6 00 6 8 PR 120 mph General c 15x6 0 6 6 PR 160 mph OAM...

Page 43: ...r TAS is CAS corrected for errors due to altitude and temperature vA Maneuvering Speed Full or abrupt control surface movement is not permissible above this speed vc Design Cruising Speed This speed m...

Page 44: ...n sea level is 15 oc 59 oF 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 oc 69 7 F is 0 0065 C m 0 00357 F ft and abo...

Page 45: ...nt errors are regarded as zero The wind speeds which are shown as variables in the diagrams in this manual should be regarded as headwind ortailwind components ofthe measured wind c Flight Performance...

Page 46: ...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 unusable fuel all...

Page 47: ...it FADEC Full Authority Digital Engine Control GT Gearbox Ternperaiure LOAD Engine output power in percent of max continuous power OP Oil Pressure oil pressure in the lubrication system of the engine...

Page 48: ...Panel INST 1 Engine Instrument PITOT Pitot Heating System LANDING Landing Light FLOOD Flood Light ESS TIE Bus Interconnection MASTER CONTROL MasterControl Avionics Main Switch Bus Connection Avionics...

Page 49: ...P Fuel Transfer Pump AV BUS Avionics Bus 2 HORIZON 2nd Artificial Horizon 2nd Attitude Gyro MAIN AV BUS MAIN AVIONIC BUS GPS NAV2 Global Positioning System and NAV Receiver No 2 COM2 COM Radio No 2 AU...

Page 50: ...System and NAV Receiver No 1 XPDR Transponder ECUBUS ECU ALT ECU Alternate power relay ECUA ECUA ECU B ECU B g Equipment ELT Emergency Locator Transmitter h Design Change Advisories MAM Mandatory Des...

Page 51: ...Federal Office of Civil Aviation ATC Air Traffic Control CFRP Carbon Fiber Reinforced Plastic GFRP Glass Fiber Reinforced Plastic JAR Joint Aviation Requirements JC VP Joint Certification Validation P...

Page 52: ...rs kts knots kmlh I 1 852 kts per hour mph miles per kmlh I 1 609 mph mls meters per hour mls x 196 85 fpm second fpm feet per minute Speed of RPM revolutions per minute rotation Mass kg kilograms lb...

Page 53: ...DAFM Dimension SI Units IUS Units Conversion Intensity of A amperes electric current Electric Ah ampere hours charge battery r n rit 1 J I Electric M volts potential Time sec seconds Page 1 18 Revisi...

Page 54: ...2 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 28 106 0 110 29 1 30 113 6 120...

Page 55: ...Io 4fADiamond AIRCRAFT 1 7 THREE VIEW DRAWING m I I Revision 6 31 Jul 2013 DA4 l DAFM I Doe 6 01 05 E...

Page 56: ...nly the information given in the Airplane Flight Manual is valid 1 8 1 ENGINE AND ENGINE INSTRUMENTS Address Phone Fax Internet Documents Thielert Aircraft Engines GmbH Platanenstrasse 14 D 09350 LICH...

Page 57: ...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 Hydraulically controlled variable pitch propeller...

Page 58: ...2 14 2 9 APPROVED MANEUVERS 2 15 2 10 MANEUVERING LOAD FACTORS 2 17 2 11 OPERATING ALTITUDE 2 18 2 12 FLIGHT CREW 2 18 2 13 KINDS OF OPERATION 2 19 2 14 FUEL 2 23 2 15 LIMITATION PLACARDS 2 25 2 16 O...

Page 59: ...rument markings and placards necessary for the safe operation ofthe airplane its power plant standard systems and standard equipment The limitations included in this Chapter are approved Page 2 2 WARN...

Page 60: ...ke full or abrupt above 980 kg 2161 lb control surface movement up to 1150 kg 2535 lb above this speed 94 KIAS above 780 kg 1720 lb up to 980 kg I 2161 lb LOG 91 KIAS Do not exceed these speeds T 0 10...

Page 61: ...Green arc Yellow arc Red line Page 2 4 IAS Significance 49 KIAS 91 KIAS Operating range with flaps fully extended 52 KIAS 129 KIAS Normal operating range 129 KIAS 178 KIAS Caution range Only in smoot...

Page 62: ...ried out Maximum Maximum overspeed d Engine power Max take off power Max continuous power 2500 RPM 2300 RPM 2500 RPM max 20 sec 99 kW 135 DIN hp at 2300 RPM 99 kW 135 DIN hp at 2300 RPM e Oil pressure...

Page 63: ...TAE 125 02 99 TAE 125 01 MAM40 256 carried out 32 oc 32 oc 140 oc I 140 oc 120 oc TAE 125 02 99 TAE 125 01 MAM40 256 carried out 105 oc 105 oc mt Propeller MTV 6 A 187 129 187 cm 6ft 2 in m Propeller...

Page 64: ...m switch assy ELECTRICAL POWER voltage Converter jEmergency Battery 26 pes ECU BackupBatterytester Doe No 6 01 05 E Type DMC63 2 ciNs43o GMA 340 KAP 146 KC 140 KC 140 KC146 KC 140 KS270C KM275 KS 271...

Page 65: ...propeller gearbox SHELL EP 75W90 API GL 4 SHELL SPIRAX GSX 75W 80 GL 4 SHELL SPIRAX S4 G 75W 90 SHELL SPIRAX S6 GXME 75W 80 API GL 4 Additionally if MAM 40 256 is incorporated CENTURION Gearbox Oil N1...

Page 66: ...e TAE Operation Manual may cause engine damage CAUTION Ifthe coolant level is low the reason must be determined and the problem must be corrected by authorized personnel p Gearbox oil propeller gearbo...

Page 67: ...0 to 2500 above RPM RPM 2500 RPM Oil below 1 2 to 2 3 bar 2 3 to 5 2 bar 5 2 to 6 5 bar above pressure 1 2 bar 6 5 bar f l ht Jr H h i I I 32 to 50 vc i 50 to 125 vc I 125 to 140 vc temp 32 c 140 c Co...

Page 68: ...0 oc 50 to 125 oc 125 to 140 oc above temp 32 oc 140 oc Coolant below 32 to 60 oc 60 to 96 oc 96 to 105 oc above temp 32 oc 105 oc Gearbox up to 115 oc 115to120oC above temp 120 oc Load 0 100 Fuel bel...

Page 69: ...description of the lights on the annunciator panel Color and Significance of the Warning Lights Red Warning Liaht CRed WARNING START DOOR TRIM FAIL ECU BACKUP UNSAFE Page 2 10 Meaning Cause Warning m...

Page 70: ...on 6 Cause On board voltage below 12 6 V 0 2V Generator failure Pitot heating OFF or failure MAIN tank fuel low Engine limit exceeded A fault has occurred in the ECU A one reset of minor faults is pos...

Page 71: ...ance of the Status Lights White Status Light White FUEL TRANS ll jLUVV Page 2 12 Meaning Cause Transfer pump Transfer pump active I fuel transfer from the AUX tank to the MAIN tank I I ll jiOW p1ugs 1...

Page 72: ...1092 kg 30 kg WARNING if MAM 40 123 is installed 2407 lb otherwise 661b Exceeding the mass limits will lead to an overstressing ofthe airplane as well as to a degradation of flight characteristics and...

Page 73: ...ertical The Datum Plane is located 2 194 meters 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 position for flight c...

Page 74: ...mal Category 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 75: ...ned CAUTION Aerobatics spinning and flight maneuvers with more than 90 of bank are not permitted in the Utility Category CAUTION The accuracy of the attitude gyro artificial horizon and the directiona...

Page 76: ...ural load factors Normal Category atvA atvNe Positive 3 8 3 8 Negative 1 52 0 Utility Categorv at VA atvNe Positive 4 4 4 4 Negative 1 76 1 0 Temporary Revision G Load Factor Correction with flaps in...

Page 77: ...negative g loads duration Extended negative g loads can cause propeller control problems and engine surging Table of maximum structural load factors Normal Category Operating Limitations at VA at VNE...

Page 78: ...emonstrated operating altitude is 16400 ft 5000 m pressure altitude 2 12 FLIGHT CREW Minimum crew 1 one person MFlximum numhF r of or r urmnts Normal Category 4 four persons Utility Category 2 two per...

Page 79: ...conditions are prohibited Flights into known thunderstorms are prohibited Minimum Operational Equipment Serviceable Operating Limitations The following table lists the minimum serviceable equipment re...

Page 80: ...indicator VSI Attitude gyro artificial horizon I Turn bank indicator Directional gyro 01 T indicator Chronometer with indication of hours minutes and seconds VHF radio COM VOR receiver Transponder XP...

Page 81: ...perature Gear box temperature Load Propeller RPM Fuel temperature left right tank Engine caution light on White Wire Lighting Doe 6 01 05 E Revision 6 Ammeter Voltmeter Position lights Strobe lights a...

Page 82: ...V AFM Safety belts for each occupied seat Airplane flight manual In addition for night VFR flights Pitot heating system Alternate static valve NOTE DA40 DAFM In addition for IFR flights Emergency batt...

Page 83: ...d to read JET Fuel JET A 1 ASTM D 1655 JET A ASTM D 1655 JP 8 MIL DTL 83133 JET Fuel No 3 China GB 6537 2006 Additionally if MAM 40 256 is incorporated Doe 6 01 05 E TS 1 GOST 10227 86 TS 1 Ukraine GS...

Page 84: ...above listed Jet Fuel grades see CAUTIONS below CAUTION Additional temperature limitations must be observed if the airplane is operated with Diesel Fuel or blends of Diesel Fuel with JET Fuel CAUTION...

Page 85: ...e between right and left tank CAUTION 2 x 20 5 US gal 2 x 77 6 liters 2 x 19 5 US gal 2 x 73 8 liters 15 US gal 56 81iters per tank 9 US gal approx 34 liters If an indicator shows 15 US gal then 19 5...

Page 86: ...appropriate equipment is installed this airplane is approved for the following kinds of operation day VFR night VFR and IFR All aerobatic maneuvers including spinning are prohibited For further opera...

Page 87: ...tity Indication Long Range Tank max usable fuel 2 x 19 5 US gal Max indicated fuel quantity 2 x 15 US gal Refer to AFM to use entire tank capacity Max difference LH RH tank 9 US gal On the Conventiona...

Page 88: ...the Two Fuel Filler Necks Operating Limitations WARNING APPROVED FUEL JET A 1 or see Airplane Flight Manual On Airplanes with early serial numbers the placard may include Diesel EN590 Doe 6 01 05 E R...

Page 89: ...0 DAFM Ess Bus NOT for normal operation See AFM In the Co Niing on the Door for the 0 Fi er Neck OIL Shell Helix Ultra SW 30 or see Airplane Flight Manual Jext to the Flan Selector S vitch max 108 KIA...

Page 90: ...ER CAUTION Intermittent use only see AFM Q 0 OFF In the Cockpit on the Left Fuselage Sidewall Doe 6 01 05 E Alternate Static OPEN tab CLOSED If Alternate Static 11 open Emergency Wind and Cockpit Vant...

Page 91: ...ions MADiamond V AIRCRAFT Next to the Baggage Compartment Beside the Door Locking Device Page 2 30 EMERGENCY EXiT Revision 6 The keylock must be unlocked during flight 31 Jul 2013 EASA approved DA40 D...

Page 92: ...r to operation is mandatory 2 16 2 FUEL TEMPERATURE JET Fuel grades and blends thereof TAE 125 01 engine TAE 125 02 99 engine MAM 40 256 carried out from 30 oc to 65 oc from 22 oF to 149 oF from 30 oc...

Page 93: ...s of equipment are Mobile telephones Remote radio controls Video screens employing CRTs iv1inidisc recorders vvhen in the record mode This list is not exhaustive The use of laptop computers including...

Page 94: ...an insufficient backup battery charge IFR flights are not permitted 2 16 8 USE OF THE SUN VISORS The sun visors if installed OAM 40 327 may only be used during cruise During all other phases of fligh...

Page 95: ...Operating Limitations Page 2 34 Revision 6 Diamond AIRCRAFT Intentionally left blank 31 Jul 2013 EASA approved DA40 DAFM Doe 6 01 05 E...

Page 96: ...0 0 0 0 0 0 0 0 0 3 11 3 2 5 RESTARTING THE ENGINE WITH STATIONARY PROPELLER 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 3 13 3 2 6 DEFECTIVE RPM REG...

Page 97: ...S 3 30 3 7 1 ICING 3 30 3 7 2 FAILURES IN THE ELECTRICAL SYSTEM 3 31 3 7 3 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE Page 3 2 CABIN 3 33 3 7 4 DOOR VVARN NG L GHT ON 3 34 NOTE Procedures for u...

Page 98: ...h understanding of the airplane by the pilot is in addition to his knowledge and experience an essential factor in the solution ofany problems which may arise WARNING In each emergency control over th...

Page 99: ...e after take off 59 KIAS 66 KIAS l l mc Tin 1 _ Airspeed for best glide angle 60 KIAS 68 KIAS Flaps UP Emergency Flaps UP 60 KIAS 68 KIAS landing with Flaps T 0 59 KIAS 66 KIAS engine off Flaps LDG i...

Page 100: ...stration Hf Type PartNo iManu acturer Temporary Revision SIN 40 080 Date ze to Js Jsm In stalled 1394T100 12RZ _ 4000C 1l j1U262 042 3 1 Mid Continantlnstr 1_ Sigmalek Cl102 KN62A KA60 Clti25 GNS 430...

Page 101: ...e must be shut down Otherwise the cause of the problem must be established in order to re establish engine performance CAUTION lfthe oil pressure is in the red range the engine must be shut down immed...

Page 102: ...unway Length Available Land straight ahead 1 Power lever IDLE On the ground 2 Brakes as required CAUTION If sufficient lime is remaining the risk of fire in the event of a collision can be reduced as...

Page 103: ...has not been reached then a straight ahead emergency landing should be carried out Do not attempt to turn back to the airfield Turning back can be fatal If time allows 2 Power lever 3 ECU SWAP WARNIN...

Page 104: ...heck NOTE If the caution light is on the engine instruments must be checked Proceed in accordance with 48 2 INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE 4 If in icing conditions Alternate Air ON 5 Fu...

Page 105: ...ANDING WITH ENGINE OFF END OF CHECKLIST lb Loss of Power NOTE As long as an airspeed ofatleast60 KIAS is maintained and there is no majormechanical engine defect the propellerwill continue to windmill...

Page 106: ...UTOMATIC WARNING If the problem does not clear itself immediately prepare for an emergency landing in accordance with 3 5 1 EMERGENCY LANDING WITH ENGINE OFF then try to restart the engine with windmi...

Page 107: ...propeller overspeed NOTE Restarting the engine with windmilling propeller is possible at airspeeds between 73 and 110 KIAS and altitudes below 6500 ft TAE 125 01 engine or 6000 ft TAE 125 01 R5 engin...

Page 108: ...IDING Carry out emergency landing in accordance with DA40 DAFM 3 5 1 EMERGENCY LANDING WITH ENGINE OFF CAUTION Engine restart following an engine fire should only be attempted if it is un ike y that a...

Page 109: ...6500 ft TAE 125 01 engine or 6000 ft TAE 125 01 R5 engine or 8000 ft TAE 125 02 99 engine pressure altitude Emergency Procedures 1 Airspeed for best glide angle 73 KIAS 1150 kg 25351b 68 KIAS 1000 kg...

Page 110: ...the CLCCTRIC MAGTCR should be set to ON see 3 2 4 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER A loss of altitude of at least 1000 ft 300 meters must be expected If it is not possible to start the...

Page 111: ...peller blades produce more rapid RPM changes than metal blades WARNING lt is possible that the propeller blades remain in the position of highest pitch in case of a malfunction ofthe engine control un...

Page 112: ...tch propeller RPM is controlled by lhe engine power setting Flight to the nearest airfield can be continued with a lower power setting and at a lower airspeed Climb and go around remain possible 1 Pow...

Page 113: ...Power lever as required do not exceed 2300 RPM I I I I I I I I NOTE If situation requires increased engine power a maximum of 2500 RPM is permissible for a maximum of 10 minutes Set the power lever to...

Page 114: ...at the high pitch stop 1 Power lever I CU VVAI NOTE as required ECU B If selecting ECU B does not solve the problem switch back to AUTOMATIC WARNING Due to this problem the propeller RPM will drop to...

Page 115: ...ck to NORMAL before the auxiliary tank indication 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 emergenc...

Page 116: ...MASTER OFF 11 ELECTRIC MASTER OFF After standstill 5 Canopy open DA40 D AFM 6 Airplane evacuate immediately END OF CHECKL ST b Electrical Fire with Smoke on the Ground 1 ELECTRIC MASTER OFF If the eng...

Page 117: ...1 Cabin heat OFF 2 If possible fly along a short cut traffic circuit and land on the airfield WARNING If in the event ofan engine problem occurring during take off the take off can no longer be aborte...

Page 118: ...ut emergency landing with engine off Allow for increased landing distance due to the flap position CAUTION In case of extreme smoke development the front canopy may be unlatched during flight This all...

Page 119: ...anding area When it seems certain that the landing area will be reached 3 Emergency fuel valve OFF 4 Power lever MAX 5 Emergency windows open if required 6 Carry out emergency landing with engine off...

Page 120: ...is are the attitude gyro artificial horizon and the directional gyro if installed However by switching the EMERGENCY switch ON the emergency battery will supply power to the attitude gyro artificial h...

Page 121: ...oss the maximum horizontal distance traveled in still air is 1 45 NM 2 68 km During this the propellerwill continue to windmill With a stationary propeller the glide ratio is 10 3 this corresponds to...

Page 122: ...t I he degree ot ottset at each part ot the c1rcu1t will allow the wind speed and direction to be assessed 4 Airspeed 73 KIAS 1150 kg 2535 lb 68 KIAS 1000 kg 22051b 60 KIAS 850 kg 1874 lb 5 Radio advi...

Page 123: ...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 corrected on the runway 3 Land wit...

Page 124: ...n order to reduce the landing run due to the greater rolling resistance CAUTION if sufficient time is remaining the risk of fire in the event of a collision can be reduced as follows after a safe touc...

Page 125: ...Rudder full deflection against direction of spin 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...

Page 126: ...itot heating ON 3 Cabin heat ON 4 Air distributor lever DEFROST 5 Power lever 6 Alternate air increase power in order to prevent ice build up on the propeller blades OPEN 7 Emergency windows open if r...

Page 127: ...ositions and engine noise 6 Prepare landing with flaps in the given position Refer to 48 6 FAILURES IN FLAP OPERATING SYSTEM 7 Land on the nearest appropriate airfield END OF CHECKLIST b Starter Malfu...

Page 128: ...age Diamond AIRCRAFT DA40 DAFM If a voltage in the red range above 15 5 V or below 11 V is indicated 1 Essential bus ON 2 Land on the nearest appropriate airfield END OF CHECKLIST Page 3 32 Revision 6...

Page 129: ...ases is noticed in the cabin the following measures should be taken 1 Cabin heat OFF 2 Ventilation open 3 Emergency windows open 4 Airspeed reduce below 120 KIAS 5 Forward canopy unlatch push up and l...

Page 130: ...he next suitable airfield I Rear Door Unlocked 4 Airspeed below 140 KIAS 5 Land at the next suitable airfield Do not try to lock the rear door in flight The safety latch may disengage and the door ope...

Page 131: ...3 3 STARTING ENGINE 4A 13 4A 3 4 BEFORE TAXIING 4A 15 4A 3 5 TAXIING 4A 16 4A 3 6 BEFORE TAKE OFF 4A 17 4A 3 7 TAKE OFF 4A 21 4A 3 8 CLIMB 4A 22 4A 3 9 CRUISE 4A 24 4A 3 10 FUEL TRANSFER 4A 25 4A 3 11...

Page 132: ...1000 kg 1150 kg 18741b 22051b 25351b Airspeed for rotation Take off run vR 49 KIAS 55 KIAS 59 KIAS Flaps T 0 Airspeed for take off climb best rate of climb speed vv 54 KIAS 60 KIAS 66 KIAS Flaps T 0...

Page 133: ...aged check locking mechanism function h All electrical equipment OFF i Circuit breakers set in if one has been pulled check reason j Power lever check condition freedom of move ment and full travel k...

Page 134: ...Visual Inspection CONTINUED CAUTION A visual inspection means examination for damage cracks delamination excessive play load transmission correct attachment and general condition ln addition control...

Page 135: ...4A 3 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4A 3 1 PRE FLIGHT INSPECTION I Cabin Check The following is added to the Checklist t Emergency Egress Hammer if OAM 40 401 installed stowed and secured...

Page 136: ...DA40 DAFM 7 4 INSTRUMENT PAti tl Diamond AIRCRAFT j Temporary Revision S N 40 080 Instrument Panel Version 040 3123 00 00 Doe No 6 01 05 E TR RAM 40 026 06 Jun 2003 Page 4 of6...

Page 137: ...spection c Air intake on lower surface visual inspection d Openings on lower surface check for foreign objects and for traces offuel iftank is full fuel may spill over through the tank vent e Tank dra...

Page 138: ...ction 3 Fuselage left side a Canopy left side visual inspection b Rear cabin door window visual inspection c Fuselage skin visual inspection d Antennas visual inspection e Autopilot static source if i...

Page 139: ...oreign objects in aileron paddle visual inspection f Wing tip visual inspection g Position light strobe light ACL visual inspection h Tie down check clear i Entire wing surface visual inspection j 2 s...

Page 140: ...5 bar 36 psi check d Wear tread depth of tires check e Tire wheel brake visual inspection f Brake line connection check for leaks g Slip marks visual inspection h Chocks remove 8 Front fuselage a Engi...

Page 141: ...rail Serious personal injury may result f Spinner including attachment screws visual inspection g Nose landing gear strut visual inspection h Gear strut fairing if installed visual inspection i Winter...

Page 142: ...on DA40 DAFM s Gascolator drain off to check for water and sediment drain until no water comes out t Venting pipes check for blockage u Fuseiage underside check for excessive contamination particularl...

Page 143: ...canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force NOTE A slight downward pressure on the canopy may be required to ease the ha...

Page 144: ...23 F on a conventional instrument panel or is below 5 oc 23 oF on a G1000 instrument panel Operation with a flashing fuel temperature indication on a conventional instrument panel below 5 oc 23 OF or...

Page 145: ...4 of the checklist is amended to read 4 ELECTRIC MASTER START I release when propeller speed has reached 500 RPM The CAUTION is added after the second WARNING CAUTION lfthe TAE 125 02 99 engine with d...

Page 146: ...RES 4A 3 3 STARTING ENGINE The CAUTION is added CAUTION Before starting the engine and until the engine is shut down the canopy must be closed and latched in position 1 or 2 cooling gap and the door m...

Page 147: ...not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool off for half an hour 4...

Page 148: ...T AIRCRAFT DA40 DAFM IDLE for 2 minutes 1400 RPM until oil temperature and coolant temperature are in the green range 8 Annunciator panel I engine instruments check 9 Acknowledge button press END OF...

Page 149: ...s required 6 Pitot heating ON test function 7 Pilot heating OFF 8 Strobe lights ACLs check ON 9 Position lights landing and taxi lights ON test function as required CAUTION When taxiing at close range...

Page 150: ...bank indicator CAUTION check for correct indications When taxiing on a poor surface select the lowest possible RPM to avoid damage to the propeller from stones or similar items CAUTION Avoid prolonge...

Page 151: ...s between the canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward pressure on the canopy may be required to eas...

Page 152: ...fuel grade is unknown a safe fuel transfer is not ensured until the fuel temperature indication of both fuel tanks is in the green range minimum 5 oc I 41 F 8 Circuit breakers check pressed in 9 Flaps...

Page 153: ...ion lights ECU A CAUTION blinking 23 Propeller RPM cycling 24 Caution lights extinguished 25 ECU BACKUP UNSAFE Iight extinguished CONTINUED WARNING Ifthe ECU BACKUP UNSAFE Iightdoes not extinguish aft...

Page 154: ...n even when the engine seems to run smoothly after the test procedure 27 ECU SWAP ECU B 28 Engine check running without a change 29 ECU SWAP AUTOMATIC NOTE When switching from one ECU to the other a s...

Page 155: ...sary 3 Elevator neutral 4 Rudder maintain direction NOTE In strong crosswinds steering can be augmented by use of the toe brakes lt should be noted however that this method increases the take off roll...

Page 156: ...KIAS 850 kg I 18741b 54 KIAS The engine temperatures must be observed then 3 Power lever MAX 4 Engine instruments in green range 5 Trim as required CAUTION fthe oil temperature and or coolant temperat...

Page 157: ...2535 lb NOTE With lower mass the air speeds can be reduced as given below 1000 kg I 2205 lb 68 KIAS 850 kg 18741b 60 KIAS The engine temperatures must be observed then 3 Power lever MAX 4 Engine inst...

Page 158: ...ransfer repeat as required in accordance with 4A 3 10 FUEL TRANSFER NOTE The engine manufacturer recommends acruise power setting of70 NOTE Proper operation of the transfer pump must be checked by mon...

Page 159: ...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 pumping each time the fuel level in the...

Page 160: ...t less than 30 CAUTION Engine combustion may stop unrecognized during descents with idle power at altitudes above 5000 ft with outside air temperatures below 10 c 2 Power lever clear engine occasional...

Page 161: ...71 KIAS 1150 kg 25351b 67 KIAS 1092 kg 24071b 63 KIAS 1000 kg 22051b 58 KIAS 850 kg 1874 lb NOTE In caseofairplaneswith a maximum landing massof1092 kg 2407 lb a landing with a higher mass constitute...

Page 162: ...0 KIAS 1000 kg 22051b 54 KIAS 850 kg 18741b 3 Flaps T 0 Above a safe height 4 Airspeed 73 KIAS 5 Flaps UP END OF CHECKLIST 1 Power lever IDLE 2 Brakes as required 3 Transponder OFF I STBY 4 Pitot heat...

Page 163: ...hut down the engine must run for at least 2 minutes with the power lever at IDLE to avoid heat damage ofthe turbo charger END OF CHECKLIST 4A 3 16 POST FLIGHT INSPECTION 1 ENGINE MASTER OFF 2 ELECTRIC...

Page 164: ...d Grounding points unpainted areas on steps left and right NOTE If the airplane is operated with Diesel Fuel additional temperature limitations must be observed if JET Fuel is used make sure that no D...

Page 165: ...NNUNCIATOR PANEL 4B 10 4B 3 1 LOW VOLTAGE CAUTION LOW VOLTS 4B 10 4B 3 2 ECU A FAILURE ECU A 4B 11 4B 3 3 ECU B FAILURE ECU B 4B 12 4B 3 4 ALTERNATOR FAILURE ALTERNATOR 4B 13 4B 3 5 ENGINE FAILURE ENG...

Page 166: ...in a field represents a lower risk than the attempt to reach the target airfield under all circumstances NOTE If no level landing area is available a landing on an upward slope should be sought 1 Sel...

Page 167: ...0 kg 1874 lb 8 Safety harnesses tighten 9 Touchdown with the lowest possible airspeed CAUTION If sufficient time is remaining the risk of fire in the event of a collision with obstacles can be reduced...

Page 168: ...he green range using ihe power iever NOTE An RPM in the yellow range is permissible for a short time if required e g for go around CAUTION If the available power is too low to continue a safe flight p...

Page 169: ...s not reach the green range within 60 seconds reduce power as far as possible and increase airspeed During cruise Reduce power Increase airspeed Check coolant temperature in green range CAUTION Ifthe...

Page 170: ...Iemperature Check coolant qty caution light WATER LEVEL NOTE During an extended descent from high altitudes with a low power setting coolant temperature may decrease If on Reduce power Expect loss of...

Page 171: ...oil with engine failure Prepare for an emergency landing in accordance with 3 5 1 EMERGENCY LANDING WITH ENGINE OFF If the oil pressure is within the green range Reduce power Increase airspeed monitor...

Page 172: ...nce with 3 5 1 EMERGENCY LANDING WITH ENGINE OFF CAUTION When starting a cold engine the oil pressure can be as high as 6 5 bar for a rnaxirnurn of 20 seconds END OF CHECKLIST Low Oil Pressure NOTE If...

Page 173: ...rmal Operating Procedures Increased fuel temperature can occurwhen the fuel quantity in the main tank is low The fuel temperature can be decreased by transferring fuel from the auxiliary to the main t...

Page 174: ...supply RPM too low la Low Voltage Caution on the Ground 1 Circuit breakers check 2 Power lever increase RPM 3 if the caution light does not go out terminate flight preparation lb Low Voltage Caution...

Page 175: ...Control Unit A the system automatically switches to ECU B 1 Press the ECU TEST button for more than 2 seconds to reset the caution message If the ECU A caution re appears or cannot be reset 2 Land on...

Page 176: ...1 Press the ECU TEST button for more than 2 seconds to reset the caution message If the ECU B caution re appears or cannot be reset 2 Land on nearest suitable airfield 3 Tl1e engine must be serviced...

Page 177: ...NG The ECU which is absolutely necessary for engine operation needs electrical power lt is recommended to switch off all electrical consumers and to land as soon as possible Be prepared for an engine...

Page 178: ...25 or AED 125 is near the end of the green range it may happen that it switches over to the yellow or red range for a short time This will also cause the ENGINE caution light to illuminate NOTE Ifan i...

Page 179: ...ing on the ground can also cause the Pitot heating caution message to be displayed In this case it indicates the activation of the thermal switch which prevents overheating of the Pitot heating system...

Page 180: ...t The caution message may be triggered during turns which are flown with slip or while taxiing in curves If the caution light does not extinguish Expect loss of fuel Be prepared for an emergency landi...

Page 181: ...CAUTION GENERATOR This caution 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 necessary and...

Page 182: ...3 Follow procedure in 48 3 4 ALTERNATOR FAILURE ALTERNATOR END OF CHECKLIST High Voltage Land on the nearest suitable airfield NOTE The ENGINE caution light on a conventional instrumentpanel can illum...

Page 183: ...however that this method increases the take off roll and should not generally be used 7 Elevator control stick Release slowly after nose wheel has lifted Allow airplane to lift off as soon as possibl...

Page 184: ...a Only UP available Airspeed 73 KIAS 1150 kg 2535 lb 68 KIAS 1000 kg 22051b 60 KIAS 850 kg 18741b Land at a fiat approach angle use povver lever to controi aii piane speed and fate of descent b Only T...

Page 185: ...12 NOTE The maximum landing mass given in Chapter 2 is the highest mass for landing conditions at the maximum descent velocity This velocity was used in the strength calculations to determine the lan...

Page 186: ...Abnormal Operating Procedures Page 48 22 Revision 6 Diamond T W AIRCRAFT DA40 DAFM Intentionally left blank 31 Jul 2013 Doe 6 01 05 E...

Page 187: ...Y ALTITUDE 5 5 5 3 4 INTERNATIONAL STANDARD ATMOSPHERE 5 6 5 3 5 STALLING SPEEDS 5 7 5 3 6 WIND COMPONENTS 5 8 5 3 7 TAKE OFF DISTANCE 5 9 5 3 8 CLIMB PERFORMANCE TAKE OFF CLIMB 5 13 5 3 9 CLIMB PERFO...

Page 188: ...ntained airplane The performances given can be attained it the procedures quoted in this manual are applied and the airplane has been well maintained Where appropriate any flight performance degradati...

Page 189: ...RAMS 5 3 1 AIRSPEED CALIBRATION 180 170 160 150 140 130 t120 r J 110 100 90 80 70 60 50 40 X Flaps UP X Flaps T 0 o Flaps LDG r 7 f V Performance v v V V f 40 50 60 70 80 90 100 110 120 130 140 150 16...

Page 190: ...l 00 I I I I I r L __J L 1 I I I I I I I I I I I I I I I 1 I I I J L l 1 1 I I I I I I 1 I j I i j I I I I I ___ _ _ _ t i I I I I I I I I I I I t I I I I I I I I I I I I I I I I I 1 I 1 r r r 5 I I...

Page 191: ...ctional gyro 10 Accessory power socket 30 Autopilot control unit 11 Alternate static valve 31 Emergency switch 12 Ventilation nozzles 32 Slaving meter 13 Chronometer with OAT indicator 33 Horizontal s...

Page 192: ...2500 800 12000 3500 2000 10000 3000 600 1500 8000 2500 400 2000 1000 6000 1500 200 4000 500 1000 0 2000 500 500 200 0 0 20 10 0 10 20 30 C 4 14 32 50 68 86 F temperature Example 1 Set 1 013 25 hPa on...

Page 193: ...000 8000 0 17l 7000 ffi 6000 0 a 5000 4000 3000 2000 1000 0 _ _ 1 _ I A 3_0 C ISA 20 C v ISA 10 C 8A ISA 10 C tr ___ r 1 ISA 2 C J I I I f I i r r EXAMPLE 11 OUTSIDEAIRTEMPER TURE 19 C K REALTITU_DE 8...

Page 194: ...2161 lb Airspeeds in KIAS Bank Angle 980kg o 30 45 so UP 47 52 58 73 Flaps T 0 44 51 58 72 LOG 42 49 57 71 Mass 1150 kg 2535 lb Airspeeds in KIAS Bank Angle 1150 kg o 30 45 so UP 52 57 66 79 Flaps T 0...

Page 195: ...c Qj c g_1 E 0 LJ o 32 30 40 60 70 80 90 o 1J Qj I Example Flight direction Wind 120 I I 10 30 Crosswind Component lkts 360 32 30 kts Result Crosswind component 16 kts Max demonstrated crosswind compo...

Page 196: ...n procedures as well as unfavorable outside conditions high temperature rain unfavorable wind conditions including cross wind will increase the take off distance CAUTION For a safe take off the availa...

Page 197: ...bove Grass up to 5 cm 2 in long 10 increase in take off roll Grass 5 to 10 cm 2 to 4 in long 15 increase in take off roll Grass longer than 10 cm 4 in at ieast 25 increase in take off roll NOTE An uph...

Page 198: ...1 hf a 9 gL I I iS 0 0 0 m rJ OUTSIDE AIR TEMPERATURE C T 0 MASS kg MND COMPONENT mls 0 2 4 6 8 10 I I I I I I 850 800 750 700 650 600 550 500 450 400 350 300 250 200 150 100 I I I I I I I I I I MND C...

Page 199: ...0 5 0 5 10 20 25 30 35 40 45 OUTSIDE AIR TEMPERAT IRE fC T OMASS b VVlND c JMPONENT m s 2 6 8 10 l h nlr phmh I I I I I I nh m nnjn ut g 0 0 T 0 MASS kg 0 1 1800 1600 14oo I 0 1200 l 0 1000 l i ill 0...

Page 200: ...22051b 54 KIAS 850 kg 18741b Altitude 0 up to 8500 ft pressure altitude NOTE The graph on the following page shows the rate ofclimb The gradient of climb cannot easily be determined with a graph but i...

Page 201: ...1 11 11 1 1 11 111 r 11 1 1 lu u SETTING j a EXAMPLE PRESSURE ALTITUDE 8000 t r ________ __ E 1 H RATE OF CL MB 560 lt rr n 2 8 mls j 1 1 11111111111 1 1 1 1 1 1 1 1 11 11 11 11 1 1 11 1 1 11 1j 1 rr...

Page 202: ...2051b 60 KIAS 850 kg 18741b Altitude 0 up to 8500 ft pressure altitude NOTE The graph on the following page shows the rate ofclimb The gradient of climb cannot easily be determined with a graph but it...

Page 203: ...11 LL uu s 1 EXAMPLI PRESSURE AlTITUDE 4000 ft OUTSIDEAIRTEMP 18 C I4 FJ FLIGHT MASS 975 kg 2150 I RESULT RATE OF CLIMB 740ft m 1 3 75 m 111111 1 1 1 1 1 1 1 1 l l l ll jl l jl li l jl lj Lr ri 1 1 1...

Page 204: ...D I TAS 16 r rT77 15000 EXAMPLE ______ POWERSETIING 80 LOAD PRESSURE ALTITUDE 6750 ft OAT ISA 10 C 14000 13000 __RESULT 12000 11 10000 g 9000 E s 8000 TRUE AIRSPEED w 7000 r c H i 8000 5000 4 110 TRUE...

Page 205: ...tance over a 50ft 15 m obstacle 744 m 2441 ft Ground roll 287 m 942 ft WARN NG Poor maintenance condition of the airplane deviation from the given procedures as well as unfavorable outside conditions...

Page 206: ...the following corrections must be taken into account compared to paved runways Grass up to 5 cm 2 in long 5 increase in landing roll Grass 5 to 10 cm 2 to 4 in long 15 increase in landing roll Grass l...

Page 207: ...ure Altitude OAT Mass Headwind comp Result LOG distance over 50 ft obstacle OUTSIDE AIR TEMPEF TURE C LANDING MASS lb MND OMPONENT m s 8888888 RI j o 2 4 e a 10 1200 1100 1000 w 000 d 800 700 m 0 1 li...

Page 208: ...5 65 75 85 95 105 115 i j Fi 0 ALTIMETER SETTING L 1013 hPa 29 92 inHg Example Pressure Attitude oAT Mass Hea n d co p Result 1 I LOG Ground Roll 195 m 640ft 6 8 10 L LW t 450 400 350 I J 300 o 0 z 0...

Page 209: ...nce over a 50ft 15 m obstacle 916 m 3005 ft Ground roll 304 m 977 ft WARNING Poor maintenance condition of the airplane deviation from the given procedures as well as unfavorable outside conditions hi...

Page 210: ...the following corrections must be taken into account compared to paved runways Grass up to 5 cm 2 in long 5 increase in landing roll Grass 5 to 10 cm 2 to 4 in long 15 increase in landing roll Grass...

Page 211: ...ETER SETTING 1013 hPa I 29 92 i Hg r Example Pressure Altitude 2000 tt 15 51b Headwind comp 10 kts Result LOG distance over 50 ft obstacle OUTSIDE AIR TEMPERATL lE C 1600 1500 1400 13oo I J 1200 D 110...

Page 212: ...mple 6 Zf e Altitude 2 0 0 ft_ c c 1 Mass Headwind camp Result LOG Ground Roll 2i0 600ft l l jlllljlll 1jllllj l 1 I 1I 11 I 1111 p1lljlllljll ll l 1 l n rprn f11Hf TTIJ IIIjlllljlllljllll 35 30 25 20...

Page 213: ...ISA MSL 5 3 14 GLIDE PERFORMANCE The following table shows the glide ratio and the resulting maximum horizontal distance in nautical miles per 1000 ft of altitude loss in a glide traveled in still air...

Page 214: ...t pipe ICAO Annex 16 Chapter X 78 7 dB A JAR 36 Subpart C 78 7 dB A With muffler ICAO Annex 16 Chapter X 69 5 dB A JAR 36 Subpart C 69 5 dB A If TAE 125 02 99 engine is installed if MAM 40 256 carried...

Page 215: ...Performance Diamond T AIRCRAFT DA40 D AFM Intentionally left blank Page 5 28 Revision 6 31 Jul 2013 Doe 6 01 05 E...

Page 216: ...ASS 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 PERMISSIBLE CENTER OF GRAVITY RANG...

Page 217: ...r and above this there is a comprehensive list of the equipment approved for this airplane Equipment List as also a list ofthat equipment installed when the airplane was weighed Equipment Inventory Be...

Page 218: ...tub 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 Report Every change in permanently insta...

Page 219: ...changes DA40D Serial No Registration Page No Changes in Mass Addition Subtraction Current Empty Mass Moment Moment Moment I Entry No Descriplion of I Partor Mass Arm Moment Mass Arm Moment Mass Arm M...

Page 220: ...ngesIn Mass 1 Addlllon t Sulltrll llon CurrantEinplyMass DIIICilpllon of Moment Moment Moment Enl yNo Partor Arm Moment M Arm Momtnl Mall Arm Momtnt IN our Modlflllation llg m lkuml llg m jkgm Ikill m...

Page 221: ...antity If an indicator shows 15 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 rnean for fuel quantity indication 3 Multip...

Page 222: ...al 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 admissible range The result found with the...

Page 223: ...important lever arms aft of the Datum Plane Front seats 2 30m 90 6 in Rear seats 3 25m 128 0 in Wing tank 2 63m 103 5 in Baggage 3 65 m 143 7 in 3 65 m 143 7 in 3 25 m 128 0 in 2 63 m 103 5 in 2 30 m...

Page 224: ...Fuel Quantity 400 US gal liters 175 150 300 r 40f 1501 j 125 f 30f t 1 100 100 200 l 75 20f 1 r sof 100 f so 1Qf f f 25 V V V V Fuel V v v f Ba 1gage V I 100 200 300 400 500 Load Moment Fr ont Seats R...

Page 225: ...empty fuel tanks Total of 1 4 2282 230 357 6 On board usable fuel 100 8 265 10 0 84 kg liter 7 01 b US gal Lever arm 2 63 m 103 5in 222 23 001 7 Total mass and total moment 1135 8 2917 60 with full f...

Page 226: ...lus 6 150 331 80 176 0 0 965 2127 100 8 222 345 29 989 260 22 528 0 0 2425 210 517 265 10 22 977 1065 8 2690 10 DA40 D AFM I 8 The total moments from rows 5 and 7 2425 and 2690 1 kgm 210 517and233 494...

Page 227: ...alance 600 400 CO 200 1 _ c Q 000 Ll 800 X CG Em elope The CG shown in the diagram is that from the example in Table 6 4 3 a CALCULA TION OF LOADING CONDITION row 7 pre take off condition The flight C...

Page 228: ...r of Gravity Position m j 2400 f 2200 c 2000 2 0 1800 DA40 D AFM The CG shown in the diagram is that from the example in Table 6 4 3 b CALCULA The flight CG position must be within the following limit...

Page 229: ...0 I V 2oool 1872 2020 r v I I i 0 I I y I I 1 I I I I I I I I I I I I I I I I I 2200 2400 2600 2352 FUGHT MASS MOMENT kgm D d v0 IS o o gJ r l b a Ill G o k 260 000 a j 1 I Ill J 1 1 I I I I I I I I I...

Page 230: ..._ BOQ QOOOQQ___ o ctJ 200 ooo t bP fl r fl t JP I I 260000 T 1 FUGH MASS MOMENT in lb r I i T 1100 I j CI DA40 D Ex mpie from 6 4 3 1000 I I 7 V L_ l 980 9oo L r 1 1 1 kt K I I I I I j I t I 200 1872...

Page 231: ...s are added to the Equipment List Airplane Serial No l 4 f Registration cc_ Descriotioli Type Part No Manulacturer COMMUNICATION NAVIGATION COMM 1 antenna Cl 291 Camant COMM 2 antenna Cl 292 2 Camant...

Page 232: ...to the Equipment List N IJle Nu b 4 1 tiJ1 ifle 1stratim j 3 C PartNo ECU j02 761 5RJ01R lhlelert ECUSaftware 02 761 ffi101R iiliielert TAE 125m232 ECUtvtppng jW 761 ffi105R ilhielert S14 230 A Date i...

Page 233: ...C Main Battery 6 5 EQUIPMENT LIST AND EQUIPMENT INVENTORY The following items are added to the Equipment List sooaNo J Re oo SL C lome 2f f o I r Description iJYpe PiltNo SIN Concorde I ELECTRICAL POW...

Page 234: ...Airplane Serial No J 4 JCf Registration W C Date t Y Description Type Part No Manu S N facturer AV ON CS COOLING Avionics cooling lan ACF314 ACF314 Sandia Aerospace Avionics cooling lan SAFE 328 305 4...

Page 235: ...ch servo KS 270 C 065 00178 2500 Bendix King X Pitch servo mount KM 275 065 00030 0000 8endiYJKing X Roll servo KS 271 C 065 00179 0300 Bendix Kiog Roll servo mount KM 275 065 00030 0000 Bendix King T...

Page 236: ...UIPMENT INVENTORY The following items are added to the Equipment List s c Airplane Serial No 1 4 3bl Registration Date Z5 IQ oescrilitloll TvtJe ParrNo Manuracturer SIN installed ELECTRICAL POWER Opti...

Page 237: ...nit E 01 ACK ELT remote unit E0105 ACK ELT antenna E0109 ACK ELT unit JE2 NG JE2 1978 1NG Jolliet Electronique ELTremote unit JE2 1978 16 Jolliet Electronique ELTantenna JE2 1978 73 Jolliet Electroniq...

Page 238: ...11eryerrcy axe G45912 Fi kar FUEL r Fuel transfer pump i i5100 00 15 iDukes i1iC i X i HYDRAULIC Master cylinder 10 54A Cleveland X Parking valve 60 5D Cleveland X Brake assembly 30 239B Cleveland X I...

Page 239: ...IST AND EQUIPMENT INVENTORY The following item is added to the Equipment List Alrplane Serial No Description SAFETY EQUIPMENT Emergency Egress Hammer Doe No 6 01 05 E Type TR OAM 40 401 Registration P...

Page 240: ...K Landing light 70346 01 0770346 00 Whelen X Electroluminescent lamp Quantaflex 1600 D4D 1131 20 05 Quantaflex Electroluminescent lamp Quantaflex 1600 D4D 1131 21 07 Quantaflex Electroluminescent lam...

Page 241: ...COM GPS 2 GNS 430 011 00280 10 CDI VORILOC GS GI106A 013 00049 01 CDI VORILOC GS 2 GI106A 013 00049 01 GPS antenna 1 GA56 011 00134 00 GPS antenna 2 GA56 011 00134 00 GPS annunciation MD41 1484 GPS an...

Page 242: ...lowing item is added to the Equipment List Airplane Serial No 16 Registration t C Date Description Type Part No Manufacturer ENGINE ENGINE CONTROL UNIT ECU 05 7611 001904 Technify Doe 6 01 05 E TR MAM...

Page 243: ...Garmin Integrated avionics 1 GIA63 011 00781 01 Garmin Integrated avionics 2 GIA63 011 00781 01 Garmin X Integrated avionics 1 GIA63W 011 01105 20 Garmin Integrated avionics 2 GIA63W 011 01105 20 Garm...

Page 244: ...Thielert Compact engine display TAE CED 125 02 7730 5501 06 02 6 Thielert iAuxiiiCIIy erryirre Ui JiCJy iAED 125 02 7730 5503 01 01 lTilieiert i i i Auxiliary engine display AED 125 02 7730 5503 02 0...

Page 245: ...DM 3225 91 00 Diamond NLG wheel fairing shell RH DM 3225 92 00 Diamond Bracket assy LH MLG wheel fairing DA4 3215 31 00 Diamond Bracket assy RH MLG wheel fairing DM 3215 32 00 Diamond Brake cover MLG...

Page 246: ...0 2 Tne cornpiete Part i urnberofthe ELT unit depends on the registration ofthe airpiane in which the ELT is installed 3 Amerex A620T is UL approved and can be used in airplanes registered in Canada a...

Page 247: ...ENT LIST AND EQUIPMENT INVENTORY The following item is added to the existing table Airpiane Serial No Registration Date Description Tvpe Part No Manufacturer S N lnst d FUEL AJtemate means for fuel qt...

Page 248: ...DA40 D AFM 66Diamond V f AIRCRAFT Mass Balance 7 Refer to Service Bulletin MSB 04 044 latest effective issue for approved firmware and mapping Place Date Doe 6 01 05 E Revision 6 31 Jul 2013 Page 6 25...

Page 249: ...Mass Balance MADiamond 47 AIRCRAFT DA40 DAFM Intentionally left blank Page 6 26 Revision 6 31 Jul 2013 Doe 6 01 05 E...

Page 250: ...OR 7 14 7 9 POWER PLANT 7 17 7 9 1 ENGINE GENERAL 7 17 7 9 2 OPERATING CONTROLS 7 18 7 9 3 PROPELLER 7 22 7 9 4 ENGINE INSTRUMENTS 7 24 7 9 5 FUEL SYSTEM 7 26 7 9 6 COOLING SYSTEM 7 35 7 9 7 TURBO CHA...

Page 251: ...d on the engine side by stainless steel cladding The two main bulkheads are GFRP CFRP items The wings have a front and rear spar each wing has a top shell and a bottom shell a fail safe concept The wi...

Page 252: ...minum bracket They are secured in position by a roll pin The absence of this roll pin can lead to the loss ofthe hinge pin and a consequent loss offlight safety Operation A rod end bearing is screwed...

Page 253: ...lage 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 which has locking varnish applied to it Damage...

Page 254: ...inst over running 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 mea...

Page 255: ...rod can be visually inspected at the upper end of the rudder Construction GFRP sandwich Hinges Upper hinge One bolt Operation Page 7 6 LO Jer hinge Bearing bracket including rudder stops heid by 4 sc...

Page 256: ...r nose up 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 attachment Forward adjustment Whilst keeping the handl...

Page 257: ...it 4 ECU Test button 25 Compact Engine Display CED 5 ECU Swap switch 26 Auxiliary Engine Display AED i v Kotary ouuons ror instrurnent lighting and flood light 7 Flap selector switch 28 Stall warning...

Page 258: ...n Designations and abbreviations used to identify the circuit breakers are explained in Section 1 5 DEFINITIONS AND ABBREVIATIONS of the AFM VFR instrument panel example IFR instrument panel example D...

Page 259: ...oll bar on the left and right side next to the front seats as well as on the central console above the passengers heads The spherical nozzles are opened and closed by twisting The figures below show t...

Page 260: ...Hydraulically operating disk brakes act on the wheels ofthe main landing gear The wheel brakes are individually operated by means of toe pedals Parking Brake The lever is located on the small center c...

Page 261: ...cription Hydraulic System Schematic brake pedals pilot parking brake valve brake cvlinder LH Page 7 12 Revision 6 4ADiamond T AIRCRAFT 31 Jul 2013 DA40 D AFM brake pedals co pilot brake cvlinder RH Do...

Page 262: ...ls The seats have removable furnishings and are equipped with energy absorbing foam elements The seats are fitted with three point safety harnesses The harnesses are fastened by inserting the belt cli...

Page 263: ...ocking device on the left side near the canopy opening lever by turning the key clockwise The closed and blocked canopy can be opened from inside by pulling the lever inside the opening handle WARNING...

Page 264: ...cy Egress Hammer is installed on the floor panel under the co pilot s seat If the canopy can not be opened in case of an emergency use the Emergency Egress Hammer to break through the canopy WARNING M...

Page 265: ...by turning the key clockwise The closed and blocked door can be opened from inside by pulling the lever inside the opening handle For a better handling an additional handle is mounted WARNING Do not...

Page 266: ...panel under the co pilot s seat see Figure below Ifthe canopy can not be opened In case ofan emergency use the emergency axe to break through the canopy WARNiNG Make sure not to harm other persons by...

Page 267: ...02 99 Max power 1689 cm3 103 in 1991 cm 121 5 in 99 kW 135 DIN HP at 2300 RPM at sea level and ISA Max continuous power 99 kW 135 DIN HP at 2300 RPM at sea level and ISA The indications for monitorin...

Page 268: ...ccording to the desired engine power preselected with the power lever The propeller governor is flanged onto the front of the engine The propeller governor oil circuiaiion is a separate oii circulatio...

Page 269: ...e power distribution system START starting the engine ENGINE MASTER The engine can only be cranked with the ENGINE MASTER switched to ON To shut down the engine the ENGINE MASTER is switched to OFF EC...

Page 270: ...nd the engine must run without a change Power lever above IDLE or RPM above approximately 900 If an ECU A or ECU B caution message is displayed the ECU TEST button can be pressed for more than 2 secon...

Page 271: ...perating lever is located under the instrument panel to the left ofthe center console To open the alternate air source the lever is pulled to the rear Normally the alternate air source is closed with...

Page 272: ...the propeller hub the leading edge is coated with adhesive PU foil These blades combine the lowest weight whilst minimizing vibration Propeller Control The propeller pitch control system is integrated...

Page 273: ...igh 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 there are no loose stones or similar items...

Page 274: ...general inforrnaiion Exactvalues cannot be indicated on the CED 125 Indications on the Engine Instrument CED 125 Designation Indication Unit RDM PrnnAIIAr RD A 1 min OP Oil pressure bar OT Engine oil...

Page 275: ...ication FUEL QUANTITY MAIN Fuel quantity MAIN tank FUEL QUANTITY AUX Fuel quantity AUX tank WATER LEVEL Coolant level FUEL TEMP LEFT Fuel temperature left tank FUEL TEMP RIGHT Fuel temperature right t...

Page 276: ...LY NORMAL FUEL TRANSrm t FUEL SUPPLY FUEL RETURN lliEi8 FUEL TRAI ISFER _ Y OFF main tank emergency fuel valve NORMAL EMERGENCY FUEL C llf H l V EMERGENCY FUEL TRANSFER main tank c EMERGENCY FUEL SUPP...

Page 277: ...when the auxiliary tank is empty or the main tank is full If fuel transfer with the transfer pump becomes impossible for any reason fuel can also be taken directly from the AUX tank rightwing As the...

Page 278: ...faiiure The check vaive Vith capiiiar1 ailovvs air to enter the tank but prevents flO J offuei to the outside The capillary equalizes the air pressure during climb The hose terminations are situated...

Page 279: ...ank If the Long Range Tank is installed the filler tube of the main and the auxiliary tank is replaced by another tank chamber This tank chamber has a capacity of approx 5 US gal 19 liters The ventila...

Page 280: ...g The fuel cooler is installed in the right hand stub wing between the main spars it receives its cooling air through an air scoop on the lowersurface ofthe stub wing This inlet is closed with a baffi...

Page 281: ...irfoil of the wing With this recess the device is held against the stall strip at the leading edge ofthe wing The exact position is marked by a bore in the stall strip Then the metal connector is pres...

Page 282: ...Airplane Description 4rADiamond T AIRCRAFT Alternate Mean for Fuel Quantity Indication for Long Range Tank Page 7 32 Revision 6 31 Jul 2013 DA40 DAFM Doe 6 01 05 E...

Page 283: ...must stand on horizontal ground with the wings level I The fuel indicator 11 includes a protractorfor an additional pitch angle measurement The I fuel indicator 11 is placed on top of the fuselage tub...

Page 284: ...added Doe 6 01 05 E 4ADiamond AIRCRAFT 0 240 220 220 2 210 200 190 I 180 170 160 l 150 D 140 QJ 120 120 a Fuel Quantity Indicator 11 Temporary Revision Alternate Means for Fuel Quantity TR MAM 40 816...

Page 285: ...48 40 90 87 78 71 55 105 97 90 80 73 112 107 98 92 83 123 115 108 103 95 135 128 120 112 105 145 137 130 124 112 160 152 145 137 130 175 168 157 150 143 192 188 180 172 165 225 215 208 202 192 Tempora...

Page 286: ...123 110 100 90 140 132 115 102 95 148 136 129 122 113 162 149 138 130 118 174 158 150 138 131 180 171 162 156 146 185 180 175 166 156 200 195 184 176 168 217 205 196 189 181 232 220 215 204 196 248 23...

Page 287: ...el or a blend of Diesel Fuel with JET Fuel is used If the fuel blend is uncertain the engine must not be started in this temperature range either Between 5 oc and 4 oc 23 F to 39 F the lower yellow ba...

Page 288: ...not heated If the airplane is operated in a cold environment it must be changed from Diesel Fuel operation to JET Fuel operation To ensure that no blend of JET Fuel with Diesel Fuel is in one of the t...

Page 289: ...adiator is activated by a thermostat valve Additionally a coolantto air heat exchanger is provided for the cabin heat system The flow through the heat exchanger is independent of the coolant temperatu...

Page 290: ...rplane Excess exhaust gases bypass the turbine The bypass is controlled by the ECU through the waste Q 1 VQIVV r IIIQIIIIVIU tJIV JUI V ioii VI IJVIIUIY LIIV oVIIItJIU I lOVI V IIVWY OJ LIIV __ V n _...

Page 291: ...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 circuit lubricates the gearand serves the governor sys...

Page 292: ...Airplane Description Diamond T AIRCRAFT 7 10 ELECTRICAL SYSTEM DA40 DAFM I L 1 il Page 7 38 Revision 6 31 Jul 2013 Doe 6 01 05 E...

Page 293: ...tput line also runs through the current sensor which provides an indication ofthe power being supplied to the electrical system by the alternator including the current for battery charging In the even...

Page 294: ...eiay is controlled with the ELECTRIC MASTER key switch which is located on the left hand side of the instrument panel In addition a 12 V 12 Ah sealed lead acid battery ECU backup battery is installed...

Page 295: ...key switch The battery bus provides power to the ECU bus and heavy duty power to the starter it also provides power to the main bus via the power relay which can be controlled by the ELECTRIC MASTER k...

Page 296: ...onnected to the main bus via the essential tie relay The essential bus provides power to the consumers connected to the essential bus and the essential avionic bus via the essential avionic relay The...

Page 297: ...green range On a conventional instrument panel the ENGINE caution light illuminates if the voltage stays in the yellow range for longer than 1 minute Ammeter The ammeter displays the intensity of cur...

Page 298: ...ed on and its brightness is adjusted Pilot Heating The Pilot probe which provides measurement for the Pitot static system is electrically heated_ The heating is activated with a switch P TOT on the ro...

Page 299: ...tem engine I OT Oil pressure lubrication system engine I OP Coolant temperature I CT Gearbox temperature I GT Camshaft RPM twice Crankshaft RPM twice Fuel pressure in the common rail Manifold pressure...

Page 300: ...B Normally the engine is controlled and regulated by the ECU A The ECU B is a backup system to ensure redundancy In case of an internal error during operation or the loss ofa sensor signal the system...

Page 301: ...rt is sounded This test verifies functionality of the microprocessor the lights and the aural signal The pilot may initiate additional system tests by holding the acknowledge button for 2 seconds All...

Page 302: ...EM Tritn failure warr r g n1essage TRil vi FAiLj The White Wire annunciator panel is prepared for the installation of an autopilot in the DA 40 D When the autopilot is installed and ready for operatio...

Page 303: ...given in 48 3 1 LOW VOLTAGE CAUTION LOW VOLTS Engine control unit caution message ECU A or ECU B This caution message is displayed in case of a malfunction of the related engine control unit ECU A or...

Page 304: ...d This is a normal function of the system After a cooling period the heating system will be switched on again automatically Engine parameter caution message ENGINE This caution message is displayed if...

Page 305: ...stem is installed additional static sources may be installed 7 12 STALL WARNING SYSTEM If airspeed drops below approximately 10 to min 5 knots above the stalling speed the stall warning horn located i...

Page 306: ...Airplane Description Page 7 52 Revision 6 6 Diamond w AIRCRAFT DA40 D AFM Intentionally left blank 31 Jul 2013 Doe 6 01 05 E...

Page 307: ...ANSPORT 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 8 8 4 5 JACKING 8 8 8 4 6 ALIGNMENT 8 8 8 4 7 ROAD TRANSPORT 8 9 8 5 CLEA...

Page 308: ...tive inspection checklists are prescribed in the Airplane Maintenance Manual Chapter 05 For maintenancework on engine and propeller the currently effective Operator s Manuals Service Instructions Serv...

Page 309: ...ANSPORT 8 4 1 GROUND HANDLING WITHOUT TOW BAR During forward traversing the nosewheel will follow the movement ofthe airplane Change in direction is achieved by pulling on the propeller near the spinn...

Page 310: ...lane 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 the nose wheel fairing as shown on th...

Page 311: ...ow 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 rearward the tow bar must be held firmly to pr...

Page 312: ...control surfaces can hit the stops in strong tail wind This can lead to excessive wear or damage WARNING The control surfaces gust lock must be removed before flight The coniroi surfaces gust iock is...

Page 313: ...ond V4 AIRCRAFT Affected Chapters 8 4 GROUND HANDLING I ROAD TRANSPORT 8 4 3 PARKING The Figures are amended to read Temporary Revision Removal of Pilot Gust Lock Mount Doe 6 01 05 E TR MAM 40 1 020 1...

Page 314: ...DA40 DAFM Diamond AIRCRAFT Handling Doe 6 01 05 E Revision 6 31 Jul 2013...

Page 315: ...the two jackpoints located on the lower side ofthe 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 section at the fuselage vertical tail j...

Page 316: ...sportation both wings must be removed from the fuselage To avoid any damage the wings must be stored in an upright position on the leading edge with the root rib area positioned on an upholstered prof...

Page 317: ...mended not to store HH airpiane OLHS1de for ong periods of time Dirt insects etc can be removed with water alone and if necessary with a mild detergent An automotive paint cleaner can be used for stub...

Page 318: ...resistant to almost any solvent The blades may be treated with commercial automotive cleaning agents or preservatives The penetration of moisture into the wooden core must be avoided by all means Sho...

Page 319: ...Name Aeroshell Compound 07 Any source AL 5 DTD 4060 1 Remove any snow from the airplane using a soft brush 2 Spray de icing fluid onto ice covered surfaces using a suitable spray bottle 3 Use a soft p...

Page 320: ...DA40 DAFM 4aDiamond V AIRCRAFT CHAPTER 9 SUPPLEMENTS Supplements Page 9 1 INTRODUCTION 9 2 9 2 LIST OF SUPPLEMENTS 9 3 Doe 6 01 05 E Revision 6 31 Jul 2013 Page 9 1...

Page 321: ...he Supplements 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 ChapteL The Air...

Page 322: ...OF SUPPLEMENTS Temporary Revision SIN 40 080 The following supplements must be added to the List of Supplements s Supplement A10 DME KN 62 A s Supplement A25 Audio Panel GMA 340 VFR Doe No 6 01 05 E T...

Page 323: ...ing Inc ADF KR 87 A9 2 17 Feb 2003 D Bendix King DME KN 62A A10 2 17 Feb 2003 D Bendix King A11 Compass System KCS 55 A 4 Bendix King 15 Mar 2005 D A13 Autopilot KAP 140 1 26 May 2003 D Bendix King CO...

Page 324: ...A25 15 Mar 2005 D 8MA340 VFR COM I NAV I 8PS A26 8NS 430 VFR 15 Mar 2005 D GARMIN COM I NAV I 8PS A28 8NS 530 VFR Operation 0 20 Mar 2003 D 8armin A29 Transponder 8TX 330 I 8TX 328 1 11 0ct 2007 D J...

Page 325: ...002 D X DAVTRON Attitude Indicator E5 LUN 1241 0 11 Nov 2002 D MIKROTECHNA E6 Operation with Baggage 0 09 Jan 2004 D Extension and Baggage Tray E7 Winter Baffle Fresh Air Inlet 1 27 Apr 2005 D Emergen...

Page 326: ...Supplements 66Diamond T4 AIRCRAFT DA40 DAFM S4 ELT Artex ME 406 10 Apr 2007 0 I I I I I I I t Page 9 6 Revision 6 31 Jul 2013 Doe 6 01 05 E...

Page 327: ...schrift BehOrde Stempel Anerkennungsdatum 4 USTRO Abi ll nmbli imik 13 DEL 1 002 Diese Erg nzung ist anerkannt fOr die Joint Aviation Authorities JAA durch die Oster reichische Luftfahrtbehorde Austro...

Page 328: ...AnlaB Nr Ab Se e Datum der Revision Aner kennungs V fll erk Datum der Datum der Unter schrift MAM 40 099 P N Anderung Autopilot Computer schnltt alle Dok Nr 6 01 05 alle ausgenommen 9 A13 0 Revision 1...

Page 329: ...1 Nov 2002 9 A13 1 26 Mai 2003 9 A13 2 26 Mai 2003 9 A13 3 26 Mai 2003 9 A13 4 26 Mai 2003 9 A13 5 26 Mai 2003 9 A13 6 26 Mai 2003 anerk 9 A13 7 26 Mai 2003 2 anerk 9 A13 8 26 Mai 2003 9 A13 9 26 Mai...

Page 330: ...9 A13 17 26 Mai 2003 9 A13 18 26 Mai 2003 9 A13 19 26 Mai 2003 9 A13 20 26 Mai 2003 9 A13 21 26 Mai 2003 9 A13 22 26 Mai 2003 9 A13 23 26 Mai 2003 9 A13 24 26 Mai 2003 9 A13 25 26 Mai 2003 9 A i3 26 2...

Page 331: ...rganzung A13 Autopilot KAP 140 9 A13 33 26 Mai 2003 9 A13 34 26 Mai 2003 9 A13 35 26 Mai 2003 9 A13 36 26 Mai 2003 9 A13 37 26 Mai 2003 9 A13 38 26 Mai 2003 9 A13 39 26 Mai 2003 9 A13 40 26 Mai 2003 9...

Page 332: ...N 9 A13 7 3 NOTVERFAHREN 9 A13 9 4A NORMALE BETRIEBSVERFAHREN 9 A13 12 48 ABNORMALE BETRIEBSVERFAHREN 9 A13 29 5 LEISTUNGEN 9 A13 33 6 MASSE UNO SCHWERPUNKT 9 A13 33 7 BESCHREIBUNG DES FLUGZEUGES UNO...

Page 333: ...Erganzung enthalten sind mussen zusammen mit dem vollstandigen Hand buch verwendet werden Diese Erganzung ist ein permanenter Teil des Flughandbuches und mur solange im Handbuch verbleiben wie das Au...

Page 334: ...KIAS Minimale Geschwindigkeit Autopilot 70 KIAS G Das ntercep ieren vorgewah er Hohen un er 800ft uber Grund ist verboten sofern die Altitude Preselect Option installiert ist H Der Autopilot mur beim...

Page 335: ...il mul1 der Autopilot deaktiviert werden L Folgendes Hinweisschild fOr Betriebsgrenzen ist im direkten Sichtfeld des Piloten anzubringen Betriebsgrenzen des KAP 140 Autopilot Systems Wenn Alternate St...

Page 336: ...AP DISC Knopf DRUCKEN und HALTEN wiihrend des Abfangens C FLUGZEUG manuell neu TRIMMEN nach Bedarf D AUTOPILOT Sicherung ZIEHEN ANMERKUNG Alternativ kann der Avionik Hauptschalter ausgeschaltet werden...

Page 337: ...einer Notfallsituation zu geben 1 Eine Fehlfunktion der automatischen Trimmung kann an einer unbeabsichtigten Flugbahnanderung oder an abnormalen Steuerausschlagen oder Bewegungen des Trimmrads erkan...

Page 338: ...alten und trim men Sie das Flugzeug nach Bedarf handisch nach Nach diesen Schritten is das automatische bzw elektrische Trimmsystem durch Ziehen der richtigen Sicherung stillzulegen Wie bei jedem ande...

Page 339: ...t ist eine Abfol ge einzelner interner Checks die den ordnungsgemar en Betrieb des Systems i iberpri ifen bevor normaler Betrieb ermoglicht wird Die Abfolge wird durch PFT und eine ansteigende Zahl fU...

Page 340: ...tische Trimmung den Vorflug Test nicht bestanden Die AUTOPILOT Sicherung mu 1 gezogen werden Die manuel le elektrische Trimmung kann nicht verwendet werden 2 TEST DER MANUELLEN ELEKTRISCHEN TRIMMUNG w...

Page 341: ...al wenn das QNH am Ho henmesser eingestellt werden mu Es werden keine weite ren Aufforderungen Biinken erteilt b ALTITUDE SELECT Knopf Hohenvorwahl nur vorhanden wenn die Altitude Preselect Option ins...

Page 342: ...schwindigkeit WARNUNG Bei aktiviertem Autopiloten mu der verantwortliche Pilot diesen laufend uberwachen und vorbereitet sein ihn zu deaktivieren sowie korrektive Sofortma nahmen inklusive manueller S...

Page 343: ...ine Verrninderung der Leistung notwendig sein urn die gewunschte Sinkrate zu halten ohne die rnaxirnale Geschwindigkeit fOr den Autopiloten zu Oberschreiten WICHTIGER HINWEIS Verrneiden Sie abrupte Le...

Page 344: ...nschte Steig Sink rate angezeigt wird Der Autopilot wird diese dann halten 4A 3 9 RE S FLUG ANMERKUNG Im Altitude Hold kann die Flughohe in starken Turbulenzen um bis zu 120ft variieren wenn die bei G...

Page 345: ...Steig Sinkrate fUr das lnterceptieren der gewiihlten Flughohe EIN STELLEN ANMERKUNG Turbulenzen verschlechtern die Kursverfolgung durch den Autopiloten Die Verwendung des ROL Basismodus wird bei Betri...

Page 346: ...rtical Trim empfohlen fOr Hohenanderungen unter 100ft 1 VERTICAL TRIM Steuerung DRUCKEN und HALTEN des UP hinauf oder rlAs DN hinunfAr KnopfAs VArtical Trim wird eine Rate von etwa 500 ftlmin wahlen 2...

Page 347: ...rbulen zen andern b Heading Hold Steuerkurs halten 1 Heading Selector Bug DREHEN auf den gewUnschten Steuerkurs Hea ding 2 HDG Knopf Steuerkurs Modus DROCKEN Beachten Sie da die Anzeige HOG aufleuchte...

Page 348: ...cept Punkt erreicht ist wird HDG deaktiviert die Anzeige ARM erlischt und der gewahl te Kurs wird automatisch interceptiert und verfolgt 2 Wenn der Kursabweichungsbalken weniger als 2 3 Punkte ausgesc...

Page 349: ...um dem Autopiloten den Bezug zum Kurs zu liefern das Flugzeug wird allerdings bis zur Interception annahernd das letzte Heading verfolgen d Wenn der Kursabweichungsbalken COl mehr als 2 bis 3 Punkte...

Page 350: ...Punkte ausgeschlagen ist Das Flugzeug verbleibt im HOG Modus oder ROL falls HDG nicht gewahlt ist mit angezeigtem APR ARM sobald der errechnete Intercept Punkt erre cht st wird der HDG Modus deaktivie...

Page 351: ...t ist wird am Autopilot 5 Sekunden lang HOG blinken um den Piloten daran zu erinnern den HOG Bug auf den gewunschten Anflugkurs zu setzen Basierend auf der Position des HOG Bug wird danach automatisch...

Page 352: ...r der HDG Bug auf den gewunschten Kurs ein estellt wird falls Compass System KCS 55A installiert ist 2 BC Landeanflug Kopplung d h ruckseitiger Localizer Kurs REV a BARO Einstellung PROFEN wenn nicht...

Page 353: ...innerungshilfe b REV Modus Auswahlknopf ORUCKEN c Heading Select Knopf OREHEN bis Obereinstimmung mit dem Localizer Front Course lnbound Steuerkurs ANMERKUNG Wenn REV ausgewahlt ist wird am Autopilot...

Page 354: ...rs automatisch interceptiert und verfolgt e Wenn der Kursabweichungsbalken COl mehr als 2 bis 3 Punkte ausgeschlagen ist der HOG Modus wird deaktiviert sobald der APR Modus gewahlt wird die Anzeige RE...

Page 355: ...Der Autopilot kann den Glideslope von oben oder unten interceptieren ANMERKUNG Das lnterceptieren einer vorgewiihlten Hohe zum Erreichen der MDA ist bei Nichtpriizisionsanflugen nicht zu empfehlen Die...

Page 356: ...C Knopf DROCKEN zum Deaktivieren des Autopiloten 48 A8NORMALE 8ETRIE8SVERFAHREN 48 7 FEHLFUNKTION DES AUTOPILOTSYSTEMS A Blinkende PT Anzeige mit einem auf oder abwarts zeigendem Pfeil auf dem isnlflv...

Page 357: ...ge des Autopilot Computers 1 Ein rotes P zeigt an daf die Nickachse Pitch Axis des Autopiloten abgeschaltet wurde und nicht wieder aktiviert werden kann AKTIVIEREN SIE NIGHT EIN SYSTEM MIT AUSSCHLIESS...

Page 358: ...ekte Baro Einstellung IIH muell EINGEBEN oder BARO drucken um den momentanen Wert zu akzeptieren 2 Hohenwarnung vorwahl nach Bedarf EINSTELLEN D Blinkende Modus Anzeige im Display des Autopiloten Eine...

Page 359: ...hat der Autopilot bereits auf eine Standard Betriebsart zuruck geschaltet d h ROL und oder VS Ein sofortiger Versuch den verlorenen Modus zu reaktivieren kann unternommen werden wenn das hinderliche...

Page 360: ...i ir die Verwendung des KAP 140 Systems in der DA 40 lnstallation der Autopilot mul1 innerhalb dieser Grenzen betrieben werden Der Autopilot KAP 140 hat ein elektrisches Trimmsystem Dieses ermoglicht...

Page 361: ...Avionic Bus Schiene fUr die Sicherungen der Funkgerate und des Autopiloten ein und ausgeschaltet Die Funktion Electric Master Schlusselschalter bleibt unverandert Er kann in Notsituationen dazu verwe...

Page 362: ...installiert RFOIENELEMENTE UNDANZ IGEN 1 NICKACHSE P ANZEIGE Wenn sie leuchtet zeigt dies eine Fehlfunktion der NlcKacnse an t mweoer w1ro oer AUtOpilOt oeClKliVIell uue 01e v u H u Nickachse verhinde...

Page 363: ...ht der Autopilot in den HOG Modus der das Flugzeug anweist jenen Steuerkurs Heading aufzunehmen und zu halten der mit der Heading Select Bug auf dem HSI gewahlt wurde Ein neuer Steuerkurs kann jederze...

Page 364: ...Vertikai Modus zum Zeitpunkt der Betatigung lm VS Modus wird beim ersten DrUcken die vorgegebene Steig Sinkrate im Display angezeigt Jeder unmittelbar folgende kurze Knopfdruck erhiihUvermindert die v...

Page 365: ...matisch Altitude Hold Arming aktiviert sobald die Referenzhohe fUr die Hohenwarnung mit den Drehknopfen eingestellt wird Beachte Die Warnfunktionen sind unabhiingig vom Arming Prozel3 und somit auch b...

Page 366: ...dauerhaft im Bereich zwischen 200 und 1000 ft van der vorgewahlten Flughi ihe sofern das Flugzeug vorher aur erhalb dieses Bereiches war Blink 1 fUr zwei Sekunden beim erstmaligen Oberfliegen der gewi...

Page 367: ...topilotbetrieb fUhrt zur Deaktivierung des Autopiloten Auf dem SteuerknUppel des Piloten angebracht 19 CWS Knopf Control Wheel Steering nicht abgebildet Wenn gedrUckt und gehalten werden die Servokupp...

Page 368: ...einer Abweichung von 200ft von der gewi ihlten Hohe auf s Die Nachricht AUTOPILOT trill auf wenn der Autopilot entwcdcr durch den Piloten oder automatisch deaktiviert wurde s Die Nachricht CHECK PITCH...

Page 369: ...40 D FHB Ergiinzung A13 Autopilot KAP 140 8 HANDHABUNG INSTANDHALTUNG UND WARTUNG Es ergeben sich keine Anderungen des Kapitels 8 des Flughandbuches Dok Nr 6 01 05 Revision 1 26 Mai 2003 Seite 9 A13...

Page 370: ...OAM 40 137 DA 40 D Unterschrift Behorde _ _ i ll d Stempel i 1030 Wicu chuirchgasse 11 Anerkennungsdatum 18 JW1 i JO S Diese Ergl lnzung ist anerkannt fOr die Joint Aviation Authorities JAA durch die...

Page 371: ...1 schnitt OAM 40 12B 1 Panel I 7 Version DA4 3140 00 00 OAM 40 137 liP WX 500 I I i i Dok 6 01 01 Dok 6 01 05 Selte 9 A24 1 9 A24 2 9 A24 7 liP I i Revision 2 Datum der IAner Datum der Datum der Unter...

Page 372: ...1 Dok 6 01 05 Seite Revision 2 28 Feb 2003 Ergiinzung A24 Stormscope WX 500 Datum 9 A24 0 28 Feb 2003 9 A24 1 28 Feb 2003 9 A24 2 28 Feb 2003 9 A24 3 28 Feb 2003 9 A24 4 28 Feb 2003 9 A24 5 28 Feb 200...

Page 373: ...N 9 A24 4 3 NOTVERFAHREN 9 A24 4 4A NORMALE BETRIEBSVERFAHREN 9 A24 4 48 ABNORMALE BETRIEBSVERFAHREN 9 A24 5 5 LEISTUNGEN 9 A24 5 6 MASSE UNO SCHWERPUNKT 9 A24 5 7 BESCHREIBUNG DES FLUGZEUGES UNO SEIN...

Page 374: ...ert ist Diese Erganzung wurde nach bestem Wissen und Gewissen ubersetzt In jedem Fall ist die Originalversion in englischer Sprache mar geblich ANMERKUNG Das Stomscope ersetzt weder ein Wetterradar no...

Page 375: ...andbuches zu berucksichtigen 7 BESCHREIBUNG DES FLUGZEUGES UNO SEINER SYSTEME ANMERKUNG Alle Funktionen des Stormscopes werden durch das COM NAV GPS GNS 430 530 oder durch das MFD GPS KMD 150 nur DA 4...

Page 376: ...en zum GNS 430 530 oder KMD 150 weiter BEDIENUNG EINSCHALTEN Beim Einschalten fUhrt das WX 500 einen Einschalt Selbsttest durch Der Selbsttest dauert ungefiihr 25 Sekunden um sicherzustellen da alie H...

Page 377: ...rzustellen dal die Entladepunkte in bezug auf den aktuellen Kurs korrekt sind KURSSTABILISIERUNG optional Das Kursstabilisierungs Feature korrigiert automatisch die Position der Entladepunkte am Dispi...

Page 378: ...STRO C cOL GmbH Behorde k Stempel A 1030Wicn dumchgussc 1 1 1 f Anerkennungsdatum 0 7 OIU Z005 l I 1 Dlese Erganzung ist f lr die EASA durch die Clsterri che Luftfah e ordeAustro Control ACG als primi...

Page 379: ...R Betrieb 9A 32 10 JH Lackner ohne Aulopllol 9 A32 17 bls 26 Feb 2007 fOrDAIJ 16 Mal2007 9 A32 20 9 A32 44 GARMIN 9 A32 1 bls Service 9 A32 5 tR Kremnltzer Bullelin Nr 15 Feb 2008 fOrDAI 29 Mal 2008 0...

Page 380: ...A32 4 01 Jun 2008 9 A32 5 01 Jun 2008 9 A32 6 01 Jun 2008 9 A32 7 01 Jun 2008 9 A32 8 01 Jun 2008 9 A32 9 01 Jun 2008 9 A32 10 01 Jun 2008 9 A32 11 01 Jun 2008 9 A32 12 01 Jun 2008 9 A32 13 01 Jun 200...

Page 381: ...Jun 2008 9 A32 29 01 Jun 2008 9 A32 30 01 Jun 2008 9 A32 31 01 Jun 2008 9 A32 32 01 Jun 2008 9 A32 33 01 Jun 2008 9 A32 34 01 Jun 2008 9 A32 35 01 Jun 2008 9 A32 36 01 Jun 2008 9 A32 37 01 Jun 2008 Q...

Page 382: ...48 01 Jun 2008 9 A32 49 01 Jun 2008 9 A32 50 01 Jun 2008 9 A32 51 01 Jun 2008 9 A32 52 01 Jun 2008 9 A32 53 01 Jun 2008 9 A32 54 01 Jun 2008 9 A32 55 01 Jun 2008 9 A32 56 01 Jun 2008 9 A32 57 01 Jun...

Page 383: ...8 3 NOTVERFAHREN 9 A32 23 4A NORMALE BETRIEBSVERFAHREN 9 A32 37 4B ABNORMALE BETRIEBSVERFAHREN 9 A32 40 5 LEISTUNGEN 9 A32 46 6 MASSE UNO SCHWERPUNKT 9 A32 46 7 BESCHREIBUNG DES FLUGZEUGES UNO SEINER...

Page 384: ...f Bezeichnung der Sicherungen am lnstrumentenbrett ESSENTIAL BUS HORIZON ADC AHRS COM1 FLOOD GPS NAV1 XPDR LANDING PFD PITOT FLAPS APWARN MASTER CONTROL Dok 6 01 05 Rev 3 Artificial Horizon KOnstlich...

Page 385: ...lay Instrument Lights lnstrumentenbeleuchtung Avionic CDU Cooling Fans Avionik CDU LOfter Power Strobe Lights Zus HIHilellstor warnlidtter ACLs Position Lights Positionslichter Taxi Light I Map Lights...

Page 386: ...NZWERTE g Oltemperatur TAE 125 01 TAE 125 02 99 MAM 40 256 durchgefi ihrt Minimum 32 oc 30 oc Maximum 140 oc 140 C i KOhlmitteltemperatur TAE 125 01 TAE 125 02 99 MAM 40 256 durchgefiihrt Minimum 32 o...

Page 387: ...er 11 V Kraftstoff unter 0 45 menge US gal Gelber Bogen Salken Warnbereich 1 2 bis 2 3 bar GrUner Roter Bogen I Balken Gelber Bogen Bogen Balkan Salken normaler oberer Betriebs Warnbereich verbotener...

Page 388: ...griiner gelber roter Bogen Bogen Bogen Balken Bogen Balken Balken Balken normaler oberer Warn Warn bereich Betriebs bereieh verbotener bereich Bereieh uber bis 2300 RPM 2300 RPM uber 1 2 bis 2 3 bar 2...

Page 389: ...abellen beschreiben die Farben und Bedeutungen der Warn Vorwarn und Zustandsanzeigen des G1000 Systems Farbe und Bedeutungen der Warnungen des G1000 Systems Warnungen rot WARNING ENG TEMP OIL TEMP OIL...

Page 390: ...ube isUsind nicht geschlossen und verriegelt Fehler im automatischen Trimmsystem des Autopiloten wenn Autopilot eingebaut Das G1000 System kann keine GPS basierten Navigationsdaten liefern Das G1000 S...

Page 391: ...GU A beftndet sich im FADEC Test wilhrend des Checks Vor dem Start Fehler in der Motorsteuerelnhelt ECU B oder ECU B befindet sich im FADEC Test wahrend des Checks Vor dem Start Wenig Kraftstoff im H...

Page 392: ...AN FAIL MFD FAN FAIL GIA FAN FAIL Dok 6 01 05 Bedeutung AnlaB Gli ihkerzen des Motors sind aktiv Kraftstotf wird vom Zusatz in den Haupttank gepumpt Der Li ifter fi ir das Primare Flugdisplay arbeitet...

Page 393: ...Fluge in bekannte oder vorhergesagte Vereisungsgebiete sind verboten Fluge in bekannte Gewitter sind verboten Funktionsfahige operationelle Mindestausrustung In der folgenden Tabelle ist die funktions...

Page 394: ...r Sichtfluge in der fur IFR Fiuge Nacht zusatzlich zusatzlich Variometer VSI ein zweiter Kunstlicher Horizon Fahrtmesser am attitude gyro am G1000 PFD und G1000 PFD oder Backupinstrurnent Backupinstru...

Page 395: ...tZ I Flughandbuch Dok 6 01 05 Rev 3 fur Sichtfluge in der Nacht zusatzlich Posilionslichter Zusammenstol warnlichtanlage anti collision lights ACL Landescheinwerfer lnstrumenten beleuchtung Flutlicht...

Page 396: ...maB Mandatory Service Bulletin DAI MSB 04 045 ausgerustet sein Software System 010 00370 Manifest 006 B0093 006 B0172 006 B0190 006 B0193 006 B0203 006 B0223 006 B0224 006 B0319 006 B0328 006 B0329 00...

Page 397: ...erden 3 Die IFR Navigation mit dem G1000 GPS Empfiinger auf Langstrecken uber Meeren und im Endanflug ist nur dann erlaubt wenn der Pilot die Aktualitiit der Datenbasis oder die Obereinstimmung aller...

Page 398: ...usgerustet sein und dieselbe mur funktionstllchtig sein e Die VNAV Informalionen durfen nur als Zusatzinformationen verwendet werden Die Verwendung der VNAV Informationen fUr lnstrumentenanflug verfah...

Page 399: ...S auf MANUAL gesetzt werden VVenn die CDI Quelle gewechselt wird wahrend der Autopilot sich im NAV Modus befindet dann wird der Laterai Modus des Autopiloten auf den ROLL ATTITUDE Modus geandert und d...

Page 400: ...asis fOr das Gelande Hindernisse und Flugplatzgelande des G1000 Systems umfaBI die folgenden Gebiete 1 Die Daten fUr das Gelande umfassen den Bereich von 75 Nord bis 60 SOd Ober alle Langengrade 2 Die...

Page 401: ...G I000 ausgestatteten Flugzeuge tle ben kein Annunciator Panel Alle lnformationen werden auf den Displays des Garmin G1000 Systems angezeigt Die Anzeigen unterscheiden sich gegenOber denen die im Hau...

Page 402: ...reicht die Motorleistung so weit wie moglich reduzieren und die Fluggeschwindigkeit erhohen wahrend des Reisefluges Motorleistung reduzieren Fluggeschwindigkeit erhOhen OberprOfen ob die KOhlmitteltem...

Page 403: ...ri iltemperatur befindet sich im oberen roten Bereich zu hoch I ubcr 140 oc die Anzeige des Oldrucks OIL PRES kontrollieren wenn der 0 druck zu niedrig ist Motorieistung reduzieren mit weiterem Olverl...

Page 404: ...S angezeigt Motorleistung reduzieren mit weiterem Olverlust und Motorschaden rechnen Auf eine Notlandung entsprechend den im Hauptteil des Flughandbuchs angegebenen Verfahren vorbereiten 3 8 5 GBOX TE...

Page 405: ...Verbrauch von elektrischer Energie zu hoch ist Mogliche Grunde dafOr sind Ein Fehler in der Verkabelung oder der elektrischen AusrOstung 1 Elektrische AusrOstung ausschalten so weit notwendig und mog...

Page 406: ...des Motors unbedingt notwendig ist benotigt elektrische Energie Es wird empfohlen alle nicht benotigten elektrischen Verbraucher auszuschalten und so bald wie moglich zu landen Auf einen Motorschaden...

Page 407: ...ahren beschrieben wird wobei die STARTER Warnung des G1000 beim Auftreten des Fehlers stetig angezeigt wird 3 8 10 DOOR OPEN DOOR OPEN Vordere und oder hintere Kabinenhaube n ist sind nicht geschlosse...

Page 408: ...em zeigt keine GPS Oaten zur Unterstutzung der Navigation an Die G1000 VORIILS Empfanger oder andere alternative Navigationsmethoden zur Navigation verwenden 3 9 3 ATTITUDE FAIL ATTITUDE FAIL Das Anze...

Page 409: ...L ALTITUDE FAIL Das Anzeigesystem empfiingt keine Hohcndaten vom Flugdatenrechner ein rotes X markiert die Hohenmesseranzeige des G1000 als ungultig Es ist der Backup Hohenmesser zu verwenden 3 9 6 VE...

Page 410: ...vom AHRS ein rotes X markiert die Flugrichtungsanzeige des G1000 als ungOitig Es is der Backup Kompar zu ve Wenden 3 9 8 WARN WARN RAIM Positionswarnung der Balken zur Darstellung der Navigationsabwei...

Page 411: ...o Bedienteil DRUCKEN Position OUT ANMERKUNG muss die DISPLAY BACKUP Taste am Audio Bedienteil gedrOcki werden Nach DrOcken der DiSPLAY BACKUP Taste bleibt das System im umgekehrten Modus auch wenn das...

Page 412: ...ers gesetzt werden 1 Zur Navigation sind der Backup Kiinstliche Horizon der Backup Kompar l und Flugkarten zu verwenden 2 Kurs mit Hilfe des digitalen Fensters festlegen 3 10 4 AUSFALL DES FLUGDATENRE...

Page 413: ...torleistung auf Basis der Stellung des Leistungshebels des MotorP ngP riiw r hP s unrl rlP r FluggP sr hwindigkeit wahlen 2 Andere Anzeigen beobachten um den Zustand des Motors einzuschatzen 3 Verwend...

Page 414: ...Vor Warnung angezeigt wird is sie als tatsachlich eingetretene Situation zu behandeln Es is den Verfahren im Hauptteil des Handbuchs zu folgen 2 Wenn ein Display einen abnormalen Zustand anzeigt aber...

Page 415: ...Abflugsverfahren im Flugplan des G 1000 progralT iTiiert rnuss cHeses ge Oscht verden bevor eln neues Abflugsverfahren in den Flugplan geladen wird Bei Nichtbeachten ki innen fehlerhafte CDI Angaben V...

Page 416: ...ei Nichtbeachten kiinnen fehlerhafte CDI Angaben Verlust der GPS Navigalionsdaten und weitere Anzeige abweichungen entstehen ANMERKUNG Wenn Anzeigeabweichungen nach der Bearbeitung des Flugplanes am G...

Page 417: ...ext in wemer Farbe Gluhkerzen des Motors sind in Betrieb Kraftstofftransfer vom Zusatz zum Haupttank ist im Gange 4A 4 4 PFD MFD GIA FAN FAIL PFD FAN FAIL Der Lufter fUr das PFD ist aul1er Betrieb MFD...

Page 418: ...HL RPM im Hauptteil des FH8 48 8 2 HIGH ODER LOW COOLANT TEMPERATURE Vorgangsweise entsprechend 48 2 2 KUHLMITTELTEMPERATUR CT im Hauptteil des FH8 48 8 3 HIGH ODER LOW OIL TEMPERATURE Vorgangsweise e...

Page 419: ...RIE8ETEMPERATUR GT im Hauptteil des FH8 48 8 6 HIGH ODER LOW FUEL TEMPERATURE Vorgangsweise entsprechend 18 2 6 KP AFTSTOFFTEMPERATUR FUEL TEMP im Hauptteil des FH8 48 8 7 HIGH ODER LOW VOLTAGE Vorgan...

Page 420: ...kunden Dauer Fehler in der Motorsteuereinheit ECU A oder ECU A befindet sich im FADEC Test wahrend des Checks Vor dem Start Eine ECU A FAIL Vorwarnung am 81000 System is gleichbedeutend mit einer ECU...

Page 421: ...nge der Fehler auftritt 46 9 4 L FUEL LOW L FUEL LOW Die Kraftstoffmenge im Haupttank ist gering Eine L FUEL LOW Vorwarnung am G1000 System ist gleichbedeutend mit der LOW FUEL Vorwarnung die am Annun...

Page 422: ...ird 48 9 7 PITOT FAIL I PITOT HT OFF PITOT FAIL Die Pitotrohrheizung ist fehlerhaft PITOT HT OFF Pitotrohrheizung is ausgeschaltet OFF Eine PITOT FAIL Vorwarnung am G1 000 System is gleichbedeutend mi...

Page 423: ...nger oder mit einem anderen 11 K zugelassenem System zu kontrollieren lbl Endanflug Wenn die INTEG RAlM not available Vorwarnung wahrend des Endanfluges auftritt wird die GPS gestlitzte Navigation bis...

Page 424: ...00 IFR 6 MASSE UNO SCHWERPUNKT Nach dem Aus oder Einbau des Garmin G1000 Systems mussen die Anderungen der Leermasse und des Leermassen Schwerpunktes des Flugzeugs im Kapitel 6 des Flughandbuches eing...

Page 425: ...L lr VI VI V I IIVUVII 7 ECU TEST Taster 20 8 ECU SWAP Schalter 21 9 ENGINE MASTER 22 10 Drehschalter fOr lnstrumenten 23 beleuchtung und Flutlicht 11 Lichtschalter 24 Dok 6 01 05 Rev 3 01 Jun 2008 Sc...

Page 426: ...ng der elektrischen Sicherungen verwendet werden sind im Abschnitt 1 5 BEZEICHNUNGEN UNO ABKURZUNGEN erlautert ANMERKUNG Die Abbildung auf der vorhergehenden Seite zeigt die typische Anordung der Ausr...

Page 427: ...RUMENTE Die Motorinstrumente werden am Garmin G1000 Multifunktionsdisplay MFD angezeigt Siehe auch 7 14 3 MULTIFUNKTIONSDISPLAY MFD Standardseite Motor wenn die SYSTEM Taste gedruckt wird wenn die FUE...

Page 428: ...Die angezeigten Werte werden auf Grund der zuletzt vom Piloten eingegebenen Kraftstoffmenge und der aktuellen Kraftstoffverbrauchsdaten errechnet Darum durfen diese errechneten Flugdauer und Reichwei...

Page 429: ...oben zur altesten Meldung unten gereiht Am unteren rechten Rand der Anzeige befindet sich der MSG Message soft key Dieser MSG soft key beinhaltet zwei Funktionen im Rahmen des CAS 1 Das Drllcken der M...

Page 430: ...kOnftig Gelb Korrekturmar nahmen erfordern Weir Weir Grun Niedrigste Erganzung A32 Garmin G1000 IFR Al ustlsche Warnung Signalton Warnung der ohne Unter brechung wieder holt wird bis er von der Besatz...

Page 431: ...aten und Alarmierungsdaten fUr den Piloten Das PFD kann auch zur Flugplanung verwendet werden Das MFD zeigt Motor Karten und Geliindeinformationen an und dient auch der Flugplanung Das Audiobedienteil...

Page 432: ...RNAV Anfluge Dies beinhaltet RNAV Anfluge die als RNAV GPS eingetragen sind vorausgesetzt die GPS Daten sind gOitig s Das System erfullt die Anspruche nach RNP5 Airspace BRNAV gema AC 90 96 und in Ob...

Page 433: ...m Kompa angezeigt der volle Ausschlag entspricht einem standard rate turn Die folgenden Anzeigen werden am PFD dargestellt im Uhrzeigersinn von rechts oben Funkgerate Lautstarke und Rauschunterdruckun...

Page 434: ...uf dem PFD Eine Warnung wird von einem sich standig wiederholenden Signalton begleitet wahrend eine Vorwarnung mit einem einmaligen Signalton angekundigt wird Das Bestatigen des Alarms beendet das Bli...

Page 435: ...UP Taste am Audiobedienteil In dieser Betriebsart bleiben alle Alarmfunktionen aufrecht es sind aber keine Karteninformationen verfugbar 7 14 3 DAS MULTIFUNKTIONSDISPLAY MULTI FUNCTION DISPLAY MFDl Da...

Page 436: ...ence System AHRS verwendet GPS Geschwindigkeitsdaten Flugdaten und die Veranderungen des magnetischen Feldes um Nick und Rollbewegungen Schiebeflug und Flugrichtung zu errechnen Der Betrieb ist auch b...

Page 437: ...den Displays des G1000 Systems sind mit einer speziellen Antireflexbeschichtung ausgerustet die gegenuber Oien Wachsen und Scheuermitteln sehr empfindlich ist REINIGUNGSMITTEL DIE AMMONIAK ENTHALTEN Z...

Page 438: ...ng Anderungsmitteilungen Unterschrift 6 01 01 6 01 05 9 Feb 2006 OAM 40 284 DA 40 OAM 40 247 DA 40 D Vertreter der DAI Design Organisation T Krassnitzer Stempel Genehmigungsdatum 25 Mai 2007 Diese in...

Page 439: ...0 D FHB 0 1 ERFASSUNG DER BERICHTIGUNGEN Rev AnlaB Nr 11 I DA40 ein rbeitet 11 I I I I Dok Nr 6 01 01 Revision 1 10 Apr 2007 Dok Nr 6 01 05 OAM40 284 OAM40 247 ErgElnzung S4 ELT ME 406 und ME 406 ACE...

Page 440: ...S4 7 9 S4 8 7 9 S4 9 9 S4 10 9 S4 11 8 9 S4 11 Dok Nr 6 01 01 OAM 40 284 Revision 1 10 Apr 2007 Dok Nr 6 01 05 OAM 40 247 Ergiinzung 54 ELT ME 406 und ME 406 ACE Datum 10 Apr 2007 10 Apr 2007 10 Apr 2...

Page 441: ...9 S4 4 3 NOTVERFAHREN 9 84 4 4A NORMALE BETRIEBSVERFAHREN 9 84 6 48 ABNORMAL 3CTRIEBSVERFAHREN 9 84 6 5 LEISTUNGEN 9 S4 6 6 MASSE UND SCHWERPUNKT 9 84 6 7 BESCHREIBUNG DES FLUGZEUGES UND SEINER SYSTEM...

Page 442: ...ssen ubersetzt In jedem Fall ist die Originalversion in englischer Sprache mal geblich 2 BETRIEBSGRENZEN Es ergeben sich keine Anderungen des Kapitels 2 des Flughandbuches 3 NOTVERFAHREN Vor einer Not...

Page 443: ...wenn die LED schon blink s Wenn das Funkgerat funktioniert und es sicher bedient werden kann keine Bedrohung durch Feuer oder Explosion das Funkgerat einschalten und 121 50 MHz wahlen Wenn der ELT geh...

Page 444: ...in der ON Position befindet mul l er auf die ARM Position geschaltet werden und es mul l kontrolliert werden ob der ELT nicht mehr sendet 4A NORMALE BETRIEBSVERFAHREN Es ergeben sich keine Anderungen...

Page 445: ...h manuell uber den Hauptschalter auf dem Notsender oder mit dem auf der rechten Seite des lnstrumentenbretts der DA 40 bzw der DA 40 D eingebauten Schaiter aktiviert werden LED Indicator Remote Switch...

Page 446: ...andercode I D Code Ein Vorteil des 406 025 MHz Senders is dar er eine genauere Positionsangabe erzeugt typischerweise 1 bis 2 Kilometer verglichen mit 15 bis 20 Kilometer der 121 5 MHz Sender Der ELT...

Page 447: ...inter dem Ringspant installiert ist Bei starken Verzogerungen der Vorwartsbewegung des Flugzeuges in Langsrichtung lost ein Beschleunigungsmesser g Schalter aus und aktiviert den ELT Solange der ELT i...

Page 448: ...ndungen oder in starker Turbulenz kann es vorkommen dal der ELT selbststandig ausliist Dann muf der ELT durch Umschalten des Schalters am lnstrumentenbrett von der ARM Position in die ON Position und...

Page 449: ...nd Frequenz 121 50 MHz einstellen Squelch ausschalten Den Schalter am lnstrumentenbrett auf ON stellen auf 3 Piepser im Funkgeriit warten was ungefiihr 1 Sekunde dauert OberprOfen daB die LED blink Da...

Page 450: ...dyne TAS600 Series Traffic Advisory System when it has been installed in accordance with Diamond Maintenance GmbH EASA Minor Change Approval EASA A C 08966 The information contained in this document s...

Page 451: ...ng only The TAS600 Series Traffic Advisory System does not detect aircraft without operating transponder Limitations The following pilots handbooks must be referred to for operating instructions and m...

Page 452: ...nd Balance Refer to the latest weight and balance report part of the basic flight manual Description and Operation of the Airplane and its Systems The Avidyne TAS600 Series Traffic Advisory System is...

Page 453: ...attached to the EASA approved Airplane Flight Manual when the TAE 125 02 114 engine has been installed in accordance with EASA STC 10036328 The information contained in this supplement supersedes or a...

Page 454: ...This page intentionally left blank...

Page 455: ...w specs 5a New section 5b new section 6 Equipment list updated 2 1 2 Correction 5a Diagram added 5b Diagram added Approved Date Endorsed Sept 01 EASASTC 2011 10036 28 March 16 c 2012 0 8 e g g i if 0...

Page 456: ...Teohnlfy MotorS Note Page iv Issue 2 AFM Supplement DA 40 D The parts of the text which changed are marked with a vertical line on the margin of the page Revision 1 Mar 2017...

Page 457: ...r 2017 6 2 0 Aug 2015 7 2 0 Aug 2015 8 2 0 Aug 2015 9 2 0 Aug 2015 APPROVAL The content of approved chapters is approved by EASA All other content is approved by TAE under the authority of EASA DOA No...

Page 458: ...NG PROCEDURES a non approved chapter CHAPTER 4b ABNORMAL OPERATING PROCEDURES a non approved chapter CHAPTER 5 PERFORMANCE a non approved chapter CHAPTER 6 WEIGHT AND BALANCE I EQUiPiviENT LIST a non...

Page 459: ..._ _ Technlfy Motors Page vi Issue 2 AFM Supplement DA 40 D This page is intentionally left blank Revision Aug 2015...

Page 460: ...is supplement consult the basic EASA approved Airplane Flight Manual 1 2 CERTIFICATION BASIS The certification basis for the TAE 125 02 114 engine installation is CS 23 dated November 14 2003 1 5 DEFI...

Page 461: ..._ Technlfy Motors Page 1 2 Issue 2 AFM Supplement DA 40 D This page intentionally left blank Revision Aug 2015...

Page 462: ...t1 kW 155 HP at 2300 RPM Max recommended cruise power 85 e 0 Pressure Min oil pressure 1 2 bar Min oil pressure at Take off power 2 3 bar Min oil pressure in flight 2 3 bar Max oil pressure 6 0 bar M...

Page 463: ...ion at a ratio of 50 50 Radiator Protection BASF Glysantin Protect Plus G48 Mobil Antifreeze Extra G48 ESSO Antifreeze Extra G48 Comma Xstream Green Concentrate G48 Zerex Glysantin G48 CAUTION CAUTION...

Page 464: ...rized personnel o Maximum restart altitude 14000 ft 2 5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the tables below Oil temp C below 32 32 to...

Page 465: ...al instrument panel versions 2 9 APPROVED MANEUVRES Refer to basic AFM CAUTION 2 14 FUEL Intentionally initiating negative G maneuvers is prohibited Approved fuel grades JET A 1 ASTM D 1655 JET A ASTM...

Page 466: ...or blends of Diesel Fuel with JET Fuel If there is uncertainty about which fuel is in the tank it must be assumed that it is Diesel 2 16 OTHER LIMITATIONS Fuel Temperature The fuel temperature limitat...

Page 467: ...otors CHAPTER 3 EMERGENCY PROCEDURES The emergency procedures included in this chapter supersede the procedures in the basic AFM For emergency procedures not included in this chapter refer to basic AF...

Page 468: ...peed for windmilling is 120 KIAS Higher airspeeds may result in fJfUfJeller uver Sf Jeed Restarting the engine with windmilling propeller is possible at airspeeds between 70 and 110 KIAS and altitudes...

Page 469: ...ide configuration carry out emergency landing Refer to basic AFM Engine restart following an engine fire should only be attempted if it is unlikely that a safe emergency landing can be made lt must be...

Page 470: ...d altitudes below 14000 ft 1 Airspeed for best glide angle 1 3 KIAS 11o0 kg 25351b 68 KIAS 1000 kg 2205 lb 60 KIAS 850 kg 18741b 2 ENGINE MASTER OFF 3 Power lever IDLE 4 Emergency fuel valve check NOR...

Page 471: ...ON see 3 2 4 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER of this supplement A loss of altitude of at least 1000 ft 300 meters must be expected If it is not possible to start the engine adopt gli...

Page 472: ..._ I Technlfy Motors Page 3 6 Issue 2 AFM Supplement DA 40 D This page intentionally left blank Revision Aug 2015...

Page 473: ...stallation Flight Mass 980 kg 1000 kg 1150 kg 2160 lb 2205 lb 2535 lb Airspeed for rotation Take off run VR 54 KIAS 55 KIAS 59 KIAS Flaps T 0 Airspeed for take off climb Vx 59 KIAS 60 KIAS 66 KIAS Fla...

Page 474: ...Technlfy Motors Page 4A 2 Issue 2 AFM Supplement DA 40 D This page intentionally left blank Revision Aug 2015...

Page 475: ...AFM Supplement DA 40 D I Technlty Motors CHAPTER 48 ABNORMAL OPERATING PROCEDURES For abnormal operating procedures refer to basic AFM Page 48 1 Issue 2 Revision Aug 2015...

Page 476: ..._ I Technlfy W Motora Page 48 2 Issue 2 AFM Supplement DA 40 D This page intentionally left blank Revision Aug 2015...

Page 477: ...e CHAPTER S a PERFORMANCE This chapter applies to aircraft with propeller MTV 6 A 187 129 The correct designation can be found on the blades The chapter not relevant to the respective propeller can be...

Page 478: ...1 I i i I I i I I lj l j i I I I I I I I I I I I I Y I i I I I I I I I I I I I i I I I I i i i i i i I l I I i i I i i I i f i I g I OOl Oif OlO s t _ 1 o m eo I C 1 N N I i I I i I I I I I I f I i i...

Page 479: ...0 C o C o C o C 0 0 ft m m m m m m m m SL 316 510 340 551 366 594 393 639 1000 334 539 360 582 387 628 416 675 2000 353 570 381 616 410 664 440 715 3000 374 604 403 652 434 703 466 756 4000 396 639 42...

Page 480: ...ft ft SL 1037 1673 1116 1808 1201 1949 1289 2097 1000 1096 1768 1181 1910 1270 2060 1365 2215 2000 1158 1870 1250 2021 J345 2179 1444 2346 3000 1227 1982 1322 2139 1424 2307 1529 2480 4000 1299 2097...

Page 481: ...o o o 8 o 8 ll 0 0 0 0 ft m m m m m m m m SL 220 355 237 383 255 413 274 444 1000 232 375 250 405 269 436 289 470 2000 246 397 265 428 285 462 306 497 3000 260 420 280 453 302 489 324 526 4000 275 44...

Page 482: ...ft ft ft ft ft SL 722 1165 778 1257 837 1355 899 1457 1000 761 1230 820 1329 883 1430 948 1542 2000 807 1303 869 1404 935 1516 1004 1631 3000 853 1378 919 1486 991 1604 1063 1726 4000 902 1457 974 15...

Page 483: ...C 0 0 C 0 g C 0 g C 0 0 ft m m m m m m m m SL 208 336 225 363 242 392 260 421 1000 220 356 237 384 256 414 274 446 2000 233 376 251 406 270 438 290 471 3000 247 398 266 430 286 464 307 499 4000 261 4...

Page 484: ...ft ft ft ft SL 682 1102 738 1191 794 1286 853 1381 1000 722 1168 778 1260 840 1358 899 1463 2000 764 1234 824 1332 886 1437 951 1545 3000 810 1306 873 1411 938 1522 1007 1637 4000 856 1385 922 1493 99...

Page 485: ...d for initial climb 66 KIAS Power MAX RATE OF CLIMB feet per minute Pres Alt Temperature C F ft ISA ISA 10 C ISA 20 C ISA 30 C ISA 18 F ISA 36 F ISA 54oF SL 646 630 614 598 1000 645 629 613 597 2000 6...

Page 486: ...r MAX I I Temperature C F ft ISA ISA 10 C ISA 20 c ISA 30 c ISA 18 F ISA 36 F ISA 54 F SL 815 785 754 723 1000 810 779 748 717 2000 804 773 742 711 3000 798 766 735 704 4000 792 760 729 697 r vvvv fO...

Page 487: ...e Temperature C F ft ISA ISA 10 C ISA 20 C ISA 30 C ISA 18 F ISA 36 F ISA 54 F SL 1023 989 955 921 1000 1018 983 949 915 2000 1012 978 944 909 3000 1006 972 938 903 4000 1001 966 932 897 5000 995 960...

Page 488: ...1emperature C F ft ISA ISA 10 C ISA 20 C ISA 30 C ISA 18 F ISA 36 F ISA 54 F SL 1055 1020 986 952 1000 1050 1015 980 946 2000 1044 1009 975 940 3000 1039 1004 969 934 I 998 963 i 4000 1033 J I l 5000...

Page 489: ...US gal usable fuel 2 Endurance time of this table is reduced by the time for startup and taxi time fuel and distance to climb and 45 min reserve 3 The range data of this table take into account the di...

Page 490: ...140 33 6 8 9 320 2 3 135 29 6 7 8 363 2 7 129 I 2b 8 I 6 8 I 412 I 3 2 I 122 22 1 5 8 470 3 9 114 18 6 4 9 538 4 7 104 1b J 4 0 6 14 5 9 143 33 6 8 9 323 2 3 137 29 6 7 8 365 2 7 131 25 8 6 8 415 3 2...

Page 491: ...2 1 5 8 12000 60 125 18 6 4 9 12000 50 113 15 3 4 0 14000 80 145 25 8 6 8 14000 70 137 22 1 5 8 14000 60 127 18 6 4 9 14000 50 115 15 3 4 0 16000 80 148 25 8 6 8 16000 70 139 22 1 5 8 16000 60 129 18...

Page 492: ...abie fuei 2 Endurance time of this table is reduced by the time for startup and laxi lime ruel e mu ui lance to climb and 45 min reserve 3 The range data of this table take into account the distance t...

Page 493: ...0 133 25 8 6 8 4000 70 126 22 1 5 8 4000 60 117 18 6 4 9 4000 50 107 15 3 4 0 6000 100 148 33 6 8 9 6000 90 142 29 6 7 8 6000 80 135 25 8 6 8 6000 70 128 22 1 5 8 6000 60 119 18 6 4 9 6000 50 109 15 3...

Page 494: ...90 150 29 6 7 8 585 12000 80 143 25 8 6 8 653 12000 70 134 22 1 5 8 730 12000 60 125 18 6 4 9 820 12000 50 113 15 3 4 0 918 I 14000 80 145 25 8 6 8 658 14000 70 137 22 1 5 8 735 14000 60 127 18 6 4 9...

Page 495: ...AFM Supplement DA 40 D 5 3 15 Approved Noise Data I Technlfy Motors With TAE 125 02 114 engine and Muffler LA50 Installed ICAO Annex 16 Chapter X 69 6 dB A Page 5 a 19 Issue 2 Revision 1 Mar 2017...

Page 496: ...CHAPTER 5 b PERFORMANCE This chapter applies to aircraft with propeller MTV 6 A 190 69 The correct designation can be found on the blades The chapter not relevant to the respective iJIUiJellt r GCIII...

Page 497: ...1 0 a 1 0 i i i i I i I j I i I y_ i i i i _j i I I i i i i i I i I i i I i I i I i i I i I I i I i I i I i i I u apnmllf l 1 se t e 0 0 0 0 0 0 O QMo DCOI rJ M 0 0 W 1 N N N I I I I I Figure 5 b 1 En...

Page 498: ...418 Flaps T 0 Power MAX Runway dry level paved I a 1 s VI c 0 E lt m m m m m 522 343 552 363 619 i 38 i 407 656 432 695 458 571 362 605 605 383 640 641 679 406 i 6 719 430 720 456 762 763 484 808 6000...

Page 499: ...1019 1694 1088 1810 1190 1984 2000 1009 1679 1078 1793 1152 1916 1261 2102 3000 1068 1776 1141 1898 1220 2030 1336 2227 4000 1131 1881 1209 2010 1293 2151 1416 2361 5000 1198 1992 1281 2130 1371 2280...

Page 500: ...0 ft m m m m m m m m m m SL 217 361 232 385 247 412 255 425 286 477 1000 230 382 245 408 262 436 269 449 303 506 2000 243 404 259 431 277 461 285 476 321 535 3000 257 428 275 457 294 488 302 504 340 5...

Page 501: ...37 859 1429 884 1474 2000 797 1325 851 1415 909 1513 936 1560 3000 843 1402 901 1498 963 1602 991 1652 4000 893 1484 954 1587 1021 1698 1050 1751 5000 945 1572 1011 1681 1082 1800 1113 1856 6000 1002...

Page 502: ...L m _ Wml W TIL Jml W rnL__ mj SL 182 302 194 322 207 344 213 355 239 399 1000 192 319 205 341 219 364 225 376 253 422 2000 203 338 217 361 232 385 238 398 268 448 3000 215 357 230 382 245 408 253 421...

Page 503: ...118 718 1194 739 1232 2000 666 1108 711 1183 760 1264 782 1304 3000 705 1172 753 1252 805 1339 828 1381 4000 746 1241 797 1326 853 1419 878 1463 5000 790 1314 845 1405 904 1504 930 1551 6000 837 1392...

Page 504: ...laps T 0 Power MAX I I 111 11 I Pres Alt Temperature C F ft ISA ISA 1o c ISA 20 C ISA 3o c ISA 35 C ISA 18 F ISA 36 F ISA 54 F ISA 63 F SL 769 766 758 705 661 1000 766 764 756 702 659 2000 764 761 753...

Page 505: ...SA 20 C ISA 30 C ISA 18 F ISA 36 F ISA 54 F SL 918 913 901 829 1000 914 909 896 824 2000 909 904 891 819 3000 905 899 887 814 4000 900 894 882 809 5000 895 889 877 804 6000 890 884 871 798 7000 885 87...

Page 506: ...SA 30 C ISA 35 C ISA 18 F ISA 36 F ISA 54 F ISA 63 F SL 1048 1043 1030 952 888 1000 1044 1038 1026 947 884 2000 1039 1034 1021 942 879 3000 1035 1029 1016 938 874 4000 1030 1025 1012 933 869 5000 1026...

Page 507: ...54 F SL 1153 1148 1135 1051 1000 1149 1144 1131 1047 2000 1144 1140 1126 1042 3000 1140 1135 1122 1038 4000 1136 1131 1117 1033 5000 1131 1126 1112 1028 6000 1127 1121 1108 1023 7000 1122 1117 1103 10...

Page 508: ...usable fuel 2 ErHiHFaftc e trme ef this t able s r eooced by the Hr r le fol startup and taxi time fuel and distance to climb and 45 min reserve 3 The range data of this table take into account the di...

Page 509: ...rs 143 33 6 8 9 326 2 3 137 29 6 7 8 370 2 7 131 25 8 6 8 420 3 2 124 22 1 5 8 480 3 9 117 18 6 4 9 552 4 7 107 15 3 4 0 635 5 9 145 33 6 8 9 330 2 2 140 29 6 7 8 374 2 6 133 25 8 6 8 424 3 1 126 22 1...

Page 510: ...8 22 1 5 8 12000 60 129 18 6 4 9 12000 50 117 15 3 4 0 1Annn An 1 9 t R l ll i i 14000 70 141 22 1 5 8 14000 60 131 18 6 4 9 14000 50 118 15 3 4 0 16000 80 152 25 8 6 8 16000 70 143 22 1 5 8 16000 60...

Page 511: ...usable fuel 2 Endurance time of this table is reduced by the time for startup and taxi time fuel and distance to climb and 45 min reserve 3 The range data of this table take into account the distance...

Page 512: ...0 70 129 22 1 22 1 4000 60 120 18 6 18 6 4000 50 111 15 3 15 3 6000 100 151 33 6 33 6 uuuu IV l to J L J U e v v 6000 80 138 25 8 25 8 6000 70 131 22 1 22 1 6000 60 123 18 6 18 6 6000 50 112 15 3 15 3...

Page 513: ...153 29 6 29 6 610 12000 80 146 25 8 25 8 681 12000 70 138 22 1 22 1 767 12000 60 129 18 6 18 6 866 12000 50 117 15 3 15 3 972 14000 80 149 25 8 25 8 691 14000 70 141 22 1 22 1 777 14000 60 131 18 6 18...

Page 514: ...AFM Supplement DA 40 D 5 3 15 Approved Noise Data I Technlty W Motors With TAE 125 02 114 engine and Muffler LA50 Installed ICAO Annex 16 Chapter X 70 5 dB A Page 5 b 19 Issue 2 Revision 1 Mar 2017...

Page 515: ...4 vx xx Mapping G14CxxxDA40 Clutch Mapping G14DxxxDA40 Dual Mass Fly Wheel EXHAUST SYSTEM Muffler LA50 ENGINE INDICATING Compact TAE CED 125 Engine Display PROPELLER Propeller MTV 6 N187 129 MTV 6 N19...

Page 516: ...S AND BALANCE REPORT After installation of the TAE 125 02 114 engine installation the empty mass and empty mass moment must be established Refer to the basic AFM and basic AMM for the DAI DA 40 D Reco...

Page 517: ...14 engine has the same general characterics as the TAE 125 02 99 engine except for the continuous and maximum power Max power 114 kW 155 DIN HP at 2300 RPM ISA SL Max cont power 114 kW 155 DIN HP at 2...

Page 518: ...125 02 114 engine but connected to the aircraft liquid cooling system Refer to Figure 7 1 for a schematic TAE 125 02 114 engine Figure 7 1 Liquid Cooling System 7 9 8 OIL SYSTEMS Bleed Screw I The eng...

Page 519: ...the basic DAI Airplane Maintenance Manual only as set forth therein 8 2 AIRPLANE INSPECTION INTERVALS Refer to supplement to the Airplane Maintenance Manual AMM 50 02 and the basic DAI Airplane Maint...

Page 520: ...I Technlfy Motors Page 8 2 Issue 2 AFM Supplement DA 40 D This page intentionally left blank Revision Aug 2015...

Page 521: ...TAE 125 02 114 engine istallation For the affected supplements a supplement has been created which adds or supersedes the affected supplements as described 9 2 LIST OF SUPPLEMENTS Sup Title No 1 Garmi...

Page 522: ...I Technlfy Motors Page 9 2 Issue 2 AFM Supplement DA 40 D This page intentionally left blank Revision Aug 2015...

Page 523: ...TAE 125 02 114 engine has been installed in accordance with EASA STC 10036328 The information contained in this supplement supersedes or adds to the EASA approved Airplane Flight Manual and supplement...

Page 524: ...lement 1 Garmin G1000 VFR Approved Description Date Endorsed New Issue Aug 15 EASASTC Change of Ownership 2015 10036328 Rev 3 Remark The parts of the text vJhich changed are marked Jith a vertical lin...

Page 525: ...2 Limitations No change The engine limitations and engine instrument marking applicable to the TAE 125 02 99 engine are valid for the TAE 125 02 114 Refer to supplement A31 of the basic AFM 3 Emergenc...

Page 526: ...ent 1 Garmin G1000 VFR 7 Description of the airplane and its systems No change Refer to supplement A31 of the basic AFM 8 Airplane Handling Care and Maintenance No change Refer to supplement A31 of th...

Page 527: ...AE 125 02 114 engine has been installed in accordance with EASA STC 10036328 The information contained in this supplement supersedes or adds to the EASA approved Airplane Flight Manual and supplement...

Page 528: ...lement 2 Garmin G1000 IFR Approved Description Date Endorsed New Issue Aug 15 EASA STC Change of Ownership 2015 10036328 Rev 3 Remark The parts of the text vvhich changed are marked vJith a vertical l...

Page 529: ...Limitations No change The engine limitations and engine instrument marking applicable to the TAE 125 02 99 engine are valid for the TAE 125 02 114 Refer to supplement A32 of the basic AFM 3 Emergency...

Page 530: ...nt 2 Garmin G1000 IFR 7 Description of the airplane and its systems No change Refer to supplement A32 of the basic AFM 8 Airplane Handling Care and Maintenance No change Refertp supplement A32 of the...