Diamond DA 40 Flight Manual Download Page 124

Page: 124 / 300

Normal Operating

Procedures

DA 40 AFM

Page 4A - 8

Rev. 8

01-Dec-2010

Doc. # 6.01.01-E

5. Fuselage, Right Side:

a) Fuselage skin . . . . . . . . . . . . . . . . . . . . . . . . visual inspection

b) Window . . . . . . . . . . . . . . . . . . . . . . . . . . . . . visual inspection

c) Canopy, right side . . . . . . . . . . . . . . . . . . . . . visual inspection

d) Autopilot static source (if OÄM 40-267

installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . check for blockage

6. Right Wing:

a) Flap and linkage . . . . . . . . . . . . . . . . . . . . . . visual inspection

b) Flap hinges and safety pin . . . . . . . . . . . . . . . visual inspection

c) Aileron and linkage . . . . . . . . . . . . . . . . . . . . visual inspection

d) Aileron hinges and safety pin . . . . . . . . . . . . visual inspection

e) Foreign objects in aileron paddle . . . . . . . . . . visual inspection

f) Wing tip . . . . . . . . . . . . . . . . . . . . . . . . . . . . . visual inspection

g) Position light, strobe light (ACL) . . . . . . . . . . visual inspection

h) Mooring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . check, clear

i) Entire wing surface . . . . . . . . . . . . . . . . . . . . visual inspection

j) 2 stall strips on wing . . . . . . . . . . . . . . . . . . . visual inspection

k) Tank air outlet in lower surface . . . . . . . . . . . visual inspection

l) Tank filler . . . . . . . . . . . . . . . . . . . . . . . . . . . . visual check, fuel quantity

must agree with indicator

m) Openings on lower surface . . . . . . . . . . . . . . check for traces of fuel (if

tank is full, fuel may spill

over through the tank vent)

n) Tank drain . . . . . . . . . . . . . . . . . . . . . . . . . . . drain off a small quantity,

check for water and

sediment

o) Step . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . visual inspection

CONTINUED

Summary of Contents for DA 40

Page 1: ......

Page 2: ...lot must familiarize himself with the complete contents of this Airplane Flight Manual In the event that you have obtained your DIAMOND STAR second hand please let us know your address so that we can supply you with the publications necessary for the safe operation of your airplane This document is protected by copyright All associated rights in particular those of translation reprinting radio tra...

Page 3: ... the left hand side of the revised page with the revision number and date appearing at the bottom of the page NOTE If pages are revised which contain information valid for your particular serial number modification level of the airplane weighing data Equipment Inventory List of Supplements then this information must be transferred to the new pages in hand writing Temporary Revisions if applicable ...

Page 4: ... 19 Dec 2000 approved by Ing Andreas Winkler for ACG 25 Jan 2001 1 1 16 2 2 1 2 7 thru 2 9 2 13 thru 2 19 3 3 7 3 8 3 19 3 20 3 25 3 26 4A 4A 3 thru 4A 8 4A 14 4A 15 4B 4B 4 thru 4B 6 6 6 1 6 2 6 12 thru 6 14 7 7 1 7 8 7 14 7 28 thru 7 38 3 OÄM 40 064 Night VFR OÄM 40 069 control surf gust lock OÄM 40 070 tow bar corrections 0 0 2 thru 0 7 05 Feb 2001 approved by Ing Andreas Winkler for ACG 02 Jul...

Page 5: ...061 KAP 140 autopilot OÄM 40 073 SlickSTART OÄM 40 081 door lock OÄM 40 085 KX 155A as COM 1 OÄM s 40 092 thru 40 094 Mikrotechna ASI altimeter VSI MÄM 40 039 a VM 1000 MÄM 40 048 RH emerg window corrections 0 0 1 thru 0 8 09 Sep 2001 approved by Ing Andreas Winkler for ACG 09 Sep 2001 1 1 2 1 5 1 14 2 2 1 2 16 2 22 2 23 2 24 3 3 13 3 18 3 22 3 23 3 24 3 31 3 36 4A 4A 8 4A 10 4A 22 4A 23 4A 26 4B ...

Page 6: ...M 40 047 069 075 078 096 099 123e 133 141 174 175 OÄM 40 063 b 071 c 077 078 080 083 a 090 091 097 098 103 104 105 106 111 112 114 115 117 117 a 119 120 121 122 124 127 128 138 140 154 165 167 168 179 181 183 185 186 190 198 200 206 237 250 a RÄM 40 014 corrections double sided layout all all except cover page 15 Jul 2006 Revision No 7 of the AFM Doc No 6 01 01 E is approved under the authority of...

Page 7: ...ed Signature Doc 6 01 01 E Rev 8 01 Dec 2010 Page 0 5 8 MÄM 40 176 227 a 313 344 360 a 378 401 415 428 446 OÄM 40 217 251 253 b 258 267 277 a 279 283 a 284 289 326 327 corrections all all except cover page 01 Dec 2010 Revision No 8 of the AFM Doc No 6 01 01 E is approved under the authority of DOA No EASA 21J 052 ...

Page 8: ...1 Dec 2010 0 11 01 Dec 2010 0 12 01 Dec 2010 0 13 01 Dec 2010 0 14 01 Dec 2010 Ch Page Date 1 1 1 01 Dec 2010 1 2 01 Dec 2010 1 3 01 Dec 2010 1 4 01 Dec 2010 1 5 01 Dec 2010 1 6 01 Dec 2010 1 7 01 Dec 2010 1 8 01 Dec 2010 1 9 01 Dec 2010 1 10 01 Dec 2010 1 11 01 Dec 2010 1 12 01 Dec 2010 1 13 01 Dec 2010 1 14 01 Dec 2010 1 15 01 Dec 2010 1 16 01 Dec 2010 1 17 01 Dec 2010 1 18 01 Dec 2010 1 19 01 D...

Page 9: ...r 2 12 01 Dec 2010 appr 2 13 01 Dec 2010 appr 2 14 01 Dec 2010 appr 2 15 01 Dec 2010 appr 2 16 01 Dec 2010 appr 2 17 01 Dec 2010 appr 2 18 01 Dec 2010 appr 2 19 01 Dec 2010 appr 2 20 01 Dec 2010 appr 2 21 01 Dec 2010 appr 2 22 01 Dec 2010 appr 2 23 01 Dec 2010 appr 2 24 01 Dec 2010 appr 2 25 01 Dec 2010 appr 2 26 01 Dec 2010 appr 2 27 01 Dec 2010 Ch Page Date 2 appr 2 28 01 Dec 2010 appr 2 29 01 D...

Page 10: ... Dec 2010 3 15 01 Dec 2010 3 16 01 Dec 2010 3 17 01 Dec 2010 3 18 01 Dec 2010 3 19 01 Dec 2010 3 20 01 Dec 2010 3 21 01 Dec 2010 3 22 01 Dec 2010 3 23 01 Dec 2010 3 24 01 Dec 2010 3 25 01 Dec 2010 3 26 01 Dec 2010 3 27 01 Dec 2010 3 28 01 Dec 2010 Ch Page Date 3 3 29 01 Dec 2010 3 30 01 Dec 2010 3 31 01 Dec 2010 3 32 01 Dec 2010 3 33 01 Dec 2010 3 34 01 Dec 2010 3 35 01 Dec 2010 3 36 01 Dec 2010 3...

Page 11: ...10 4A 14 01 Dec 2010 4A 15 01 Dec 2010 4A 16 01 Dec 2010 4A 17 01 Dec 2010 4A 18 01 Dec 2010 4A 19 01 Dec 2010 4A 20 01 Dec 2010 4A 21 01 Dec 2010 4A 22 01 Dec 2010 4A 23 01 Dec 2010 4A 24 01 Dec 2010 4A 25 01 Dec 2010 4A 26 01 Dec 2010 4A 27 01 Dec 2010 Ch Page Date 4A 4A 28 01 Dec 2010 4A 29 01 Dec 2010 4A 30 01 Dec 2010 4A 31 01 Dec 2010 4A 32 01 Dec 2010 4A 33 01 Dec 2010 4A 34 01 Dec 2010 4A ...

Page 12: ...0 4B 11 01 Dec 2010 4B 12 01 Dec 2010 Ch Page Date 5 5 1 01 Dec 2010 5 2 01 Dec 2010 5 3 01 Dec 2010 5 4 01 Dec 2010 5 5 01 Dec 2010 5 6 01 Dec 2010 5 7 01 Dec 2010 5 8 01 Dec 2010 5 9 01 Dec 2010 5 10 01 Dec 2010 5 11 01 Dec 2010 5 12 01 Dec 2010 5 13 01 Dec 2010 5 14 01 Dec 2010 5 15 01 Dec 2010 5 16 01 Dec 2010 5 17 01 Dec 2010 5 18 01 Dec 2010 5 19 01 Dec 2010 5 20 01 Dec 2010 5 21 01 Dec 2010...

Page 13: ... Dec 2010 6 10 01 Dec 2010 6 11 01 Dec 2010 6 12 01 Dec 2010 6 13 01 Dec 2010 6 14 01 Dec 2010 6 15 01 Dec 2010 6 16 01 Dec 2010 6 17 01 Dec 2010 6 18 01 Dec 2010 6 19 01 Dec 2010 6 20 01 Dec 2010 6 21 01 Dec 2010 6 22 01 Dec 2010 6 23 01 Dec 2010 6 24 01 Dec 2010 6 25 01 Dec 2010 6 26 01 Dec 2010 6 27 01 Dec 2010 Ch Page Date 6 6 28 01 Dec 2010 6 29 01 Dec 2010 6 30 01 Dec 2010 6 31 01 Dec 2010 6...

Page 14: ... Dec 2010 7 21 01 Dec 2010 7 22 01 Dec 2010 7 23 01 Dec 2010 7 24 01 Dec 2010 7 25 01 Dec 2010 7 26 01 Dec 2010 7 27 01 Dec 2010 Ch Page Date 7 7 28 01 Dec 2010 7 29 01 Dec 2010 7 30 01 Dec 2010 7 31 01 Dec 2010 7 32 01 Dec 2010 7 33 01 Dec 2010 7 34 01 Dec 2010 7 35 01 Dec 2010 7 36 01 Dec 2010 7 37 01 Dec 2010 7 38 01 Dec 2010 7 39 01 Dec 2010 7 40 01 Dec 2010 7 41 01 Dec 2010 7 42 01 Dec 2010 7...

Page 15: ...58 01 Dec 2010 Ch Page Date 8 8 1 01 Dec 2010 8 2 01 Dec 2010 8 3 01 Dec 2010 8 4 01 Dec 2010 8 5 01 Dec 2010 8 6 01 Dec 2010 8 7 01 Dec 2010 8 8 01 Dec 2010 8 9 01 Dec 2010 8 10 01 Dec 2010 8 11 01 Dec 2010 8 12 01 Dec 2010 Ch Page Date 9 9 1 01 Dec 2010 9 2 01 Dec 2010 9 3 01 Dec 2010 9 4 01 Dec 2010 9 5 01 Dec 2010 9 6 01 Dec 2010 ...

Page 16: ...ROCEDURES a non approved chapter 3 NORMAL OPERATING PROCEDURES a non approved chapter 4A ABNORMAL OPERATING PROCEDURES a non approved chapter 4B PERFORMANCE a non approved chapter 5 MASS AND BALANCE EQUIPMENT LIST a non approved chapter 6 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS a non approved chapter 7 AIRPLANE HANDLING CARE AND MAINTENANCE a non approved chapter 8 SUPPLEMENTS 9 ...

Page 17: ...CAUTIONS AND NOTES 1 5 1 4 DIMENSIONS 1 6 1 5 DEFINITIONS AND ABBREVIATIONS 1 8 1 6 UNITS OF MEASUREMENT 1 18 1 6 1 CONVERSION FACTORS 1 18 1 6 2 CONVERSION CHART LITERS US GALLONS 1 20 1 7 THREE VIEW DRAWING 1 21 1 8 SOURCE DOCUMENTATION 1 22 1 8 1 ENGINE 1 22 1 8 2 PROPELLER 1 23 1 8 3 ENGINE INSTRUMENTS 1 23 1 8 4 IGNITION CONTROL UNIT 1 24 ...

Page 18: ...number Therefore some of the information contained in this manual is applicable depending on the respective equipment and modification level The exact equipment of your serial number is recorded in the Equipment Inventory in Section 6 5 The modification level is recorded in the following table as far as necessary for this manual Modification Source Installed RH Emergency Window MÄM 40 048 9 yes 9 ...

Page 19: ...Adjustment OÄM 40 251 9 yes 9 no CO Monitor OÄM 40 253 9 yes 9 no Autopilot Static Source OÄM 40 267 9 yes 9 no Tall Main Landing Gear OÄM 40 283 9 yes 9 no ELT Artex ME 406 ACE OÄM 40 284 9 yes 9 no MT P 860 23 Governor OÄM 40 289 9 yes 9 no Emergency Axe OÄM 40 326 9 yes 9 no For installation of the Baggage Tray the Baggage Extension must be installed This Airplane Flight Manual must be kept on ...

Page 20: ... degree of reliability which is required by the certification basis Nevertheless an 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 constitute a risk It is therefore highly recommended to select flight times and flight routes such that this risk is minimized...

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

Page 22: ... Area appr 13 54 m appr 145 7 sq ft Mean aerodynamic chord MAC appr 1 121 m appr 3 ft 8 1 in Aspect ratio appr 10 53 Dihedral appr 5 Leading edge sweep appr 1 Aileron Area total left right appr 0 654 m appr 7 0 sq ft Wing Flaps Area total left right appr 1 56 m appr 16 8 sq ft Horizontal Tail Area appr 2 34 m2 appr 25 2 sq ft Elevator area appr 0 665 m appr 7 2 sq ft Angle of incidence appr 3 0 re...

Page 23: ...ea appr 0 47 m appr 5 1 sq ft Landing Gear Track appr 2 97 m appr 9 ft 9 in Wheelbase appr 1 68 m appr 5 ft 6 in Nose wheel 5 00 5 6 PR 120 mph Main wheel a 6 00 6 6 PR 120 mph in combination with any MLG strut b 15 x 6 0 6 6 PR 160 mph only in combination with the thin MÄM 40 123 e or the tall OÄM 40 283 MLG strut ...

Page 24: ...ManeuveringSpeed Full or abrupt controlsurfacemovementisnotpermissible above this speed vFE Max Flaps Extended Speed This speed must not be exceeded with the given flap setting vNE Never Exceed Speed in smooth air This speed must not be exceeded in any operation vNO Maximum Structural Cruising Speed This speed may be exceeded only in smooth air and then only with caution vS Stalling Speed or the m...

Page 25: ...n of the measuring point above MSL and the actual atmospheric pressure at the measuring point Indicated Pressure Altitude Altitude reading with altimeter set to 1013 25 hPa 29 92 inHg Pressure Altitude Altitude above MSL indicated by a barometric altimeter which is set to 1013 25 hPa 29 92 inHg The Pressure Altitude is the Indicated Pressure Altitude corrected for installation and instrument error...

Page 26: ...ulations are measured Moment Arm The horizontal distance from the Datum Plane to the Center of Gravity of a component Moment The mass of a component multiplied by its moment arm CG Center of Gravity also called center of mass Imaginary point in which the airplane mass is assumed to be concentrated for mass and balance calculations Its distance from the Datum Plane is equal to the Center of Gravity...

Page 27: ...ence between take off mass and empty mass Maximum Take off Mass The maximum permissible mass for take off Maximum Landing Mass The highest mass for landing conditions at the maximum descent velocity This velocity was used in the strength calculations to determine the landing gear loads during a particularly hard landing e Engine Take off Power Maximum permissible engine output power for take off M...

Page 28: ...irection Finder AUDIO Audio Panel Intercom AUTOPILOT Autopilot AVIONIC BUS Avionic Bus DME Distance Measuring Equipment ESSENTIAL AVIONIC Essential Avionic Bus GPS Global Positioning System GPS2 Global Positioning System 2 NAV COM1 Navigation Communication 1 NAV COM2 Navigation Communication 2 STRIKE Strike Finder XPDR Transponder ENGINE IGNITION Ignition INST 1 Engine Instrument VM 1000 START Sta...

Page 29: ...o FAN OAT Fan Outside Air Temperature Indicator FLAPS Flaps FUEL PUMP Fuel Pump HORIZON Artificial Horizon Attitude Gyro PITOT HEAT Pitot Heating System T B Turn Bank Indicator ELECTRICAL ALT Alternator ALT CONT Alternator Control ALT PROT Alternator Protection BATT Battery ESSENTIAL TIE Bus Interconnection MAIN TIE Bus Interconnection MASTER CONTROL Master Control avionic master switch essential ...

Page 30: ...tor Control ALT PROT Alternator Protection AV BUS Avionic Bus DG Directional Gyro FAN OAT Fan Outside Air Temperature Indicator FUEL PUMP Fuel Pump IGNITION Ignition INST Instrument Lights MAIN TIE Bus Interconnection POSITION Position Lights START Starter STROBE Strobe Lights Anti Collision Lights ACLs T B Turn Bank Indicator TAXI MAP Taxi Light Map Light ...

Page 31: ...2 Communication Navigation 2 DME Distance Measuring Equipment GPS2 Global Positioning System 2 GPS NAV2 Global Positioning System Navigation 2 STRIKE Strike Finder Wx 500 Stormscope TAS Traffic Advisory System ESS AV BUS Essential Avionic Bus COM1 Communication 1 COM NAV1 Communication Navigation 1 GPS1 Global Positioning System 1 GPS NAV1 Global Positioning System Navigation 1 XPDR Transponder ...

Page 32: ...nic Bus ESS TIE Bus Interconnection FLAPS Flaps FLOOD Flood Light HORIZON Artificial Horizon Attitude Gyro INST 1 Engine Instrument VM 1000 LANDING Landing Light MASTER CONTROL Master Control avionic master switch essential bus switch essential avionics relay bus interconnection relay avionics master relay PITOT Pitot Heating System ...

Page 33: ...gn Change Advisory OÄM Optional Design Change Advisory i Miscellaneous ACG Austro Control GmbH formerly BAZ 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 Procedure PCA Primary Certification Authority ...

Page 34: ... gal l 0 9464 qts Speed km h kilometers per hour m s meters per second kts knots mph miles per hour fpm feet per minute km h 1 852 kts km h 1 609 mph m s x 196 85 fpm Speed of rotation RPM revolutions per minute Mass kg kilograms lb pounds kg x 2 2046 lb Force weight N newtons lbf pounds force N x 0 2248 lbf Pressure hPa hecto pascals mbar millibars bar bars inHg inches of mercury psi pounds per s...

Page 35: ...al Dimension SI Units US Units Conversion Doc 6 01 01 E Rev 8 01 Dec 2010 Page 1 19 Intensity of electric current A ampères Electric charge battery capacity Ah ampère hours Electric potential V volts Time sec seconds ...

Page 36: ... 6 2 7 6 15 4 0 4 15 1 20 5 3 6 22 7 25 6 6 8 30 3 30 7 9 10 37 9 35 9 2 12 45 4 40 10 6 14 53 0 45 11 9 16 60 6 50 13 2 18 68 1 60 15 9 20 75 7 70 18 5 22 83 3 80 21 1 24 90 9 90 23 8 26 98 4 100 26 4 28 106 0 110 29 1 30 113 6 120 31 7 32 121 1 130 34 3 34 128 7 140 37 0 36 136 3 150 39 6 38 143 8 160 42 3 40 151 4 170 44 9 45 170 3 180 47 6 50 189 3 ...

Page 37: ...DA 40 AFM General Doc 6 01 01 E Rev 8 01 Dec 2010 Page 1 21 1 7 THREE VIEW DRAWING ...

Page 38: ...espective publisher However only the information given in the Airplane Flight Manual is valid 1 8 1 ENGINE Address Textron Lycoming 652 Oliver Street WILLIAMSPORT PA 17701 USA Phone 1 570 323 6181 Webpage www lycoming textron com Documents a Textron Lycoming Operator s Manual Aircraft Engines 60297 12 Part No b Service Bulletins SB Service Instructions SI e g SI 1014 SI 1070 Service Letters SL e g...

Page 39: ...propeller com Webpage www mt propeller de Documents E 124 Operation and Installation Manual Hydraulically controlled variable pitch propeller MTV 5 6 9 11 12 14 15 16 21 22 25 1 8 3 ENGINE INSTRUMENTS Address VISION MICROSYSTEMS INC ADVANCED ELECTRONIC INSTRUMENTATION 4071 Hannegan Road Suite T BELLINGHAM WA 98226 USA Phone 1 360 714 8203 Documents 5010002 REV F VM 1000 Owner s Manual ...

Page 40: ...CONTROL UNIT The electronic ignition control unit LASAR is optional equipment Address UNISON Industries 7575 Baymeadows Way JACKSONVILLE FL 32256 USA Phone 1 904 739 4066 Webpage www unisonindustries com Documents L 1502 LASAR Installation Operation and Troubleshooting Manual ...

Page 41: ...HTS 2 9 2 7 MASS WEIGHT 2 11 2 8 CENTER OF GRAVITY 2 13 2 9 APPROVED MANEUVERS 2 14 2 10 MANEUVERING LOAD FACTORS 2 16 2 11 OPERATING ALTITUDE 2 17 2 12 FLIGHT CREW 2 17 2 13 KINDS OF OPERATION 2 18 2 14 FUEL 2 22 2 15 LIMITATION PLACARDS 2 24 2 16 OTHER LIMITATIONS 2 32 2 16 1 TEMPERATURE 2 32 2 16 2 BATTERY CHARGE 2 32 2 16 3 EMERGENCY SWITCH 2 32 2 16 4 OPERATION TIME OF ELECTRICAL EQUIPMENT 2 ...

Page 42: ... Flight Manual includes operating limitations instrument markings and placards necessary for safe operation of the airplane its power plant standard systems and standard equipment The limitations included in this Chapter are approved WARNING Operation of the airplane outside of the approved operating limitations is not permissible ...

Page 43: ...S above 1036 kg 2284 lb up to 1200 kg 2646 lb 94 KIAS 780 kg 1720 lb up to 1036 kg 2284 lb Do not make full or abrupt control surface movement above this speed vFE Max flaps ex tended speed LDG 91 KIAS T O 108 KIAS Do not exceed these speeds with the given flap setting vNO vC Max structural cruising speed 129 KIAS Do not exceed this speed except in smooth air and then only with caution vNE Never e...

Page 44: ... 3 AIRSPEED INDICATOR MARKINGS Marking IAS Significance White arc 49 KIAS 91 KIAS Operating range with flaps fully extended Green arc 52 KIAS 129 KIAS Normal operating range Yellow arc 129 KIAS 178 KIAS Caution range Only in smooth air Red line 178 KIAS Maximum speed for all operations vNE ...

Page 45: ... Max continuous RPM 2400 RPM d Manifold pressure limitations Maximum FULL throttle e Oil pressure Minimum IDLE 25 PSI 1 72 bar Maximum 98 PSI 6 76 bar Normal operating range 55 to 95 PSI 3 8 to 6 55 bar f Oil quantity Minimum 4 qts Maximum 8 qts g Oil temperature Maximum 245 F 118 C h Fuel pressure Minimum 14 PSI 0 97 bar Maximum 35 PSI 2 4 bar i Cylinder head temperature Maximum 500 F 260 C j Pro...

Page 46: ...of a cylinder airplane engine oil should be used which meets SAEJ1966 MIL L 6082 Standard straight mineral type The viscosity should be selected according to the recommendation given in the following table OAT at Ground Level During the first 50 hours SAEJ1966 MIL L 6082 Mineral Oil After 50 hours SAEJ1899 MIL L 22851 Ashless Dispersant Oil All temperatures SAE 15 W50 SAE 20 W50 above 80 F above 2...

Page 47: ...wer prohibited range Yellow arc bar caution range Green arc bar normal operating range Yellow arc bar caution range Red arc bar upper prohibited range Manifold pressure 13 30 inHg RPM 500 2400 RPM 2400 2700 RPM above 2700 RPM Oil temp 149 230 F 231 245 F above 245 F Cylinder head temp 150 475 F 476 500 F above 500 F Oil pressure below 25 PSI 25 55 PSI 56 95 PSI 96 97 PSI above 97 PSI Fuel pressure...

Page 48: ...nge Page 2 8 Rev 8 01 Dec 2010 EASA approved Doc 6 01 01 E Fuel quantity Standard Tank 0 US gal 0 15 US gal1 0 17 US gal2 Fuel quantity Long Range Tank 0 US gal 0 16 US gal 0 9 US gal3 1 up to and including serial number 40 054 2 serial number 40 055 and subsequent 3 numerical indication of the additional auxiliary fuel quantity for a total fuel quantity on one side in the range between 16 and 25 ...

Page 49: ...n the annunciator panel Color and Significance of the Warning Lights Red Warning Lights Red Cause Variant DAI Variant White Wire Meaning OIL PR OIL PRESS Oil pressure Oil pressure below 25 PSI FUEL PR FUEL PRESS Fuel pressure Fuel pressure below 14 PSI ALT ALTERNATOR Alternator Generator Alternator failure START START Starter Operation of starter or failure of the starter motor to disengage from t...

Page 50: ...n the right tank less than 3 US gal 1 US gal LOW FUEL Fuel quantity 1st caution fuel quantity in one tank less than 3 US gal 1 US gal 2nd caution fuel quantity in second tank less than 3 US gal 1 US gal VOLT LOW VOLTS Voltage On board voltage below 24 V PITOT PITOT Pitot heating Pitot heating not switched ON or fault in the Pitot heating system Color and Significance of the Status Light White Stat...

Page 51: ...ent 30 kg 66 lb Max load in baggage tube 5 kg 11 lb Max load in extended baggage compartment OÄM 40 163 Max load in forward part 45 kg 100 lb Max load in aft part 18 kg 40 lb Max total load forward aft 45 kg 100 lb Max surface load for baggage compartments 75 kg m 15 3 lb ft WARNING Exceeding the mass limits will lead to an overstressing of the airplane as well as to a degradation of flight charac...

Page 52: ...ed Doc 6 01 01 E NOTE In some countries the beginning of a flight is defined by starting the engine In those countries a maximum ramp mass 4 kg 9 lb above the maximum take off mass is approved At the time of lift off the maximum permitted take off mass must not be exceeded ...

Page 53: ...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 for flight conditions must lie between the following limits Most forward CG 2 40 m 94 5 in aft of DP from 780 kg to 980 kg 1720 lb to 2161 lb 2 46 m 96 9 in aft of DP at 1150 kg 2535 lb linear variation between these values If MÄM 40 227 is carried out 2 40 ...

Page 54: ...in accordance with JAR 23 Approved Maneuvers a Normal 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 more than 60 is attained CAUTION Aerobatics spinning and flight maneuvers with more than 60 of bank are not permitted in the Normal Category ...

Page 55: ...hich an angle of bank of not more than 90 is attained 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 directional gyro is affected by the maneuvers approved under item 3 if the bank angle exceeds 60 Such maneuvers may therefore only be flown when the above menti...

Page 56: ... of maximum structural load factors Normal Category at vA at vNE With Flaps in T O or LDG Position Positive 3 8 3 8 2 0 Negative 1 52 0 Utility Category at vA at vNE With Flaps in T O or LDG Position Positive 4 4 4 4 2 0 Negative 1 76 1 WARNING Exceeding the maximum load factors will lead to an overstressing of the airplane ...

Page 57: ...g altitude is 16 400 ft 5 000 m The maximum approved operating altitude for US registered airplanes is 14 000 ft MSL unless an approved supplemental oxygen system is installed 2 12 FLIGHT CREW Minimum crew number 1 one person Maximum number of occupants Normal Category 4 four persons Utility Category 2 two persons both of whom must sit in front ...

Page 58: ...t night flights according to Visual Flight Rules NVFR With the appropriate equipment flights according to Instrument Flight Rules IFR Flights into known or forecast icing conditions are prohibited Flights into known thunderstorms are prohibited Minimum Operational Equipment Serviceable ThefollowingtableliststheminimumserviceableequipmentrequiredbyJAR 23 Additional minimum equipment for the intende...

Page 59: ...ss Vertical speed indicator VSI Attitude gyro artificial horizon Turn bank indicator Directional gyro OAT indicator Chronometer with indication of hours minutes and seconds VHF radio COM with speaker and microphone VOR receiver Transponder XPDR Mode A and Mode C 1 headset Second VHF radio COM VOR LOC GP receiver Marker beacon receiver Engine Instru ments Fuel indicators Integrated engine instrumen...

Page 60: ...2010 EASA approved Doc 6 01 01 E Lighting Position lights Strobe lights anti collision lights Landing light Instrument lighting Flood light Flashlight Other Opera tional Minimum Equip ment Stall warning system Fuel quantity measuring device see 7 10 Safety belts for each occupied seat Airplane flight manual Pitot heating system Alternate static valve Essential bus Emergency battery ...

Page 61: ...R operation it is not sufficient to install the required equipment The retrofit must be carried out in accordance with the requirements of the manufacturer see Service Bulletins and the national AirworthinessAuthority Anyadditionalequipment equipment which is not listed in the Equipment List in Section 6 5 must also be approved for the intended kind of operation by the national Airworthiness Autho...

Page 62: ...tandard Tank Total fuel quantity 2 x 20 6 US gal app 2 x 78 liter Unusable fuel 2 x 0 5 US gal app 2 x 2 liter Max indicated fuel quantity up to and incl serial no 40 054 15 US gal app 57 liter per tank serial no 40 055 subsequent 17 US gal app 64 liter per tank Max permissible difference between right and left tank 10 US gal app 38 liter ...

Page 63: ...r Max indicated fuel quantity 16 US gal app 61 liter per tank Indicated quantity auxiliary fuel tank 0 to 9 US gal app 0 to 34 liter per tank Max permissible difference between right and left tank 8 US gal app 30 liter CAUTION If a fuel indicator shows 16 US gal and the aux fuel indicator reads 0 US gal on the same side then 19 US gal must be assumed for the calculation of the difference between r...

Page 64: ...kg above 2161 up to 2535 lb vA 94 KIAS 780 to 980 kg 1720 to 2161 lb This airplane may only be operated in accordance with the Airplane Flight Manual It can be operated in the Normal and Utility categories in non icing conditions Provided that national operational requirements are met and the appropriate equipment is installed this airplane is approved for the following kinds of operation day VFR ...

Page 65: ...ance with the Airplane Flight Manual It can be operated in the Normal and the Utility categories in non icing conditions Provided that national operational requirements are met and the 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 operational limitatio...

Page 66: ...d fuel quantity 17 US gal left and right tank max 10 US gal difference For use of max tank capacity see AFM Fuel qty indication 16 9 US gal max difference LH RH tank 8 US gal AUX FUEL QTY switch for LH RH auxiliary fuel quantity NOTE See AFM for more information on AUX FUEL Next to the Fuel Quantity Indication a Standard Tank Up to serial number 40 054 Serial number 40 055 and subsequent b Long Ra...

Page 67: ...perating Limitations Doc 6 01 01 E Rev 8 01 Dec 2010 EASA approved Page 2 27 On the Fuel Tank Selector a Standard Tank b Long Range Tank if installed Fu e l S e l e c t o r L EFT OF F 25 US gal 25 US gal 94 l 94 l ...

Page 68: ... Bus NOT for normal operation See AFM In the Cowling on the Door for the Oil Filler Neck OIL 1 qt 0 95 liters SAE 15W50 ashless dispersant aviation grade oil SAE Standard J 1899 or see AFM Chapter 2 VFR Min Max 4 8 qts IFR Min Max 6 8 qts Next to the Flap Selector Switch Next to the Essential Bus Switch if installed ...

Page 69: ...ations Doc 6 01 01 E Rev 8 01 Dec 2010 EASA approved Page 2 29 66 lbs 30 kg max In the Cockpit on the Left Fuselage Sidewall if alternate static valve is installed Next to the Baggage Compartment a Standard Baggage Compartment ...

Page 70: ...TMENT MAX 18 kg 40 lb ARM 4 54 m 178 7 FORWARD BAGGAGE COMPARTMENT MAX 45 kg 100 lb ARM 3 89 m 153 1 MAX BAGGAGE TOTAL 45 kg 100 lb MAX SURFACE LOAD 75 kg m 15 lb sq ft CAUTION OBSERVE WEIGHT AND BALANCE LIMITATIONS SEE AIRPLANE FLIGHT MANUAL CHAPTER 6 b Extended Baggage Compartment OÄM 40 163 if installed ...

Page 71: ... Rev 8 01 Dec 2010 EASA approved Page 2 31 Beside the Door Locking Device OÄM 40 081 if installed Above the NAV 2 CDI OÄM 40 206 if installed NAV No 2 not approved for precision approaches EMERGENCY EXIT The keylock must be unlocked during flight ...

Page 72: ...mpty battery is not permitted The use of an external power supply for engine starting with an empty airplane battery is not permitted if the subsequent flight is intended to be an IFR flight In this case the airplane battery must first be charged 2 16 3 EMERGENCY SWITCH IFR flights are not permitted when the seal on the emergency switch is broken 2 16 4 OPERATION TIME OF ELECTRICAL EQUIPMENT Follo...

Page 73: ...rplane is not permitted as it could lead to interference with the airplane s avionics Examples of undesirable items of equipment are Mobile telephones Remote radio controls Video screens employing CRTs MiniDisc recorders when in the record mode This list is not exhaustive The use of laptop computers including those with CD ROM drives CD and minidisc players in the replay mode cassette players and ...

Page 74: ...Operating Limitations DA 40 AFM Page 2 34 Rev 8 01 Dec 2010 EASA approved Doc 6 01 01 E Intentionally left blank ...

Page 75: ... 4 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER 3 17 3 2 5 DEFECTIVE ENGINE CONTROLS 3 18 3 2 6 RESTARTING THE ENGINE WITH STATIONARY PROPELLER 3 20 3 3 SMOKE AND FIRE 3 22 3 3 1 SMOKE AND FIRE ON THE GROUND 3 22 3 3 2 SMOKE AND FIRE DURING TAKE OFF 3 24 3 3 3 SMOKE AND FIRE IN FLIGHT 3 26 3 4 GLIDING 3 28 3 5 EMERGENCY LANDINGS 3 29 3 5 1 EMERGENCY LANDING WITH ENGINE OFF 3 29 3 5 2 LANDING W...

Page 76: ...S 3 34 3 7 1 ICING 3 34 3 7 2 FAILURES IN THE ELECTRICAL SYSTEM 3 35 3 7 3 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN 3 39 3 7 4 DOOR WARNING LIGHT ON 3 40 3 7 5 EMERGENCY EXIT 3 41 NOTE Procedures for uncritical system faults are given in Chapter 4B ABNORMAL OPERATING PROCEDURES ...

Page 77: ...is Airplane Flight Manual a thorough understanding of the airplane by the pilot is in addition to his knowledge and experience an essential factor in the solution of any problems which may arise WARNING In each emergency control over the flight attitude and the preparation of a possible emergency landing have priority over attempts to solve the current problem first fly the aircraft Prior to the f...

Page 78: ...00 kg 2205 lb 1150 kg 2535 lb 1200 kg 2646 lb Engine failure after take off Flaps T O 59 KIAS 66 KIAS 72 KIAS 74 KIAS Airspeed for best glide angle Flaps UP 60 KIAS 68 KIAS 73 KIAS 76 KIAS Emergency landing with engine off Flaps UP 60 KIAS 68 KIAS 73 KIAS 76 KIAS Flaps T O 59 KIAS 66 KIAS 72 KIAS 74 KIAS Flaps LDG 58 KIAS 63 KIAS 71 KIAS 73 KIAS ...

Page 79: ...e IDLE 2 Brakes as required 3 Engine switch off if considered necessary otherwise establish the cause of the problem and re establish engine performance CAUTION If the oil pressure is below the green sector the engine must be switched off immediately WARNING If the problem cannot be cleared the airplane must not be flown END OF CHECKLIST ...

Page 80: ...ed Sufficient Runway Length Available Land Straight Ahead 1 Throttle IDLE On the Ground 2 Brakes as required CAUTION If sufficient time is remaining the risk of fire in the event of a collision can be reduced as follows Fuel tank selector OFF Mixture control lever LEAN shut engine off Ignition switch OFF Master switch ALT BAT OFF CONTINUED ...

Page 81: ...height has not been reached then a straight ahead emergency landing should be carried out Turning back can be fatal If Time Allows 2 Fuel tank selector check selected tank 3 Electrical fuel pump check ON 4 Ignition switch check BOTH 5 Throttle check MAX PWR 6 RPM lever check HIGH RPM 7 Mixture control lever check RICH leaner above 5000 ft 8 Alternate Air OPEN WARNING If the problem does not clear ...

Page 82: ...ntinued if there is no other alternative 1 Airspeed 76 KIAS 1200 kg 2646 lb 73 KIAS 1150 kg 2535 lb 68 KIAS 1000 kg 2205 lb 60 KIAS 850 kg 1874 lb 2 Electrical fuel pump check ON 3 Fuel tank selector check selected tank 4 Engine instruments check 5 Throttle check 6 RPM lever check 7 Mixture control lever set for smooth running 8 Alternate Air OPEN 9 Ignition status light check only if the electron...

Page 83: ...nition control unit is installed if rough running is cleared by doing this the circuit breaker should remain open 12 Throttle RPM Mixture try various settings WARNING If the problem does not clear itself immediately and the engine is no longer producing sufficient power then an emergency landing should be carried out END OF CHECKLIST ...

Page 84: ...d cylinder head temperatures 2b If the oil pressure indication drops below the green sector while the oil or cylinder head temperature is rising or If the oil pressure warning light illuminates or flashes or If both of these occur together Reduce engine power to the minimum required Land as soon as possible Be prepared for engine failure and emergency landing 2c Oil pressure tending to zero combin...

Page 85: ...se is high it is probable that the fault lies in the oil temperature indication The airplane should be serviced A stable oil temperature indication of 26 F 3 C or 317 F 158 C suggests a failure of the oil temperature sensor If the cylinder head temperature or exhaust gas temperature is also high Check oil pressure If the oil pressure is low proceed as in 3 2 3 b LOSS OF OIL PRESSURE If the oil pre...

Page 86: ... setting enrich mixture if necessary 2 Check oil temperature If the oil temperature is also high Check oil pressure If the oil pressure is low proceed as in 3 2 3 b LOSS OF OIL PRESSURE If the oil pressure is in the green sector Reduce power if this produces no improvement land at the nearest appropriate airfield Be prepared for possible emergency landing END OF CHECKLIST ...

Page 87: ...PM should be regulated using the throttle Proceed as in 3 2 3 b LOSS OF OIL PRESSURE 3 If oil pressure is normal Pull RPM lever back and listen for an associated drop in RPM If the indication does not change in spite of an audible drop in RPM it is probable that the RPM indication is defective which should thus be ignored the airplane should be serviced If there is no audible drop in RPM it is pro...

Page 88: ... RPM If there is no audible rise in RPM it is probable that the governor system is defective In this case the RPM can be regulated within certain limits using the throttle Land at the nearest appropriate airfield Be prepared for possible emergency landing If the indication does not change in spite of an audible rise in RPM it is probable that the RPM indication is defective which should thus be ig...

Page 89: ...PRESSURE WITH THE ELECTRICAL FUEL PUMP SET TO ON If the fuel pressure is in the green sector or the fuel pressure warning light is not illuminated the likely cause is a defective fuel flow indication which should thus be ignored the airplane should be serviced Fuel flow data should be taken from the engine performance table in Chapter 5 3 Check fuel quantity A rapid reduction in fuel quantity conf...

Page 90: ... leak between the injection system and the injectors Land on the nearest suitable airfield If the fuel flow is in the green sector and the engine is running smoothly the likely cause is a defective fuel pressure indication which should thus be ignored the airplane should be serviced Monitor engine for power loss and rough operation that could indicate fuel starvation If the engine is no longer pro...

Page 91: ...jor engine failure the propeller will continue to windmill 1 Airspeed 80 KIAS 2 Fuel tank selector fullest tank 3 Ignition switch check BOTH 4 Mixture control lever check appropriate position 5 Electrical fuel pump check ON 6 Alternate air OPEN If Engine Does Not Start 7 Mixture control lever LEAN 8 Mixture control lever push forward slowly until engine starts NOTE If it is not possible to start t...

Page 92: ... reaction of the engine to a higher power setting A lean mixture can lead to engine roughness and a loss of power The landing approach must be planned accordingly WARNING Go aroundmaybecomeimpossiblewiththeremainingpower b Engine Shut Down 1 Parking brake set 2 Engine instruments check 3 Avionics master switch OFF 4 All electrical equipment OFF 5 Throttle IDLE 6 Ignition switch OFF 7 Master switch...

Page 93: ...ble to Continue Flight 1 Carry out emergency landing as in 3 5 1 EMERGENCY LANDING WITH ENGINE OFF END OF CHECKLIST Defective RPM Lever Control Cable a Sufficient Engine Power Available to Continue Flight 1 Approach nearest airfield control engine power with throttle 2 Perform normal landing WARNING Go aroundmaybecomeimpossiblewiththeremainingpower b No Sufficient Engine Power Available to Continu...

Page 94: ...r check 6 Fuel tank selector check 7 Electrical fuel pump check ON 8 Alternate air OPEN 9 Ignition switch START NOTE By increasing the airspeed above approximately 130 KIAS the propeller will begin to rotate and the engine can thus be started For this the Ignition switch should be set at BOTH see 3 2 4 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER An altitude loss of at least 1000 ft 300 meter ...

Page 95: ... 8 01 Dec 2010 Page 3 21 CAUTION Engine restart following an engine fire should only be attempted if it is unlikely that a safe emergency landing can be made It must be expected that engine restart is impossible after an engine fire END OF CHECKLIST ...

Page 96: ...OKE AND FIRE ON THE GROUND a Engine Fire When Starting on the Ground 1 Fuel tank selector OFF 2 Cabin heat OFF 3 Brakes apply After Standstill 4 Throttle MAX PWR 5 Master switch ALT BAT OFF When the Engine Has Stopped 6 Ignition switch OFF 7 Canopy open 8 Airplane evacuate immediately END OF CHECKLIST ...

Page 97: ...23 b Electrical Fire with Smoke on the Ground 1 Master switch ALT BAT OFF If the Engine is Running 2 Throttle IDLE 3 Mixture control lever LEAN shut off engine When the Engine Has Stopped 4 Ignition switch OFF 5 Canopy open 6 Airplane evacuate immediately END OF CHECKLIST ...

Page 98: ...D OF CHECKLIST b If Take Off Cannot Be Aborted 1 Cabin heat OFF 2 If possible fly along a short cut traffic circuit and land on the airfield WARNING If in the event of an engine problem occurring during take off the take off can no longer be aborted and a safe height has not been reached then a straight ahead emergency landing should be carried out Turning back can be fatal 3 Airspeed 74 KIAS 1200...

Page 99: ...h ALT BAT OFF 8 Emergency window s open if required 9 Carry out 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 allows it to partially open in order to improve ventilation The canopy will remain open in this position Flight characteristics will not be af...

Page 100: ... or landing site a Engine Fire in Flight 1 Cabin heat OFF 2 Select appropriate emergency landing field When it Seems Certain that the Landing Field Will Be Reached 3 Fuel tank selector OFF 4 Throttle MAX PWR 5 Electrical fuel pump OFF 6 Master switch ALT BAT ON 7 Emergency window s open if required 8 Carry out emergency landing with engine off CAUTION In case of extreme smoke development the front...

Page 101: ...nd electric equipment Also affected from this are if installed the attitude gyro artificial horizon and the directional gyro However by switching the Emergency switch ON only installed in the IFR model the emergency battery will supply power to the attitude gyro artificial horizon and the flood light CAUTION In case of extreme smoke development the front canopy may be unlatched during flight This ...

Page 102: ...8 8 i e for every 1000 ft 305 meter of altitude loss the maximum horizontal distance traveled in still air is 1 45 NM 2 68 km During this the propeller will continue to windmill With a stationary propeller the glide ratio is 10 3 this corresponds to a maximum horizontal distance of 1 70 NM 3 14 km for every 1000 ft altitude In consideration of a safe airspeed however this configuration may not be ...

Page 103: ...ort cut rectangular circuit On the downwind leg of the circuit the landing area should be inspected for obstacles from a suitable height The degree of offset at each part of the circuit will allow the wind speed and direction to be assessed 4 Airspeed 76 KIAS 1200 kg 2646 lb 73 KIAS 1150 kg 2535 lb 68 KIAS 1000 kg 2205 lb 60 KIAS 850 kg 1874 lb 5 If time allows advise ATC 6 Fuel tank selector OFF ...

Page 104: ... 2010 Doc 6 01 01 E CAUTION If sufficient time is remaining the risk of fire in the event of a collision with obstacles can be reduced as follows Ignition switch OFF Master switch ALT BAT OFF 9 Touchdown with the lowest possible airspeed END OF CHECKLIST ...

Page 105: ...ane at the edge of the runway that is located on the side of the intact tire so that changes in direction which must be expected during roll out due to the braking action of the defective tire can be corrected on the runway 3 Land with one wing low The wing on the side of the intact tire should be held low 4 Direction should be maintained using the rudder This should be supported by use of the bra...

Page 106: ...ass is recommended in order to reduce the landing run by virtue of 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 Fuel tank selector OFF Mixture control lever LEAN shut off engine Ignition switch OFF Master switch ALT BAT OFF END OF CHECKLIST ...

Page 107: ...imultaneously 1 Throttle IDLE 2 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 8 Return the airplane from a descending into a normal flight attitude In so doing do not exceed the never exceed speed vNE END OF CHECKLIST ...

Page 108: ...at ON 4 Air distributor lever up 5 RPM increase in order to prevent ice build up on the propeller blades 6 Alternate air OPEN 7 Emergency window s open if required CAUTION Ice build up increases the stalling speed If required for safety reasons engine speeds up to 2700 RPM are admissible without time limit 8 ATC advise if an emergency is expected CAUTION When the Pitot heating fails and the altern...

Page 109: ...al failure of the electrical system is extremely unlikely If nevertheless a total failure should occur all circuit breakers should be checked pulled and re set If this does not help Set Emergency switch to ON if installed When necessary use the flood light for lighting the instruments as well as levers and switches etc Set power based on lever positions and engine noise Prepare landing with flaps ...

Page 110: ...K proceed with step 2 2 Electrical equipment switch OFF all equipment which is not needed 3 Voltmeter check regularly CAUTION Those items of equipment which are not needed for the safe operation and secure landing of the airplane can be switched off with the Essential Bus switch if installed When the essential bus is switched ON only the following items of equipment are supplied with power NAV COM...

Page 111: ...acity is not sufficient to reach a suitable airfield an emergency battery is installed in the IFR model serving as an additional back up system for the attitude gyro artificial horizon and flood light This battery is switched on with the Emergency switch It lasts for 1 hour and 30 minutes when the flood light is switched on ii Alternator Failure on the Ground NOTE An alternator failure may also be...

Page 112: ... has started 1 Throttle IDLE 2 Mixture control lever LEAN shut off engine 3 Ignition switch OFF 4 Master switch ALT BAT OFF Terminate flight preparation END OF CHECKLIST d Overvoltage If a voltage in the upper red sector above 32 Volts is indicated 1 Essential bus ON if installed 2 Master switch ALT OFF WARNING Leave Master switch BAT ON 3 Equipment that is not needed in particular Pitot heating O...

Page 113: ...y be equipped with a CO detector optional equipment OÄM 40 253 If the visual alert annunciator illuminates in flight press the TEST RESET button If the alert continues with the remote light staying ON or a smell similar to exhaust gases is noticed in the cabin the following measures should be taken 1 Cabin heat OFF 2 Ventilation open 3 Emergency window s open 4 Forward canopy open CAUTION In case ...

Page 114: ... 4 Airspeed below 140 KIAS 5 Land at the next suitable airfield Rear Door Unlocked 4 Airspeed below 140 KIAS 5 Land at the next suitable airfield WARNING Do not try to lock the rear door in flight The safety latch may disengage and the door opens Usually this results in a separation of the door from the airplane NOTE If the rear door has been lost the airplane can be safely flown to the next suita...

Page 115: ... 2010 Page 3 41 3 7 5 EMERGENCY EXIT In case of a roll over of the airplane on ground it can be evacuated through the rear door For this purpose release the front hinge of the rear door The function is displayed on a placard next to the hinge END OF CHECKLIST ...

Page 116: ...Emergency Procedures DA 40 AFM Page 3 42 Rev 8 01 Dec 2010 Doc 6 01 01 E Intentionally left blank ...

Page 117: ... BEFORE STARTING ENGINE 4A 11 4A 3 3 STARTING ENGINE 4A 13 4A 3 4 BEFORE TAXIING 4A 19 4A 3 5 TAXIING 4A 20 4A 3 6 BEFORE TAKE OFF 4A 22 4A 3 7 TAKE OFF 4A 25 4A 3 8 CLIMB 4A 27 4A 3 9 CRUISE 4A 29 4A 3 10 MIXTURE ADJUSTMENT 4A 31 4A 3 11 DESCENT 4A 33 4A 3 12 LANDING APPROACH 4A 34 4A 3 13 GO AROUND 4A 36 4A 3 14 AFTER LANDING 4A 37 4A 3 15 ENGINE SHUT DOWN 4A 38 4A 3 16 POST FLIGHT INSPECTION 4A...

Page 118: ...R NORMAL OPERATING PROCEDURES Flight Mass Event 850 kg 1874 lb 1000 kg 2205 lb 1150 kg 2535 lb 1200 kg 2646 lb Airspeed for take off climb best rate of climb speed vY Flaps T O 54 KIAS 60 KIAS 66 KIAS 67 KIAS Airspeed for cruise climb Flaps UP 60 KIAS 68 KIAS 73 KIAS 76 KIAS Approach speed for normal landing Flaps LDG 58 KIAS 63 KIAS 71 KIAS 73 KIAS Minimum speed during touch go Flaps T O 54 KIAS ...

Page 119: ...ition key pulled out d Front canopy and rear door clean undamaged check locking mechanism function e All electrical equipment OFF f Circuit breakers set in if one has been pulled check reason g Engine control levers check condition freedom of movement and full travel of throttle RPM and mixture levers h Throttle IDLE i Mixture control lever LEAN j RPM lever HIGH RPM k Master switch BAT ON l Annunc...

Page 120: ...rried out the fuel quantity available for flight planning is the indicated amount Long Range Tank At an indication of 16 US gal the quantity of auxiliary fuel can be determined by switching the AUX FUEL QTY switch to the respective position LH or RH The auxiliary fuel quantity is added to the 16 US gal An auxiliary fuel quantity of less than 3 US gal cannot be indicated by the system In this case ...

Page 121: ... around check visual inspection CAUTION A visual inspection means examination for damage cracks delamination excessive play load transmission correct attachment and general condition Inadditioncontrolsurfaces should be checked for freedom of movement CAUTION In low ambient temperatures the airplane must be completely cleared of ice snow and similar accumulations For approved de icing fluids refer ...

Page 122: ...ne connection check for leaks h Slip marks visual inspection i Chocks remove 2 Left Wing a Entire wing surface visual inspection b Step visual inspection c Air intake on lower surface visual inspection d Openings on lower surface check for traces of fuel if tank is full fuel may spill over through the tank vent e Tank drain drain off a small quantity check for water and sediment f Stall warning ch...

Page 123: ...ection r Flap and linkage visual inspection s Flap hinges and safety pin visual inspection 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 OÄM 40 267 installed check for blockage 4 Empennage a Stabilizers and control surfaces visual inspection b Hinges vi...

Page 124: ...n hinges and safety pin visual inspection e Foreign objects in aileron paddle visual inspection f Wing tip visual inspection g Position light strobe light ACL visual inspection h Mooring check clear i Entire wing surface visual inspection j 2 stall strips on wing visual inspection k Tank air outlet in lower surface visual inspection l Tank filler visual check fuel quantity must agree with indicato...

Page 125: ... visual inspection g Brake line connection check for leaks h Slip marks visual inspection i Chocks remove 8 Front Fuselage a Oil level check dipstick min 4 qts for VFR operation min 6 qts for IFR operation b Cowling visual inspection c 3 air intakes clear d Propeller visual inspection blade shake max 3 mm 1 8 in angular play of blade max 2 WARNING Never move the propeller by hand while the ignitio...

Page 126: ...l inspection m Tow bar removed n Tire inflation pressure 2 0 bar 29 PSI check o Chocks remove p Exhaust visual inspection q Forward cabin air inlets if installed clear r Winter baffle for fresh air inlet if installed visual inspection WARNING The exhaust can cause burns when it is hot Underside s Antennas if fitted visual inspection t Gascolator drain off a small quantity of fuel check for water a...

Page 127: ...g the canopy ensure that there are no obstructions between the canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward pressure on the canopy may be required to ease handle operation 8 Front canopy Position 1 or 2 Cooling Gap 9 Canopy lock if installed unblocked key removed 10 Parking brake set 11 Flight controls ...

Page 128: ...led CAUTION When the essential bus is switched ON the battery will not be charged unless the essential tie relay bypass OÄM 40 126 is installed 21 Master switch BAT ON 22 Annunciator panel test see Section 7 11 23 Fuel tank selector on full tank WARNING Never move the propeller by hand while the ignition is switched on as it may result in serious personal injury Never try to start the engine by ha...

Page 129: ... control lever RICH for 3 5 sec then LEAN 5 Throttle 1 cm 0 4 in forward from IDLE measured from rear of slot WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds Aft...

Page 130: ...ly cold temperatures After a warm up period of approximately 2 to 5 minutes depending on the ambient temperature at 1500 RPM the engine is ready for take off if it accelerates smoothly and the oil pressure is normal and steady 6 Ignition switch START When Engine Fires 7 Mixture control lever rapidly move to RICH 8 Oil pressure green sector within 15 sec 9 Electrical fuel pump OFF WARNING If the oi...

Page 131: ...ot 4 Mixture control lever RICH for 1 3 sec then LEAN WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool o...

Page 132: ...o RICH 7 Oil pressure green sector within 15 sec WARNING If the oil pressure has not moved into the green sector within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 8 Electrical fuel pump OFF 9 Master switch ALT ON 10 Ammeter check 11 Fuel pressure check 14 PSI to 35 PSI 12 Annunciator panel check END OF CHECKLIST ...

Page 133: ... WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the engine let the starter cool off for half an hour 5 Ignition switch START 6 Throttl...

Page 134: ...rapidly move to RICH 8 Oil pressure green sector within 15 sec WARNING If the oil pressure has not moved into the green sector within 15 seconds after starting SWITCH OFF ENGINE and investigate problem 9 Master switch ALT ON 10 Ammeter check 11 Fuel pressure check 14 PSI to 35 PSI 12 Annunciator panel check END OF CHECKLIST ...

Page 135: ... increase RPM 7 Fuel tank selector change tanks confirm that engine also runs on other tank at least 1 minute at 1500 RPM 8 Pitot heating ON test function ammeter must show rise 9 Pitot heating OFF 10 Strobe lights ACLs check ON as required 11 Position lights landing and taxi lights ON as required CAUTION When taxiing at close range to other aircraft or during night flight in clouds fog or haze th...

Page 136: ...for correct indications CAUTION When taxiing on a poor surface select the lowest possible RPM to avoid damage to the propeller from stones or similar items CAUTION Following extended operation on the ground or at high ambient temperatures the following indications of fuel vapor lock may appear Arbitrary changes in idle RPM and fuel flow Slow reaction of the engine to operation of throttle Engine w...

Page 137: ...ts 2 Pull throttle back to IDLE to confirm smooth running 3 Set throttle to 1200 RPM and mixture for taxiing i e use mixture control lever to set the maximum RPM attainable 4 Immediately before the take off run set the mixture for take off apply full throttle and hold this position for 10 seconds NOTE Vapor lock can be avoided if the engine is run at speeds of 1800 RPM or more This results in lowe...

Page 138: ... check closed and locked 5 Front canopy closed and locked CAUTION When operating the canopy ensure that there are no obstructions in between the canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward pressure on the canopy may be required to ease handle operation 6 Door warning light DOOR or DOORS check OFF 7 Fue...

Page 139: ...ning of the engine or a loss of performance The mixture should be set for smooth running of the engine 13 Flaps check T O 14 Trim check T O 15 Flight controls free movement correct sense 16 Throttle 2000 RPM 17 RPM lever pull back until a drop of 250 to 500 RPM is reached HIGH RPM cycle 3 times 18 Magneto check L BOTH R BOTH Max RPM drop 175 RPM Max difference 50 RPM If the electronic ignition con...

Page 140: ...oubt the magneto check can be repeated with a leaner mixture in order to confirm a problem Even when running on only one magneto the engine should not run unduly roughly 19 Circuit breaker check in 20 Voltmeter check in green range 21 Throttle IDLE 22 Parking brake release 23 Alternate air check CLOSED 24 Landing light ON as required 25 Pitot heating ON as required END OF CHECKLIST ...

Page 141: ... that the take off can be aborted if necessary A rough engine sluggish RPM increase or failure to reach take off RPM 2680 20 RPM are reasons for aborting the take off If the engine oil is cold an oil pressure in the yellow sector is permissible 4 Elevator neutral 5 Rudder maintain direction NOTE In strong crosswinds steering can be augmented by use of the toe brakes It should be noted however that...

Page 142: ... Page 4A 26 Rev 8 01 Dec 2010 Doc 6 01 01 E 7 Airspeed 67 KIAS 1200 kg 2646 lb 66 KIAS 1150 kg 2535 lb 60 KIAS below 1000 kg 2205 lb Above a Safe Height 8 RPM lever 2400 RPM 9 Electrical fuel pump OFF 10 Landing light OFF END OF CHECKLIST ...

Page 143: ...850 kg 1874 lb 3 RPM lever 2400 RPM 4 Throttle MAX PWR 5 Mixture control lever RICH above 5000 ft hold EGT constant 6 Engine instruments in green sector 7 Trim as required 8 Electrical fuel pump ON at high altitudes CAUTION Operation at high altitudes with the electrical fuel pump OFF may cause vapor bubbles resulting in intermittent low fuel pressure indications sometimes followed by high fuel fl...

Page 144: ...RPM lever 2400 RPM 4 Throttle MAX PWR 5 Mixture control lever RICH above 5000 ft hold EGT constant 6 Engine instruments in green sector 7 Trim as required 8 Electrical fuel pump ON at high altitudes CAUTION Operation at high altitudes with the electrical fuel pump OFF may cause vapor bubbles resulting in intermittent low fuel pressure indications sometimes followed by high fuel flow indications EN...

Page 145: ...ptimize engine life the cylinder head temperature CHT should lie between 150 F 66 C and 400 F 204 C in continuous operation and not rise above 435 F 224 C in fast cruise NOTE The oil temperature in continuous operation should lie between 165 F 74 C and 220 F 104 C If possible the oil temperature should not remain under 180 F 82 C for long periods so as to avoid accumulation of condensation water 4...

Page 146: ...S gal with Long Range Tank 7 Electrical fuel pump ON at high altitudes CAUTION Operation at high altitudes with the electrical fuel pump OFF may cause vapor bubbles resulting in intermittent low fuel pressure indications sometimes followed by high fuel flow indications NOTE While switching from one tank to the other the electrical fuel pump should be switched ON END OF CHECKLIST ...

Page 147: ...ng rate should not exceed 50 F 22 8 C per minute Best Economy Mixture The best economy mixture setting may only be used up to a power setting of 75 In order to obtain the lowest specific fuel consumption at a particular power setting proceed as follows Slowly pull the mixture control lever back towards LEAN until the engine starts to run roughly Then push the mixture control lever forward just far...

Page 148: ...mance at allpower settings The mixture should first be set as for best economy The mixture should then be enriched until the exhaust gas temperature is approximately 100 F 55 C lower This mixture setting produces the maximum performance for a given manifold pressure and is mainly used for high power settings approximately 75 END OF CHECKLIST ...

Page 149: ...emperature should not exceed 50 F 22 8 C per minute This is normally guaranteed by the self adapting inlet An excessive cooling rate may occur however when the engine is very hot and the throttle is reduced abruptly in a fast descent This will be indicated by a flashing cylinder head temperature indication CAUTION Operation at high altitudes with the electrical fuel pump OFF may cause vapor bubble...

Page 150: ...s required 7 Landing light as required Before Landing 8 Mixture control lever RICH 9 RPM lever HIGH RPM 10 Throttle as required 11 Airspeed reduce to operate flaps 91 KIAS 12 Flaps LDG 13 Approach speed 73 KIAS 1200 kg 2646 lb 71 KIAS 1150 kg 2535 lb 67 KIAS 1092 kg 2407 lb 63 KIAS 1000 kg 2205 lb 58 KIAS 850 kg 1874 lb CAUTION In conditions such as e g strong wind danger of wind shear or turbulen...

Page 151: ...Page 4A 35 NOTE In case of airplanes with a maximum landing mass less than the maximum permitted flight mass a landing with a higher mass constitutes an abnormal operating procedure Refer to Sections 2 7 MASS WEIGHT and 4B 7 LANDING WITH HIGH LANDING MASS END OF CHECKLIST ...

Page 152: ...2 Airspeed 67 KIAS 1200 kg 2646 lb 66 KIAS 1150 kg 2535 lb 60 KIAS 1000 kg 2205 lb 54 KIAS 850 kg 1874 lb 3 Flaps T O Above a Safe Height 4 RPM lever 2400 RPM 5 Airspeed 76 KIAS 1200 kg 2646 lb 73 KIAS 1150 kg 2535 lb 68 KIAS 1000 kg 2205 lb 60 KIAS 850 kg 1874 lb 6 Flaps UP 7 Electrical fuel pump OFF END OF CHECKLIST ...

Page 153: ...c 6 01 01 E Rev 8 01 Dec 2010 Page 4A 37 4A 3 14 AFTER LANDING 1 Throttle IDLE 2 Brakes as required 3 Electrical fuel pump OFF 4 Transponder OFF STBY 5 Pitot heating OFF 6 Avionics as required 7 Lights as required 8 Flaps UP END OF CHECKLIST ...

Page 154: ...arking brake set 2 Engine instruments check 3 Avionics Master switch OFF 4 All electrical equipment OFF 5 Throttle 1000 RPM 6 Ignition check OFF until RPM drops noticeably then immediately BOTH again 7 Mixture control lever LEAN shut engine off 8 Ignition switch OFF 9 Master switch ALT BAT OFF END OF CHECKLIST ...

Page 155: ...nics Master switch OFF 6 Master switch BAT OFF 7 Parking brake release use chocks 8 Airplane moor if unsupervised for extended period NOTE If the airplane is not operated for more than 5 days the long term parking procedure should be applied If the airplane is not operated for more than 30 days the storage procedure should be applied Both procedures are described in the Airplane Maintenance Manual...

Page 156: ... minimal Flight through very heavy rain should be avoided because of the associated visibility problems 4A 3 18 REFUELING CAUTION Before refueling the airplane must be connected to electrical ground Groundingpoints unpaintedareas latches onsteps left and right 4A 3 19 FLIGHT AT HIGH ALTITUDE At high altitudes the provision of oxygen for the occupants is necessary Legal requirements for the provisi...

Page 157: ...ANDING 4B 2 4B 2 INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE 4B 4 4B 3 FAILURES IN THE ELECTRICAL SYSTEM 4B 5 4B 4 TAKE OFF FROM A SHORT GRASS STRIP 4B 7 4B 5 FAILURES IN FLAP OPERATING SYSTEM 4B 9 4B 6 FAILURES IN ELECTRICAL RUDDER PEDAL ADJUSTMENT 4B 10 4B 7 LANDING WITH HIGH LANDING MASS 4B 11 4B 8 STARTING THE ENGINE WITH EXTERNAL POWER 4B 12 ...

Page 158: ... controlled landing 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 Select appropriate landing area 2 Consider wind 3 Approach If possible the landing area should be overflown at a suitable height in order to recognize obstacles The degree of offset at...

Page 159: ...proach 6 Flaps LDG 7 Safety harnesses tighten 8 Touchdown with the lowest possible airspeed CAUTION If sufficient time is remaining the risk in the event of a collision with obstacles can be reduced as follows Fuel tank selector OFF Ignition switch OFF Master switch ALT BAT OFF END OF CHECKLIST ...

Page 160: ...If the manifold pressure indicator is clearly above the green range the reading is faulty In this case the performance settings should be undertaken by means of the lever settings The airplane should be serviced c Oil Temperature A constant reading of the oil temperature of 26 F 3 C or 317 F 158 C suggests a faulty oil temperature sensor The airplane should be serviced d Cylinder Head Temperature ...

Page 161: ... i Low Voltage Caution on the Ground 1 Engine speed 1200 RPM 2 Electrical equipment OFF 3 Ammeter check If the caution light does not go out and the ammeter flashes and reads zero Terminate flight preparation ii Low Voltage Caution During Flight 1 Electrical equipment OFF if not needed 2 Ammeter check If the caution light does not go out and the ammeter flashes and reads zero Follow procedure in 3...

Page 162: ...tion control unit is installed but inoperative the white status light for the ignition IGN or IGNITION will be illuminated and the conventional magneto ignition will take over the ignition control The flight can be continued normally However fuel consumption will slightly increase and engine starting will become difficult END OF CHECKLIST ...

Page 163: ...osswinds steering can be augmented by use of the toe brakes It should be noted however that this method increases the take off roll and should not generally be used 7 Elevator control stick release slowly when nose wheel has lifted Allow airplane to lift off as soon as possible and increase speed at low level 8 Airspeed 67 KIAS 1200 kg 2646 lb 66 KIAS 1150 kg 2535 lb 60 KIAS 1000 kg 2205 lb 54 KIA...

Page 164: ...ormal Operating Procedures DA 40 AFM Page 4B 8 Rev 8 01 Dec 2010 Doc 6 01 01 E 10 Flaps UP above safe altitude 11 Electrical fuel pump OFF above safe altitude 12 Landing light as required END OF CHECKLIST ...

Page 165: ... in white sector Re check all positions of the flap switch Modified Approach Procedure Depending on the Available Flap Setting a Only UP or T O Available Airspeed 76 KIAS 1200 kg 2646 lb 73 KIAS 1150 kg 2535 lb 68 KIAS 1000 kg 2205 lb 60 KIAS 850 kg 1874 lb Land at a flat approach angle use throttle to control airplane speed and rate of descent b Only LDG Available Perform normal landing END OF CH...

Page 166: ... FAILURES IN ELECTRICAL RUDDER PEDAL ADJUSTMENT Runaway of Electrical Rudder Pedal Adjustment Optional Equipment OÄM 40 251 NOTE The circuit breaker for the rudder pedal adjustment is located below the related switch on the rear wall of the leg room 1 Circuit breaker pull END OF CHECKLIST ...

Page 167: ...d 4A 3 12 LANDING APPROACH 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 landing gear loads during a particularly hard landing Perform landing approach and landing according to Chapter 4A but maintain an increased airspeed during landing approach Approa...

Page 168: ... external power supply must be operated by a person made aware of the associated procedures Special care is required due to the proximity of the propeller area NOTE Starting the engine with external power is recommended in particular at ambient temperatures below 0 C 32 F to reduce wear and abuse to the engine and electrical system 1 Pre flight inspection complete 2 Rudder pedals adjusted 3 Passen...

Page 169: ...n 8 Front canopy Position 1 or 2 Cooling gap 9 Canopy lock if installed unblocked key removed 10 Parking brake set 11 Flight controls free movement 12 Trim wheel T O 13 Throttle IDLE 14 RPM lever HIGH RPM 15 Mixture control lever LEAN 16 Friction device throttle quadrant adjusted 17 Alternate air CLOSED 18 Alternate static valve CLOSED if installed 19 Avionics Master switch OFF 20 Essential Bus sw...

Page 170: ...lector on full tank WARNING Never move the propeller by hand while the ignition is switched on as it may result in serious personal injury Never try to start the engine by hand 25 Starting engine procedure refer to 4A 3 3 execute 26 External power disconnect close access panel 27 Ammeter check 28 Master switch ALT OFF note decrease of ammeter reading 29 Master switch ALT ON END OF CHECKLIST ...

Page 171: ...ABLE FOR SETTING ENGINE PERFORMANCE 5 4 5 3 3 PRESSURE ALTITUDE DENSITY ALTITUDE 5 7 5 3 4 STALLING SPEEDS 5 8 5 3 5 WIND COMPONENTS 5 9 5 3 6 TAKE OFF DISTANCE 5 10 5 3 7 CLIMB PERFORMANCE TAKE OFF CLIMB 5 13 5 3 8 CLIMB PERFORMANCE CRUISE CLIMB 5 15 5 3 9 CRUISING TRUE AIRSPEED TAS 5 17 5 3 10 LANDING DISTANCE FLAPS LDG 5 18 5 3 11 LANDING DISTANCE FLAPS UP 5 21 5 3 12 GRADIENT OF CLIMB ON GO AR...

Page 172: ...ce or a poorly maintained airplane The performances given can be attained if the procedures quoted in this manual are applied and the airplane has been well maintained 5 2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS In order to illustrate the influence of a number of different variables the performance data is reproduced in the form of tables or diagrams These contain sufficiently detailed informat...

Page 173: ...DA 40 AFM Performance Doc 6 01 01 E Rev 8 01 Dec 2010 Page 5 3 5 3 PERFORMANCE TABLES AND DIAGRAMS 5 3 1 AIRSPEED CALIBRATION ...

Page 174: ...NOTE If the Long Range Tank is installed Auxiliary fuel below 3 US gal cannot be indicated by the system If a fuel indicator shows 16 US gal and the auxiliary fuel indicator reads 0 US gal on the same side for in flight fuel consumption flight planning a fuel quantity available of 16 US gal must be assumed ...

Page 175: ...1 20 7 19 6 18 4 23 3 21 9 20 7 3000 9 48 21 8 20 4 19 3 18 2 23 0 21 6 20 4 4000 7 45 21 5 20 2 19 0 17 9 22 7 21 2 20 1 5000 5 41 21 2 19 9 18 7 17 6 22 3 20 9 19 8 6000 3 38 20 9 19 6 18 4 17 4 22 0 20 6 19 5 7000 1 34 20 5 19 3 18 2 17 1 21 7 20 3 19 3 8000 1 31 20 2 19 0 17 9 16 9 21 3 20 0 19 0 9000 3 27 19 9 18 7 17 6 16 6 21 1 19 7 18 7 10000 5 23 19 6 18 4 17 3 16 3 19 4 18 4 11000 7 19 1...

Page 176: ... 22 9 26 5 25 2 3000 9 48 25 7 23 8 22 6 26 1 24 8 4000 7 45 25 4 23 5 22 3 24 5 5000 5 41 23 1 22 0 24 1 6000 3 38 22 8 21 7 7000 1 34 22 4 21 4 8000 1 31 21 0 9000 3 27 20 7 10000 5 23 The areas shaded grey under each RPM heading are the recommended bands Correcting the Table for Variation from Standard Temperature At ISA 15 C ISA 27 F the performance values fall by approx 3 of the power selecte...

Page 177: ...0 4000 2000 0 0 500 1000 1500 2000 2500 3000 3500 4000 0 500 1000 1500 2000 2500 3000 3500 4000 20 10 0 10 20 30 500 32 50 68 86 14 4 C F 5 3 3 PRESSURE ALTITUDE DENSITY ALTITUDE Conversion from pressure altitude to density altitude Example 1 Set 1013 25 hPa on altimeter and read pressure altitude 900 ft 2 Establish ambient temperature 21 EC 70 F 3 Read off density altitude 1800 ft Result From a p...

Page 178: ...lb 980 kg Bank Angle 0 30 45 60 Flaps UP 47 52 58 73 T O 44 51 58 72 LDG 42 49 57 71 Mass 1150 kg 2535 lb 1150 kg Bank Angle 0 30 45 60 Flaps UP 52 57 66 79 T O 51 55 64 78 LDG 49 55 62 76 Mass 1200 kg 2646 lb if MÄM 40 227 is carried out 1200 kg Bank Angle 0 30 45 60 Flaps UP 53 58 68 83 T O 52 57 67 81 LDG 52 57 66 80 ...

Page 179: ... 40 AFM Performance Doc 6 01 01 E Rev 8 01 Dec 2010 Page 5 9 5 3 5 WIND COMPONENTS Example Flight direction 360 Wind 32 30 kts Result Crosswind component 16 kts Max demonstrated crosswind component 20 kts ...

Page 180: ...535 lb 60 KIAS below 1000 kg 2205 lb Runway level asphalt surface WARNING Poor maintenance condition of the airplane deviation from the given procedures as well as unfavorable external factors hightemperature rain unfavorablewindconditions including cross wind will increase the take off distance CAUTION For a safe take off the take off run available TORA should be at least equal to the take off di...

Page 181: ...lowing corrections must be taken into account compared to paved runways typical values see CAUTION above 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 least 25 increase in take off roll Grass longer than 25 cm 10 in take off should not be attempted NOTE On wet grass a further 10 increase in take ...

Page 182: ...Performance DA 40 AFM Page 5 12 Rev 8 01 Dec 2010 Doc 6 01 01 E ...

Page 183: ...01 E Rev 8 01 Dec 2010 Page 5 13 5 3 7 CLIMB PERFORMANCE TAKE OFF CLIMB Conditions Throttle MAX PWR RPM lever 2400 RPM Flaps T O Airspeed 67 KIAS 1200 kg 2646 lb 66 KIAS 1150 kg 2535 lb 60 KIAS 1000 kg 2205 lb 54 KIAS 850 kg 1874 lb ...

Page 184: ...Performance DA 40 AFM Page 5 14 Rev 8 01 Dec 2010 Doc 6 01 01 E ...

Page 185: ...1 01 E Rev 8 01 Dec 2010 Page 5 15 5 3 8 CLIMB PERFORMANCE CRUISE CLIMB Conditions Throttle MAX PWR RPM lever 2400 RPM Flaps UP Airspeed 76 KIAS 1200 kg 2646 lb 73 KIAS 1150 kg 2535 lb 68 KIAS 1000 kg 2205 lb 60 KIAS 850 kg 1874 lb ...

Page 186: ...Performance DA 40 AFM Page 5 16 Rev 8 01 Dec 2010 Doc 6 01 01 E ...

Page 187: ...E AIRSPEED TAS Diagram to establish true airspeed TAS at a given power setting Example Pressure altitude 5000 ft Temperature 15 EC 59 F Power setting 55 Result True Airspeed TAS 118 kts CAUTION In case of operation without wheel fairings the cruising speed reduces by approximately 5 ...

Page 188: ...1150 kg 2535 lb up to 1200 kg 2646 lb will increase the landing distance over a 50 ft 15 m obstacle and the landing ground roll distance up to 6 Values for ISA and MSL at 1150 kg 2535 lb Landing distance over a 50 ft 15 m obstacle approx 638 m 2093 ft Ground roll approx 352 m 1155 ft WARNING Poor maintenance condition of the airplane deviation from the given procedures as well as unfavorable exter...

Page 189: ... of the runway to ensure a safe landing NOTE For landings on dry short cut grass covered runways the following corrections must be taken into account compared to paved runways typical values see CAUTION above 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 longer than 10 cm 4 in at least 25 increase in landing roll NOTE On wet...

Page 190: ...Performance DA 40 AFM Page 5 20 Rev 8 01 Dec 2010 Doc 6 01 01 E ...

Page 191: ... 1150 kg 2535 lb up to 1200 kg 2646 lb will increase the landing distance over a 50 ft 15 m obstacle and the landing ground roll distance up to 6 Values for ISA and MSL at 1150 kg 2535 lb Landing distance over a 50 ft 15 m obstacle approx 775 m 2543 ft Ground roll approx 471 m 1545 ft WARNING Poor maintenance condition of the airplane deviation from the given procedures as well as unfavorable exte...

Page 192: ...of the runway to ensure a safe landing NOTE For landings on dry short cut grass covered runways the following corrections must be taken into account compared to paved runways typical values see CAUTION above 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 longer than 10 cm 4 in at least 25 increase in landing roll NOTE On wet ...

Page 193: ...Rev 8 01 Dec 2010 Page 5 23 Landing Distance Flaps UP Example Result Pressure altitude 4000 ft Landing distance over 50 ft obstacle approx 580 m 1903 ft OAT 8 C 46 F Ground roll approx 270 m 886 ft Mass 1000 kg 2205 lb Headwind comp 8 kts ...

Page 194: ...ing Take off Flaps LDG Airspeed 70 KIAS ISA MSL If MÄM 40 227 is carried out The DA 40 reaches a constant gradient of climb of 7 0 in the following condition Mass max flight mass 1200 kg 2646 lb Power setting Take off Flaps LDG Airspeed 73 KIAS ISA MSL 5 3 13 APPROVED NOISE DATA ICAO Annex 16 Chapter X 69 28 dB A JAR 36 Subpart C 69 28 dB A If MÄM 40 227 is carried out ICAO Annex 16 Chapter X 78 4...

Page 195: ... 6 2 DATUM PLANE 6 3 6 3 MASS AND BALANCE REPORT 6 3 6 4 FLIGHT MASS AND CENTER OF GRAVITY 6 5 6 4 1 MOMENT ARMS 6 9 6 4 2 LOADING DIAGRAM 6 10 6 4 3 CALCULATION OF LOADING CONDITION 6 11 6 4 4 PERMISSIBLE CENTER OF GRAVITY RANGE 6 13 6 4 5 PERMISSIBLE MOMENT RANGE 6 15 6 5 EQUIPMENT LIST AND EQUIPMENT INVENTORY 6 16 ...

Page 196: ... at any point in time is described in this Chapter Over and above this there is a comprehensive list of the equipment approved for this airplane Equipment List as also a list of that equipment installed when the airplane was weighed Equipment Inventory Before the airplane is delivered the empty mass and the corresponding CG position are determined and entered in Section 6 3 MASS AND BALANCE REPORT...

Page 197: ...86 38 in forward of the most forward point of the root rib on the stub wing 6 3 MASS AND BALANCE REPORT The empty mass and the corresponding CG position established before delivery are the first entries in the Mass and Balance Report Every change in permanently installed equipment and every repair to the airplane which affects the empty mass or the empty mass CG must be recorded in the Mass and Ba...

Page 198: ...al or equipment changes Page Current Empty Mass Moment kg m in lb Moment Arm m in Mass kg lb Registration Changes in mass Subtraction Moment kg m in lb Moment Arm m in Mass kg lb Serial No Addition Moment kg m in lb Moment Arm m in Mass kg lb DA 40 Description of Part or Modification Upon delivery Entry No OUT IN Date ...

Page 199: ...and enter the figures in the appropriate boxes under the column marked Your DA 40 in Table 6 4 3 CALCULATION OF LOADING CONDITION Oil The difference between the actual amount of oil in the engine check with dipstick and the maximum oil quantity is called Oil not added this mass and its related moment are counted as negative The empty mass of the airplane is established with the maximum amount of o...

Page 200: ... 6 4 3 CALCULATION OF LOADING CONDITION For variants a and b use row 5 of the table row 6 is filled with 0 For variant c use row 6 of the table row 5 is filled with 0 Fuel a Standard Tank The fuel quantity can be read on the fuel indicators NOTE Depending on the type of fuel probes installed the indicator can read a maximum of 15 US gal or 17 US gal refer to Section 7 10 for details When the fuel ...

Page 201: ...witching the AUX FUEL QTY switch to the respective position LH or RH The indicated auxiliary fuel quantity is added to the 16 US gal An auxiliary fuel quantity of less than 3 US gal cannot be indicated by the system In this case the quantity must be determined by means of the fuel quantity measuring device see Section 7 10 FUEL SYSTEM CAUTION The correct indication of the fuel quantity takes 2 min...

Page 202: ...ION For airplanes equipped with the optional Long Range Tank a restricted range of permitted CG positions applies As an illustration the total mass and the CG position are entered on Diagram 6 4 4 PERMISSIBLE CENTER OF GRAVITY RANGE This checks graphically that the current configuration of the airplane is within the permissible range Graphical Method Diagram 6 4 2 LOADING DIAGRAM is used to determ...

Page 203: ...00 mm 23 62 in 31 mm 1 22 in 6 4 1 MOMENT ARMS The most important lever arms aft of the Datum Plane Oil 1 00 m 39 4 in Front seats 2 30 m 90 6 in Rear seats 3 25 m 128 0 in Wing tanks Standard Long Range 2 63 m 103 5 in Baggage in standard baggage compartment 3 65 m 143 7 in baggage in baggage tube 4 32 m 170 1 in Baggage in extended baggage compartment forward part 3 89 m 153 1 in aft part 4 54 m...

Page 204: ...8 01 Dec 2010 Doc 6 01 01 E 25 50 100 125 150 175 200 225 75 Load Mass lb kg 100 200 300 400 500 kgm 50 100 150 10 20 30 40 Fuel Quantity US gal Liters Load Moment 200 50 100 200 300 400 500 100 200 300 400 500 In lb 6 4 2 LOADING DIAGRAM ...

Page 205: ...al Long Range Tank a restricted range of permitted CG positions applies NOTE For the mass weight of the fuel a density of 0 72 kg liter 6 01 lb US gal is assumed For the mass weight of the engine oil a density of 0 89 kg liter 1 86 lb US qt 0 84 kg US qt is assumed NOTE In the following example it is assumed that the fuel tank is not full at take off ...

Page 206: ...89 m 153 1 in 27 60 105 9 186 Aft extended baggage compartment Lever arm 4 54 m 178 7 in 18 40 81 7 7 148 7 Total mass total moment with empty fuel tanks Total of 1 6 1003 3 2212 2533 8 220 047 8 Usable fuel Lever arm 2 63 m 103 5 in 99 4 219 261 4 22 667 9 Total mass total moment including fuel 7 plus 8 1102 7 2431 2795 2 242 714 10 The total moments from rows 7 and 9 2533 8 and 2795 2 kgm 220 04...

Page 207: ... 2 50 2 55 2 60 6 4 4 PERMISSIBLE CENTER OF GRAVITY RANGE The CG s shown in the diagram are those that from the example in Table 6 4 3 CALCULATION OF LOADING CONDITION Forward Flight CG Limit 2 40 m 94 5 in aft of Datum Plane at 780 to 980 kg 1720 to 2161 lb 2 46 m 96 9 in aft of Datum Plane at 1150 kg 2535 lb linear variation between these values If MÄM 40 227 is carried out 2 40 m 94 5 in aft of...

Page 208: ...ass Balance DA 40 AFM Page 6 14 Rev 8 01 Dec 2010 Doc 6 01 01 E Rearward Flight CG Limit 2 59 m 102 0 in aft of Datum Plane Standard Tank 2 55 m 100 4 in aft of Datum Plane with Long Range Tank installed ...

Page 209: ...DA 40 AFM Mass Balance Doc 6 01 01 E Rev 8 01 Dec 2010 Page 6 15 2486 3060 3108 2600 6 4 5 PERMISSIBLE MOMENT RANGE ...

Page 210: ...elow The items of equipment installed in your particular airplane are indicated in the appropriate column The set of items marked as installed constitutes the Equipment Inventory NOTE The equipment listed below cannot be installed in any arbitrary combination The airplane manufacturer must be contacted before removing or installing equipment with the exception of replacing a unit by an identical u...

Page 211: ... 7 1 68 70 08 1 78 COMM 1 KX 165 069 01025 0025 Bendix King 5 65 2 56 70 08 1 78 COMM 1 KX 165A 069 01033 0101 Bendix King 4 0 1 81 70 08 1 78 COMM 1 KX 165A 8 33 kHz 069 01033 0201 Bendix King 4 0 1 81 70 08 1 78 COMM 1 GNS 430 011 00280 00 Garmin 5 1 2 31 70 08 1 78 COMM 1 GNS 430 011 00280 10 Garmin 5 1 2 31 70 08 1 78 COMM 1 GNS 530 011 00550 00 Garmin 6 8 3 08 70 08 1 78 COMM 1 GNS 530 011 00...

Page 212: ...H pax Echelon 100 Telex Speaker FRS8 4 Ohms Visaton Handmic 100TRA 62800 001 Telex AUTOPILOT SYSTEM Autopilot system KAP 140 Bendix King Flight computer w o alt preselect KC 140 065 00176 5402 without MÄM 40 099 or MSB 40 018 Bendix King 2 02 0 918 70 08 1 78 Flight computer with alt preselect KC 140 065 00176 7702 without MÄM 40 099 or MSB 40 018 Bendix King 2 02 0 918 70 08 1 78 Flight computer ...

Page 213: ... 1 224 120 0 3 06 Trim servo KS 272 C 065 00180 3500 Bendix King 2 22 1 005 87 2 2 21 Trim servo mount KM 277 065 00041 0000 Bendix King 1 09 0 494 87 2 2 21 Configuration module KCM 100 071 00073 5000 Bendix King 0 06 0 026 70 08 1 78 Sonalert SC SC 628 Mallory Control stick DA4 2213 12 90 Diamond CWS stick 031 00514 0000 Bendix King AP disc switch 031 00428 0000 Bendix King Trim switch assy 200 ...

Page 214: ...nverter MD 26 MD 26 28 Mid Continent EQUIPMENT Safety belt pilot 5 01 Series 5 01 1C0701 Schroth 3 36 1 524 92 52 2 35 Safety belt co pilot 5 01 Series 5 01 1C5701 Schroth 3 36 1 524 92 52 2 35 Safety belt LH pax 5 01 Series 5 01 1B5701 Schroth 3 0 1 36 126 7 3 22 Safety belt RH pax 5 01 Series 5 01 1B0701 Schroth 3 0 1 36 126 7 3 22 Safety belt receptacle pilot Schroth 0 54 0 245 92 52 2 35 Safet...

Page 215: ...unit ME 406 453 6603 Artex 2 0 91 173 2 4 40 ELT buzzer 452 6505 Artex ELT antenna WHIP 110 773 Artex ELT remote switch ACE 453 0023 Artex ELT module interface 453 1101 Artex Winter baffle DA4 2157 00 00 Diamond Armrest DA4 5210 50 91 Diamond Baggage extension OÄM 40 163 Baggage net OÄM 40 163 Baggage tray OÄM 40 164 FLIGHT CONTROLS Flaps control unit instr panel 430550 Diamond Flaps actuator assy...

Page 216: ...warning horn assy F DA4 2739 10 00X05 Diamond SAFETY EQUIPMENT Fire extinguisher portable HAL 1 AIR Total 4 85 2 2 110 0 2 794 Fire extinguisher portable 1 A 620 T Amerex 2 43 1 1 110 0 2 794 First aid kit Emergency axe G45912 Fiskars 1 23 0 558 78 74 2 00 FUEL Fuel qty indicator VM1000 4010028 Vision Microsyst Fuel qty sensor LH VM1000 30100 11 Vision Microsyst Fuel qty sensor RH VM1000 30100 11 ...

Page 217: ...0 239 Cleveland INDICATING REC SYSTEM Digital chronometer LC 2 AT420100 Astro Tech Digital chronometer Model 803 Davtron Flight timer 85000 12 Hobbs Flight timer 85094 12 Hobbs Annunciator panel system Diamond Annunciator panel WW IDC 001 White Wire CO detector Model 452 201 CO Guardian LLC LANDING GEAR MLG wheel fairing inst DA4 3215 00 00 Diamond MLG speed kit LH DA4 3219 01 00 Diamond MLG speed...

Page 218: ...sy WW LCM 002 White Wire Glareshield lamp assy DA4 3311 10 01 Diamond Aircraft Glareshield light inverter APVL328 8 3 L 18QF Quantaflex Strobe Pos light assy LH A600 PR D 28 01 0790006 05 Whelen Strobe Pos light assy RH A600 PG D 28 01 0790006 07 Whelen Strobe light power supply LH RH A490ATS CF 14 28 01 0770062 05 Whelen 1 592 0 722 101 0 2 566 Taxi light 70346 01 0770346 05 Whelen Landing light ...

Page 219: ...1 78 Vertical speed indicator LUN 1144 1144 A4B4 Mikrotechna 0 9 0 4 70 08 1 78 Airspeed indicator 8025 United Instruments 0 7 0 32 70 08 1 78 Airspeed indicator LUN 1116 1116 B4B3 Mikrotechna 0 77 0 35 70 08 1 78 Outside air temp indication 301F C Davtron 0 27 0 124 70 08 1 78 Magnetic compass C2400L4P Airpath 0 65 0 293 70 08 1 78 Compass system C O KCS 55A Bendix King Slaved gyro KG 102 A 060 0...

Page 220: ...4T100 12RB Mid Continent Instr 1 41 0 64 70 08 1 78 Marker antenna CI102 Comant DME KN 62A 066 01068 0004 Bendix King 2 6 1 18 70 08 1 78 DME antenna KA60 071 01174 0000 Bendix King DME antenna KA60 071 01591 0001 Bendix King DME antenna KA61 071 00221 0010 Bendix King Transponder KT 76A 066 1062 10 Bendix King 0 85 0 39 70 08 1 78 Transponder KT 76C 066 01156 0101 Bendix King 0 2 0 09 70 08 1 78 ...

Page 221: ...OM 1 volt conv KA39 071 01041 001 Bendix King NAV COM 1 KX155A 069 01032 0201 Bendix King 3 7 1 68 70 08 1 78 NAV COM 1 KX 165 069 01025 0025 Bendix King 5 65 2 56 70 08 1 78 NAV COM 1 KX 165A 069 01033 0101 Bendix King 4 0 1 81 70 08 1 78 NAV COM 1 KX 165A 8 33 kHz 069 01033 0201 Bendix King 4 0 1 81 70 08 1 78 NAV COM 2 KX155A 069 01032 0201 Bendix King 3 7 1 68 70 08 1 78 NAVCOM GPS 1 GNS 430 0...

Page 222: ... Bendix King GPS antenna 1 GA 56 011 00134 00 Garmin GPS antenna 2 GA 56 011 00134 00 Garmin GPS annunciation unit MD41 1488 Mid Continent GPS AP switch assy MD41 528 Mid Continent Multifunction display GPS KMD 150 066 01174 0101 Bendix King 3 3 1 5 70 08 1 78 Stormscope WX 500 805 11500 001 Goodrich Stormscope antenna NY 163 805 10930 001 Goodrich Strike finder display SF 2000 2000 009 Insight St...

Page 223: ...rosyst Fuel pressure transmitter VM1000 3010017 Vision Microsyst ENGINE IGNITION SYSTEM SlickSTART booster SS1001 Unison Lasar ignition controller LC 1002 03 LC 1002 03 Unison Lasar ignition harnedd LH 1004 43 Unison Magneto RH LH 4370 4347 Slick Magneto RH LH 4770 4771 Slick ENGINE INDICATING RPM sensor VM1000 3010005 Vision Microsyst Manifold pressure sensor VM1000 3010016 Vision Microsyst Cyl h...

Page 224: ...3020003 Vision Microsyst I O board assy 3020018 Vision Microsyst ENGINE OIL Oil temperature sensor VM1000 3010021 Vision Microsyst Oil pressure transducer VM1000 3010018 Vision Microsyst ENGINE STARTING Starter 149 24LS Skytec PROPELLER SYSTEM Propeller MTV 12 B 180 17 mt Propeller 47 0 21 32 15 0 0 381 Propeller MTV 12 B 180 17f mt Propeller 47 0 21 32 15 0 0 381 Propeller governor C 210776 Woodw...

Page 225: ...01 Dec 2010 Page 6 31 AIRPLANE FLIGHT MANUAL Doc No 6 01 01 E Diamond 1 The Amerex A 620 T fire extinguisher is UL approved and can be used in airplanes registered in Canada and the USA For airplanes registered in other countries refer to the national Airworthiness Authority Place ____________________ Date ______________________ Signature __________________________ ...

Page 226: ...DA 40 AFM Mass and Balance Doc No 6 01 01 E Rev 8 01 Dec 2010 Page 6 32 Intentionally left blank ...

Page 227: ...BAGGAGE COMPARTMENT 7 16 7 8 CANOPY REAR DOOR AND CABIN INTERIOR 7 17 7 9 POWER PLANT 7 20 7 9 1 ENGINE GENERAL 7 20 7 9 2 OPERATING CONTROLS 7 21 7 9 3 PROPELLER 7 24 7 9 4 ENGINE INSTRUMENTS 7 25 7 10 FUEL SYSTEM 7 31 7 11 ELECTRICAL SYSTEM 7 40 7 11 1 GENERAL 7 42 7 11 2 DAI ANNUNCIATOR PANEL WARNING CAUTION AND STATUS LIGHTS 7 46 7 11 3 WHITE WIRE ANNUNCIATOR PANEL WARNING CAUTION AND STATUS L...

Page 228: ...irplane Description DA 40 AFM Page 7 2 Rev 8 01 Dec 2010 Doc 6 01 01 E 7 15 CO MONITOR IF INSTALLED 7 55 7 15 1 SELF TEST SEQUENCE 7 55 7 15 2 IN FLIGHT CO ALARM 7 55 7 15 3 UNIT FAILURE INDICATION 7 56 ...

Page 229: ...esistant matting which is covered on the engine side by stainless steel cladding The two main bulkheads are GFRP CFRP items Wings The wings have a front and rear spar each wing has a top shell and a bottom shell a fail safe concept The wings as well as the aileron and flaps are made of GFRP CFRP and are principally of sandwich construction An aluminum fuel tank is installed in each of the wings Em...

Page 230: ...s which are hinge pins mounted in an aluminum bracket They are secured in position by a roll pin The absence of this roll pin can lead to the loss of the hinge pin and a consequent loss of flight safety Operation A rod end bearing is screwed into a steel push rod and locked by means of a nut which has locking varnish applied to it Damage to this varnish can indicate a twisting and thus a change to...

Page 231: ...n tube The torsion tube is located in the fuselage creating a connection between the left and right flaps Operation A rod end bearing is screwed into a steel push rod and locked by means of a nut which has locking varnish applied to it Damage to this varnish can indicate a twisting and thus a change to the adjustment The connection between the rod end bearing and the control horn is a bolt the nut...

Page 232: ...ected by a limit switch to guard against over running the end positions The electrical flap drive has an automatic circuit breaker which can also be operated manually Flap Position Indicator The current flap position is indicated by means of three lights beside the flap selector switch When the upper light green is illuminated the flaps are in the Cruise position UP When the center light white is ...

Page 233: ...well as the connection to the push rod can be visually inspected at the upper end of the rudder Rudder Construction GFRP sandwich Hinges Upper hinge One bolt Lower hinge Bearing bracket including rudder stops held by 4 screws to the rear web of the vertical stabilizer The mating part on the rudder is a bracket which is attached to the rudder by 2 bolts The bolts and nuts are accessible to visual i...

Page 234: ...s may only be adjusted on the ground The pedals are unlocked by pulling the black T grip handle which is located behind the rear attachment straight back NOTE When adjusting rudder pedals to install the control surfaces gust lock pull straight back on T grip do not pull up Forward Adjustment Whilst keeping the handle pulled push the pedals forward with your feet Release the handle and allow the pe...

Page 235: ... leg room The related circuit breaker is located below the switch Forward Adjustment To move the pedals forward depress lower side of switch When pedals are in correct position release switch Rearward Adjustment To move the pedals in the rearward direction depress upper side of switch When pedals are in correct position release switch Locking Upon release the switch moves automatically to the powe...

Page 236: ...s instrument panel variants Therefore only two example variants VFR and IFR are described in this section The equipment that is actually installed in a particular airplane is listed in the Equipment Inventory in Section 6 5 The airplane manufacturer must be contacted before removing or installing equipment with the exception of replacing a unit by an identical unit ...

Page 237: ...DA 40 AFM Airplane Description Doc 6 01 01 E Rev 8 01 Dec 2010 Page 7 11 VFR instrument panel example IFR instrument panel example ...

Page 238: ...ntrol unit optional 12 Vertical speed indicator VSI 29 Transponder 13 Attitude gyro artificial horizon 30 Stall warning horn 14 Horizontal situation indicator HSI 31 Microphone socket 15 Airspeed indicator 32 Ventilation nozzles 16 Turn bank indicator 33 Alternate Static Valve optional for VFR version 17 Slaving meter 34 ELT operating unit RCPI Designations and abbreviations used to identify the c...

Page 239: ...erformance see Chapter 5 Wheel Brakes Hydraulically operating disk brakes act on the wheels of the main landing gear The wheel brakes are individually operated by means of toe pedals Parking Brake The lever is located on the small center console under the instrument panel and is in the upper position when the brakes are released To operate the parking brake pull the lever downwards until it catche...

Page 240: ...Airplane Description DA 40 AFM Page 7 14 Rev 8 01 Dec 2010 Doc 6 01 01 E brake pedals pilot brake pedals co pilot parking brake valve brake cylinder LH brake cylinder RH Hydraulic System Schematic ...

Page 241: ...erlying controls Covers on the control sticks prevent loose objects from falling into the area of the controls 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 end of the belts in the belt lock and are opened by pressing the release on the belt lock The backs ...

Page 242: ...y be installed It is separated by a cloth cover Extended Baggage Compartment OÄM 40 163 and OÄM 40 164 if installed The extended baggage compartment consists of the standard baggage compartment behind the rear seats and the baggage extension mounted between the baggage compartment frame and ring frame No 1 The baggage extension has a door that may be hinged up to keep items from sliding aft or hin...

Page 243: ...y The front canopy can be blocked by a locking device optional 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 The airplane may be operated with the front canopy in the cooling gap position on the ground only Before take off the front canopy must be completely ...

Page 244: ... can be blocked by a locking device optional on the left side near the door opening lever by turning the key clockwise The closed and blocked door can be opened from inside by pulling the lever inside the opening handle WARNING The rear door must be closed and locked but not blocked with the locking device before the engine is started Heating and Ventilation Heating and ventilation are operated us...

Page 245: ...an emergency axe is installed on the floor panel under the pilot s seat see Figure below If the canopy can not be opened in case of an emergency use the emergency axe to break through the canopy WARNING Make sure not to harm other persons by using the emergency axe WARNING Beware of sharp edges and fragments of the broken canopy ...

Page 246: ... of the engine are the propeller governor the starter motor and the alternator The ignition optionally controlled by an electronic control unit the twin magneto system and the mechanical fuel pump are at the rear of the engine Fuel is supplied via a fuel injection system Further information should be obtained from the engine operating manual The engine instruments are on the right hand side of the...

Page 247: ...rward the engine is being provided with extra fuel for high performance settings Lever forward MAX PWR Full throttle higher MP Lever to rear IDLE Idle low MP High manifold pressure means that a large quantity of fuel air mixture is being supplied to the engine while low manifold pressure means a lesser quantity of fuel air mixture is being supplied RPM Lever Central lever with blue handle Lever fo...

Page 248: ...ould be adjusted using the throttle Every effort should be made not to exceed 2700 RPM CAUTION The throttle and RPM lever should be moved slowly in order to avoid over speeding and excessively rapid RPM changes The light wooden propeller blades produce more rapid RPM changes than metal blades Mixture Control Lever Right hand lever with red handle and lock to avoid inadvertent operation This lever ...

Page 249: ...y there is thus no fuel in the cylinders Alternate Air In the event of the loss of manifold pressure because of icing or blocking of the air filter there is the possibility of drawing air from the engine compartment The operating lever for alternate air is located under the instrument panel to the left of the center console To open alternate air the lever is pulled to the rear Normally alternate a...

Page 250: ...e lowest weight whilst minimizing the chance of vibration CAUTION Operation on the ground at high RPM should be avoided as far as possible as the blades could suffer stone damage For this reason a suitable site for engine runs magneto and propeller checks should be selected where there are no loose stones or similar items WARNING Never move the propeller by hand while the ignition is switched ON a...

Page 251: ... Page 7 25 7 9 4 ENGINE INSTRUMENTS Button 1 Lean mode Button 2 Digital exhaust gas cylinder head temperature mode Button 3 Switch in autotrack Button 4 Fuel computer mode Button 5 Engine data recorder Button 3 has an additional function on switch on Display mode ...

Page 252: ...inter as in conventional analog instruments whilst in the other case the circular instruments fill with pointers bars up to the current value It remains for the pilot to select his preferred presentation Indications on the Vision Microsystems VM 1000 Engine Instrument Designation Indication Unit MAN Manifold pressure inHg RPM RPM RPM EGT Exhaust gas temperature F CHT Cylinder head temperature F FU...

Page 253: ...The operation of button 1 causes the display to move to Lean mode This is confirmed by two half bars appearing to the left and right of the bar blocks In this mode all bars which previously showed cylinder head and exhaust gas temperature are used for exhaust gas temperature only One bar represents 10 F 4 6 C If the columns are completely filled with bars before the mixture is lean button 1 should...

Page 254: ... as beside it the number of the hottest cylinder Alternating with this the associated temperatures are displayed Button 3 Switch in Autotrack In the Autotrack mode changes in the engine values are shown If button 3 is operated in flight variations from the current values will be displayed in that the relevant circular instrument and the annotation AUTOTRACK will start to flash In order to leave th...

Page 255: ... 10 US gal are added by pressing button 3 while pressing button 5 adds one US gal to the total The quantity is confirmed by pressing button 4 In doing this the quantity which has been entered in ADD is added to the previous total under REM To check the fuel quantity button 4 should be pressed until REM is shown If too much has been added button 4 should not be pressed for confirmation After approx...

Page 256: ... The numerical RPM indicator will indicate the total operating hours Pressing button 5 again will show the maximum values encountered Pressing button 5 still another time will turn off the engine data recorder and the display will return to the original mode If button 5 is not pressed for approximately 20 seconds the display will automatically return to the original mode Data of the engine data re...

Page 257: ...w indication pump bleed line capillary check valve LEFT HAND WING filler neck tank with sensor drain finger filter FUSELAGE drain electrical pump filter screen fuel tank selector RIGHT HAND TANK symmetrical FIREWALL injection timing device with screen check valve intake air bleed line to cylinders to cylinders mechanical pump 7 10 FUEL SYSTEM a Standard Tank ...

Page 258: ...ed line capillary check valve LEFT HAND WING filler neck drain finger filter FUSELAGE drain electrical pump filter screen fuel tank selector RIGHT HAND WING symmetrical FIREWALL injection timing device with screen check valve intake air bleed line to cylinders to cylinders mechanical pump s e n s o r f o r a u x f u e l q t y f u e l q t y s e n s o r fuel tank b Long Range Tank ...

Page 259: ...d with the FUEL PUMP switch on the row of switches on the instrument panel It is checked during engine start and is used as a safety back up during take off and landing as well as when switching fuel tanks It is also switched on for safety in the event of a decrease in fuel pressure Fuel Tank Selector The fuel tank selector is situated on the center console Its positions are LEFT tank RIGHT tank a...

Page 260: ...iece of flexible hose and two independent vent hoses There are two separate vents per tank The hose terminations are situated on the underside of the wing approx 2 meter 7 ft from the wing tip One vent acts as a capillary both to equalize the air pressure and to provide a safety factor in the event of a failure of the other vent The second vent is a check valve to allow air to enter the tank but p...

Page 261: ...Tank A capacity probe ascertains fuel quantity in the tank When the fuel quantity indicator reads zero only the unusable fuel remains in the tank The total capacity of each tank is 20 US gal approximately 76 liter The maximum quantity that can be indicated is either 15 US gal up to serial number 40 054 or 17 US gal serial number 40 055 and subsequent The indication up to this quantity is correct A...

Page 262: ...s and is brought to indication on the left and right side of the instrument in increments of 1 US gal A fuel quantity between 16 US gal and 25 US gal is ascertained by the additional probes and is brought to indication in the central area of the fuel quantity indicator The indication is numerical in 3 US gal steps in the range from 0 to 3 US gal and 1 US gal steps in the range above 3 US gal up to...

Page 263: ...tween 16 US gal and 25 US gal of the tank selected with the AUX FUEL QTY switch The actual fuel quantity in the respective tank LH RH is the sum of the central indication and the corresponding indication on the left or right side CAUTION The correct indication of the fuel quantity takes 2 minutes after actuation of the AUX FUEL QTY switch ...

Page 264: ...strip at the leading edge of the wing The exact position is marked by a bore in the stall strip Then the metal connector is pressed against the drain of the tank The amount of fuel in the tank can now be read off from the vertical ascending pipe For a correct indication the airplane must be placed on a horizontal ground and the fuel filler must have been opened before The designated place for the ...

Page 265: ...17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 aeroplane on level ground unit in u s gallons unuseable fuel not indicated by cockpit instruments 20 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 aeroplane on level ground unit in u s gallons unuseable fuel 21 22 23 24 25 Diam ond AIRCRAFT Industries Dwg No D41 2807 90 00 ...

Page 266: ...Airplane Description DA 40 AFM Page 7 40 Rev 8 01 Dec 2010 Doc 6 01 01 E Simplified wiring diagram for serial numbers without Essential Bus 7 11 ELECTRICAL SYSTEM ...

Page 267: ...DA 40 AFM Airplane Description Doc 6 01 01 E Rev 8 01 Dec 2010 Page 7 41 Simplified wiring diagram for serial numbers with Essential Bus ...

Page 268: ... is extremely unlikely Storage Power is stored in a lead acid battery which is mounted in the right hand side of the engine compartment It has a capacity of 10 Ampère hour or more depending on the battery type The battery is connected to the airplane electrical system via the main 70 Ampère circuit breaker In addition a non rechargeable dry battery or a lithium battery pack is installed in the IFR...

Page 269: ...s controlled by the conventional retard breaker magneto system As an option the LASAR electronic ignition control unit can be installed instead of the SlickSTART system This unit measures manifold pressure and RPM and uses these parameters to optimize the ignition timing This provides for smooth engine running and improved starting behavior If the electronic ignition control is not in operation th...

Page 270: ... panel Position and Strobe Lights Combined position and strobe lights anti collision lights are installed on both wing tips Each system is operated by a switch POSITION STROBE on the row of switches on the instrument panel Flood Light A two dimensional light emitter is mounted above the instrument panel It illuminates the instrument panel as well as all levers switches etc With a rotary button FLO...

Page 271: ...the instrument panel The temperature is automatically kept constant by means of a thermal switch on the Pitot probe and as an additional safety measure a thermal fuse is built in If this thermal fuse is activated the Pitot heating can no longer be switched on and the Pitot heating caution will be displayed In this case the system should be serviced NOTE The Pitot heating caution will also be displ...

Page 272: ...switch This is to check that the lights have not failed All lights must be serviceable Alternator Warning Light ALT The alternator warning light illuminates on alternator failure The only remaining source of electrical power is the battery The color is red The procedure to be followed upon alternator warning is given in 3 7 2 FAILURES IN THE ELECTRICAL SYSTEM Low Voltage Caution Light VOLT This ca...

Page 273: ...gal 1 US gal The indication is calibrated for straight and level flight The light may illuminate during turns which are flown with slip or while taxiing in curves The color is amber Oil Pressure Warning Light OIL PR The oil pressure warning light illuminates when the oil pressure drops below 25 PSI The color is red The procedure to be followed upon oil pressure warning is given in 3 2 3 ENGINE PRO...

Page 274: ...e starter motor and the engine has not been broken This occurs when the pinion of the starter motor remains engaged with the propeller flywheel The color is red The procedure to be followed upon starter warning is given in 3 7 2 FAILURES IN THE ELECTRICAL SYSTEM Pitot Heating Caution Light PITOT The Pitot heating caution light is illuminated when the Pitot heating is not switched on or when there ...

Page 275: ...is muted By pressing the acknowledge button the lights are extinguished and a momentary aural alert 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 lights will begin flashing and the aural alert will sound continuously Warning Messages A warning is in...

Page 276: ...umination The LOW FUEL caution message is displayed in a slightly different manner extended functionality which is described below Alternator Warning Message ALTERNATOR The alternator warning message is displayed on alternator failure The only remaining source of electrical power is the battery The procedure to be followed upon alternator warning is given in 3 7 2 FAILURES IN THE ELECTRICAL SYSTEM...

Page 277: ...cond tank is also less than 3 US gal 1 US gal a caution message is displayed in a different manner A continuous aural alert is sounded in the airplane s intercom system the amber CAUTION light is flashed and the amber LOW FUEL caution light is flashed By pressing the acknowledge button which is now illuminated green the aural alert will be terminated and the CAUTION light will be extinguished The ...

Page 278: ...l be in use The color is white The WARNING light the CAUTION light and the aural alert will not be activated The procedure to be followed upon illumination of the ignition status light is given in 4B 3 FAILURES IN THE ELECTRICAL SYSTEM Starter Warning Message START The starter warning message is displayed when the connection between the starter motor and the engine has not been broken This occurs ...

Page 279: ...rheating of the Pitot heating system on the ground This is a normal function of the system After a cooling period the heating system will be switched on again automatically Trim Failure Warning Message TRIM FAIL The White Wire annunciator panel is prepared for the installation of an autopilot in the DA 40 When the autopilot is installed and ready for operation this warning message indicates a fail...

Page 280: ...re source in the event of a failure of the Pitot static system If an autopilot system is installed additional static sources may be installed OÄM 40 267 7 13 STALL WARNING If airspeed drops below approximately 10 to minimum 5 knots above the stalling speed the stall warning horn located in the instrument panel will sound The horn becomes progressively louder the closer one gets to stalling speed S...

Page 281: ...sensor and the integrity of the total CO detector system The remote alert light will flash twice Then the remote light will remain OFF until there is another CO alert or until a failure of the unit occurs 7 15 2 IN FLIGHT CO ALARM If the CO detector visual alert annunciator illuminates in flight press the TEST RESET button If the alert continues with the remote light staying ON proceed with the em...

Page 282: ... FAILURE INDICATION A failure of the CO sensor temperature sensor or the micro controller will result in the following failure indications The remote light will flash at an approximately rate of one flash each four seconds until the failure is cleared or power is removed from the unit ...

Page 283: ...S 8 3 8 4 GROUND HANDLING ROAD TRANSPORT 8 3 8 4 1 GROUND HANDLING WITHOUT TOW BAR 8 3 8 4 2 GROUND HANDLING WITH TOW BAR 8 3 8 4 3 PARKING 8 5 8 4 4 MOORING 8 7 8 4 5 JACKING 8 7 8 4 6 ALIGNMENT 8 7 8 4 7 ROAD TRANSPORT 8 8 8 5 CLEANING AND CARE 8 9 8 5 1 PAINTED SURFACES 8 9 8 5 2 CANOPY AND REAR DOOR 8 10 8 5 3 PROPELLER 8 10 8 5 4 ENGINE 8 10 8 5 5 INTERIOR SURFACES 8 11 8 6 DE ICING ON THE GR...

Page 284: ...RPLANE INSPECTION INTERVALS For maintenance work on engine and propeller the currently effective Operator s Manuals Service Instructions Service Letters and Service Bulletins of Lycoming and mt Propeller must be followed For airframe inspections the currently effective checklists manuals of the manufacturer must be followed CAUTION Unscheduled maintenance checks are required after Hard landings Pr...

Page 285: ...direction the tail section of the airplane should be pushed down until the nose wheel is clear of the ground This method can also be used to turn the airplane around its main landing gear 8 4 2 GROUND HANDLING WITH TOW BAR For pushing or pulling the airplane on the ground it is recommended to use the tow bar which is available from the manufacturer The tow bar is bent apart and engaged in the appr...

Page 286: ...Handling DA 40 AFM Page 8 4 Rev 8 01 Dec 2010 Doc 6 01 01 E NOTE When moving the airplane rearward the tow bar must be held firmly to prevent abrupt sideward deflection of the nose wheel ...

Page 287: ...manufacturer offers a control surfaces gust lock which can be used to block the primary controls It is recommended that the control surfaces gust lock be used when parking outdoors because otherwise the 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 control surfaces gust lock ...

Page 288: ...Handling DA 40 AFM Page 8 6 Rev 8 01 Dec 2010 Doc 6 01 01 E ...

Page 289: ...4 5 JACKING The DA 40 can be jacked at the two jackpoints located on the lower side of the fuselage s LH and RH root ribs as well as at the tail fin 8 4 6 ALIGNMENT For alignment push down on the tail section at the fuselage vertical tail junction until the nose wheel is clear of the ground With the nose wheel free the DA 40 can be turned around the main landing gear After turning the airplane int...

Page 290: ...elage movement during transportation 2 Wings For transportation both wings must be removed from the fuselage To avoid any damage the wings are stored in an upright position on the leading edge with the root rib area positioned on an upholstered profiled surface with a width of at least 400 mm 1 3 ft The outside wing area approximately 3 m 10 ft from the root rib area is placed on an upholstered pr...

Page 291: ...n a hangar for prolonged storage Moisture that has penetrated must be removed by storing the affected parts in a dry place and turning them over several times Dirt insects etc can be removed with water alone and if necessary with a mild detergent An automotive paint cleaner can be used for stubborn spots For best results clean the airplane after the day s flying is ended so that the dirt will not ...

Page 292: ...nd malfunctions during operation must be inspected by authorized personnel Surface The manufacturer uses PU paint or acrylic paint which is 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 Should doubts arise an appropriately rated inspector must be con...

Page 293: ...be cleaned using a soft dry cloth plastic surfaces should be wiped clean using a damp cloth without any cleaning agents The leather interior should be treated with leather sealer within 3 months since new and then at intervals of 3 to 6 months Clean the leather interior with an appropriate mild leather cleaning agent and a soft cleaning brush for leather Note that the acrylic glass windows transmi...

Page 294: ...cing Fluids Manufacturer Product Kilfrost TKS 80 Aeroshell Compound 07 Any source AL 5 DTD 406B De Icing Procedure 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 piece of cloth to wipe the airplane dry ...

Page 295: ...DA 40 AFM Supplements Doc 6 01 01 E Rev 8 01 Dec 2010 Page 9 1 CHAPTER 9 SUPPLEMENTS Page 9 1 INTRODUCTION 9 2 9 2 LIST OF SUPPLEMENTS 9 3 ...

Page 296: ... stated the procedures given in the 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 Chapter The Airplane Flight Manual contains exactly those Supplements which correspond to the installed equipment according to the Equipment Inventory of Section 6 5 ...

Page 297: ...II PS Engineering Inc 2 15 Mar 2005 9 9 A3 Transponder KT 76A Bendix King 1 20 Apr 2001 9 9 A4 GPS KLN 89B Bendix King 1 20 Apr 2001 9 9 A5 Course Deviation Indicator KI 208 Bendix King 1 20 Apr 2001 9 9 A6 GPS KLN 94 VFR Operation Bendix King 2 09 Sep 2001 9 9 A7 Audio Amplifier Intercom Marker Beacon Receiver KMA 28 Bendix King 1 20 Apr 2001 9 9 A8 VHF Communication Navigation Transceivers KX 15...

Page 298: ...CS 55A Bendix King 4 15 Mar 2005 9 9 A12 Transponder KT 76C Bendix King 2 15 Mar 2005 9 9 A13 Autopilot System KAP 140 Bendix King 2 15 Mar 2005 9 9 A14 GPS KLN 94 IFR Operation Bendix King 3 15 Mar 2005 9 9 A15 GPS Annunciation Control Unit MD 41 Mid Continent 2 15 Mar 2005 9 9 A16 Multifunction Display GPS KMD 150 Bendix King 0 20 Sep 2001 9 9 A17 COM NAV GPS GNS 430 Garmin 3 22 Jun 2005 9 9 A18...

Page 299: ...000 Insight 0 10 Oct 2001 9 9 A23 GPS Annunciation Unit MD 41 1488 1484 MID Continent 1 20 Dec 2002 9 9 A24 Stormscope WX 500 Goodrich 2 28 Feb 2003 9 9 A25 Audio Panel GMA 340 Garmin VFR 2 15 Mar 2005 9 9 A26 COM NAV GPS GNS 430 Garmin VFR 0 02 Aug 2002 9 9 A27 Ground Com 2 Switch 0 05 Apr 2002 9 9 A29 Transponder GTX 330 Garmin 0 25 Jun 2003 9 9 E1 Digital Chronometer LC 2 AstroTech 1 20 Apr 200...

Page 300: ...r 2005 9 9 E4 Digital Chronometer Model 803 Davtron 1 15 Mar 2005 9 9 E7 Ventilation Inlet Baffle 1 27 Apr 2005 9 9 O1 Use of the DA 40 as Tow Plane 1 28 Nov 2001 9 9 O2 Operation of the DA 40 with Winter Kit 0 26 Nov 2001 9 9 S1 Emergency Locator Transmitter Model E 01 ACK 2 15 Mar 2005 9 9 S2 Emergency Locator Transmitter JE2 NG Jolliet 0 01 Jun 2001 9 9 S4 ELT Artex ME 406 ACE 1 10 Apr 2007 9 9...

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