Diamond DA 42 Flight Manual Download

Page: 7 / 400

DA 42 AFM

Introduction

Rev.

No.

Reason

Chap-

ter

Page(s)

Date of

Revision

Approval

Verification

Date

Inserted

Signature

Doc. No. 7.01.05-E

Rev. 8

15-Dec-2017

Page 0 - 5

MÄM 42-

-174/a, -186,

-198/b, -206,

-240, -254,

-258/a,

OÄM 42-

-055/a,

-056/d,

-062, -065,

-066, -067,

-070, -074,

-082, -092,

-094, -095,

-099, -101,

-105, -112,

-116, -121,

-129,

corrections

all

except cover

page

15 Nov

2007

Revision

No. 5 of the

AFM Doc.

No.

7.01.05-E is

approved

under the

authority of

DOA No.

EASA.21J.

052

Summary of Contents for DA 42

Page 1: ......

Page 2: ...1 05 E NOTE This airplane flight manual is valid for DA42 airplanes with a KAP 140 or no autopilot system installed Refer to the airplane flight manual DA42 with Garmin GFC 700 OÄM 42 102 Doc No 7 01 06 E for airplanes with a Garmin Autopilot system installed ...

Page 3: ...ot must familiarize himself with the complete contents of this Airplane Flight Manual In the event that you have obtained your DIAMOND DA 42 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 4: ...e appearing at the bottom of the page If pages are revised which contain information valid for your particular serial number modification level of the airplane weighing data Equipment Inventory List of Supplements then this information must be transferred to the new pages in hand writing The cover pages of Temporary Revisions if applicable are inserted behind the cover page of this manual the foll...

Page 5: ...1 Dec 2004 2005 196 Ing Andreas Winkler for ACG 2 MÄM 42 034 elevator stop OÄM 42 060 T B coordinat Take off diagrams 0 4A 4B 5 6 7 0 3 0 5 0 7 0 8 0 9 4A 9 4B 25 5 11 5 12 6 18 7 7 28 Jan 2005 10 Feb 2005 Dipl Ing FH Manfred Reichel for DAI 3 FAA Certification MÄM 42 062 070 a 079 080 091 101 111 b TR MÄM 42 111 a 115 OÄM 42 053 056 057 059 079 Corrections all all 15 Oct 2005 25 Oct 2005 Ing Andr...

Page 6: ... OÄM 42 054 077 080 corrections 0 0 3 thru 0 10 30 Nov 2005 EASA A C Ø2618 20 Dec 2005 Ing Andreas Winkler for ACG 1 1 2 1 11 2 2 2 2 4 2 7 2 8 2 10 2 14 2 15 2 18 2 21 thru 2 23 2 26 2 27 2 32 3 3 30 3 31 3 32 3 38 0 16667 all 4A 1 thru 4A 40 4B 4B 2 4B 13 4B 25 4B 27 4B 30 thru 4B 34 5 all 5 1 thru 5 34 6 6 5 6 8 6 10 thru 6 14 6 16 6 20 7 7 1 7 2 7 40 thru 7 66 8 8 4 8 12 9 39692 ...

Page 7: ...oc No 7 01 05 E Rev 8 15 Dec 2017 Page 0 5 5 MÄM 42 174 a 186 198 b 206 240 254 258 a OÄM 42 055 a 056 d 062 065 066 067 070 074 082 092 094 095 099 101 105 112 116 121 129 corrections all all except cover page 15 Nov 2007 Revision No 5 of the AFM Doc No 7 01 05 E is approved under the authority of DOA No EASA 21J 052 ...

Page 8: ...7 01 05 E 6 MÄM 42 268 a 270 272 284 292 301 304 310 336 347 377 405 443 OÄM 42 053 d 054 d 056 e 074 a 106 a 107 d 108 a 109 a 111 a 158 116 a 125 127 130 141 142 145 146 a 175 188 195 205 208 VÄM 42 002 corrections all all except cover page 30 Apr 2011 Revision No 6 of the AFM Doc No 7 01 05 E is approved under the authority of DOA No EASA 21J 052 ...

Page 9: ...814 861 OÄM 42 055 d 056 f 094 a 107 f 111 b 158 a 246 119 178 185 215 252 253 259 279 280 corrections all all except cover page 30 Nov 2015 Revision No 7 of the AFM Doc No 7 01 05 E is approved under the authority of DOA No EASA 21J 052 8 OÄM 42 222 252 b 304 a corrections all all except cover page 15 Dec 2017 Revision No 8 of the AFM Doc No 7 01 05 E is approved under the authority of DOA No EAS...

Page 10: ...15 Dec 2017 0 14 15 Dec 2017 0 15 15 Dec 2017 0 16 15 Dec 2017 0 17 15 Dec 2017 0 18 15 Dec 2017 Ch Page Date 1 1 1 15 Dec 2017 1 2 15 Dec 2017 1 3 15 Dec 2017 1 4 15 Dec 2017 1 5 15 Dec 2017 1 6 15 Dec 2017 1 7 15 Dec 2017 1 8 15 Dec 2017 1 9 15 Dec 2017 1 10 15 Dec 2017 1 11 15 Dec 2017 1 12 15 Dec 2017 1 13 15 Dec 2017 1 14 15 Dec 2017 1 15 15 Dec 2017 1 16 15 Dec 2017 1 17 15 Dec 2017 1 18 15 ...

Page 11: ... 15 Dec 2017 appr 2 21 15 Dec 2017 appr 2 22 15 Dec 2017 appr 2 23 15 Dec 2017 appr 2 24 15 Dec 2017 appr 2 25 15 Dec 2017 appr 2 26 15 Dec 2017 appr 2 27 15 Dec 2017 appr 2 28 15 Dec 2017 Ch Page Date 2 appr 2 29 15 Dec 2017 appr 2 30 15 Dec 2017 appr 2 31 15 Dec 2017 appr 2 32 15 Dec 2017 appr 2 33 15 Dec 2017 appr 2 34 15 Dec 2017 appr 2 35 15 Dec 2017 appr 2 36 15 Dec 2017 appr 2 37 15 Dec 201...

Page 12: ... 35 15 Dec 2017 3 36 15 Dec 2017 3 37 15 Dec 2017 3 38 15 Dec 2017 3 39 15 Dec 2017 3 40 15 Dec 2017 3 41 15 Dec 2017 3 42 15 Dec 2017 3 43 15 Dec 2017 3 44 15 Dec 2017 3 45 15 Dec 2017 Ch Page Date 3 3 46 15 Dec 2017 3 47 15 Dec 2017 3 48 15 Dec 2017 3 49 15 Dec 2017 3 50 15 Dec 2017 3 51 15 Dec 2017 3 52 15 Dec 2017 3 53 15 Dec 2017 3 54 15 Dec 2017 3 55 15 Dec 2017 3 56 15 Dec 2017 3 57 15 Dec ...

Page 13: ...2017 4A 17 15 Dec 2017 4A 18 15 Dec 2017 4A 19 15 Dec 2017 4A 20 15 Dec 2017 4A 21 15 Dec 2017 4A 22 15 Dec 2017 4A 23 15 Dec 2017 4A 24 15 Dec 2017 4A 25 15 Dec 2017 4A 26 15 Dec 2017 4A 27 15 Dec 2017 4A 28 15 Dec 2017 4A 29 15 Dec 2017 Ch Page Date 4A 4A 30 15 Dec 2017 4A 31 15 Dec 2017 4A 32 15 Dec 2017 4A 33 15 Dec 2017 4A 34 15 Dec 2017 4A 35 15 Dec 2017 4A 36 15 Dec 2017 4A 37 15 Dec 2017 4...

Page 14: ...2017 4B 12 15 Dec 2017 4B 13 15 Dec 2017 4B 14 15 Dec 2017 4B 15 15 Dec 2017 4B 16 15 Dec 2017 4B 17 15 Dec 2017 4B 18 15 Dec 2017 4B 19 15 Dec 2017 4B 20 15 Dec 2017 4B 21 15 Dec 2017 4B 22 15 Dec 2017 4B 23 15 Dec 2017 4B 24 15 Dec 2017 4B 25 15 Dec 2017 4B 26 15 Dec 2017 4B 27 15 Dec 2017 4B 28 15 Dec 2017 Ch Page Date 4B 4B 29 15 Dec 2017 4B 30 15 Dec 2017 4B 31 15 Dec 2017 4B 32 15 Dec 2017 4...

Page 15: ...15 Dec 2017 5 12 15 Dec 2017 5 13 15 Dec 2017 5 14 15 Dec 2017 5 15 15 Dec 2017 5 16 15 Dec 2017 5 17 15 Dec 2017 5 18 15 Dec 2017 5 19 15 Dec 2017 5 20 15 Dec 2017 5 21 15 Dec 2017 5 22 15 Dec 2017 5 23 15 Dec 2017 5 24 15 Dec 2017 5 25 15 Dec 2017 5 26 15 Dec 2017 5 27 15 Dec 2017 5 28 15 Dec 2017 5 29 15 Dec 2017 Ch Page Date 5 5 30 15 Dec 2017 5 31 15 Dec 2017 5 32 15 Dec 2017 5 33 15 Dec 2017...

Page 16: ...15 Dec 2017 6 11 15 Dec 2017 6 12 15 Dec 2017 6 13 15 Dec 2017 6 14 15 Dec 2017 6 15 15 Dec 2017 6 16 15 Dec 2017 6 17 15 Dec 2017 6 18 15 Dec 2017 6 19 15 Dec 2017 6 20 15 Dec 2017 6 21 15 Dec 2017 6 22 15 Dec 2017 6 23 15 Dec 2017 6 24 15 Dec 2017 6 25 15 Dec 2017 6 26 15 Dec 2017 6 27 15 Dec 2017 6 28 15 Dec 2017 6 29 15 Dec 2017 Ch Page Date 6 6 30 15 Dec 2017 6 31 15 Dec 2017 6 32 15 Dec 2017...

Page 17: ...15 Dec 2017 7 23 15 Dec 2017 7 24 15 Dec 2017 7 25 15 Dec 2017 7 26 15 Dec 2017 7 27 15 Dec 2017 7 28 15 Dec 2017 7 29 15 Dec 2017 Ch Page Date 7 7 30 15 Dec 2017 7 31 15 Dec 2017 7 32 15 Dec 2017 7 33 15 Dec 2017 7 34 15 Dec 2017 7 35 15 Dec 2017 7 36 15 Dec 2017 7 37 15 Dec 2017 7 38 15 Dec 2017 7 39 15 Dec 2017 7 40 15 Dec 2017 7 41 15 Dec 2017 7 42 15 Dec 2017 7 43 15 Dec 2017 7 44 15 Dec 2017...

Page 18: ... 71 15 Dec 2017 7 72 15 Dec 2017 7 73 15 Dec 2017 7 74 15 Dec 2017 7 75 15 Dec 2017 7 76 15 Dec 2017 Ch Page Date 8 8 1 15 Dec 2017 8 2 15 Dec 2017 8 3 15 Dec 2017 8 4 15 Dec 2017 8 5 15 Dec 2017 8 6 15 Dec 2017 8 7 15 Dec 2017 8 8 15 Dec 2017 8 9 15 Dec 2017 8 10 15 Dec 2017 8 11 15 Dec 2017 8 12 15 Dec 2017 8 13 15 Dec 2017 8 14 15 Dec 2017 8 15 15 Dec 2017 8 16 15 Dec 2017 Ch Page Date 9 9 1 15...

Page 19: ...PROCEDURES 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 20: ...Introduction DA 42 AFM Page 0 18 Rev 8 15 Dec 2017 Doc No 7 01 05 E Intentionally left blank ...

Page 21: ...NGS CAUTIONS AND NOTES 1 6 1 4 DIMENSIONS 1 7 1 5 DEFINITIONS AND ABBREVIATIONS 1 9 1 6 UNITS OF MEASUREMENT 1 17 1 6 1 CONVERSION FACTORS 1 17 1 6 2 CONVERSION CHART LITERS US GALLONS 1 19 1 7 THREE VIEW DRAWING 1 20 1 8 G1000 AVIONICS SYSTEM 1 21 1 9 SOURCE DOCUMENTATION 1 24 1 9 1 ENGINE 1 24 1 9 2 PROPELLER 1 25 1 9 3 AVIONICS SYSTEM 1 25 ...

Page 22: ...s of the airplane may vary from serial number to serial number Therefore some of the information contained in this manual is applicable depending on the respective equipment and modification level 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 ...

Page 23: ...ent OÄM 42 070 9 yes 9 no Mission Power Supply System OÄM 42 074 a 9 yes 9 no Removable Fuselage Nose Cone OÄM 42 077 9 yes 9 no Operator Desk Full CFRP Version OÄM 42 111 9 yes 9 no Operator Desk CFRP Version with Aluminum Joint OÄM 42 111 a 9 yes 9 no Garmin GWX 68 Weather Radar OÄM 42 119 9 yes 9 no ECU Backup Battery OÄM 42 129 9 yes 9 no Exhaust End Pipe OÄM 42 130 9 yes 9 no DA 42 M IFR OÄM ...

Page 24: ...apping O28V273DA42 ECU Mapping O28V291DA42 and ECU Mapping O28V294DA42 is limited to TAE 125 02 99 engines MÄM 42 198 latest revision carried out NOTE The use of ECU Mapping R28V291DIA is limited to TAE 125 01 engines This Airplane Flight Manual must be kept on board the airplane at all times Its designated place is the side bag of the forward left seat The designated place for the Garmin G1000 Co...

Page 25: ...h degree of reliability which is required by the certification basis Nevertheless an engine failure is not completely impossible For this reason it is highly recommended for flights during the night on top under IMC or above terrain which is unsuitable for a landing to select flight times and flight routes such that reduced performance in case of single engine operation does not constitute a risk ...

Page 26: ...erning 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 dra...

Page 27: ... Overall Dimensions Span 13 42 m 44 0 ft 13 55 m 44 5 ft including ACL Length 8 56 m 28 ft 1 in Height 2 49 m 8 ft 2 in Wing Airfoil Wortmann FX 63 137 20 W4 Wing area 16 29 m 175 3 sq ft Mean aerodynamic chord 1 271 m 4 ft 2 in Aspect ratio 11 06 Dihedral 5 Leading edge sweep 1 Aileron Area total left right 0 66 m 7 1 sq ft ...

Page 28: ... ft Elevator area 0 66 m 7 1 sq ft Angle of incidence 1 1 relative to longitudinal axis of airplane Vertical Tail Area 2 43 m 26 2 sq ft Rudder area 0 78 m 8 4 sq ft Landing Gear Track 2 95 m 9 ft 8 in Wheelbase 1 735 m 5 ft 8 in Nose wheel 5 00 5 Main wheel 15x6 0 6 for details refer to the Airplane Maintenance Manual Doc No 7 02 01 latest revision ...

Page 29: ...abrupt controlsurface movement is not permissible above this speed vFE Maximum Flaps Extended Speed This speed must not be exceeded with the given flap setting vLO Maximum Landing Gear Operating Speed This speed may not be exceeded during the extension or retraction of the landing gear vLE Maximum Landing Gear Extended Speed This speed may not be exceeded if the landing gear is extended vmCA Minim...

Page 30: ...tentionally inoperative idle training purposes vx Best Angle of Climb Speed vy Best Rate of Climb Speed vYSE Best Rate of Climb Speed for one engine inoperative b Meteorological Terms ISA International Standard Atmosphere Conditions at which air is identified as an ideal dry gas The temperature at mean sea level is 15 C 59 F air pressure at MSL is 1 013 25 hPa 29 92 inHg the temperature gradient u...

Page 31: ... Altitude corrected for installation and instrument errors In this Airplane Flight Manual altimeter instrument errors are regarded as zero Wind The wind speeds which are shown as variables in the diagrams in this manual should be regarded as headwind or tailwind components of the measured wind c Flight Performance and Flight Planning AGL Above Ground Level Demonstrated Crosswind Component The spee...

Page 32: ...ich the airplane at a given mass must be operated DP Datum Plane an imaginary vertical plane from which all horizontal distances for center of gravity calculations are measured Empty Mass The mass of the airplane including unusable fuel all operating fluids and the maximum quantity of oil Maximum Take off Mass The maximum permissible mass for take off Maximum Landing Mass The highest mass for land...

Page 33: ...be used for flight Useful Load The difference between take off mass and empty mass e Engine ECU Engine Control Unit FADEC Full Authority Digital Engine Control RPM Revolutions per minute rotational speed of the propeller Engine starting fuel temperature Above this fuel temperature the engine may be started Take off fuel temperature Above this fuel temperature take off power setting is permitted ...

Page 34: ...TAXI MAP ACL Taxi Map Anti Collision Light FLOOD OXY Flood Light Oxygen System PFD Primary Flight Display ADC Air Data Computer AHRS Attitude Heading Reference System GEAR WRN ELEV LIMIT Landing Gear Annunciation Variable Elevator Stop GEAR Landing Gear Control RH MAIN BUS MFD Multi Function Display AH Artificial Horizon STALL WRN Stall Warning System FLAP Flap System LDG LT START Landing Light St...

Page 35: ...DIO Audio Panel AUTO PILOT Auto Pilot System Wx 500 Stormscope ADF Automatic Direction Finder DME Distance Measuring Equipment Wx RDR Weather Radar TAS Traffic Advisory System DATA LINK GDL 69A Data Link System LH ENG ECU BUS ECU BUS LH ECU Bus ECU B LH ECU B ECU A LH ECU A LH BUS ALT LH LH Alternator BATT Battery RH BUS ALT RH RH Alternator BATT Battery ...

Page 36: ...visory 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 EASA European Aviation Safety Agency EPU External Power Unit GIA Garmin Integrated Avionics GFRP Glass Fiber Reinforced Plastic JAR Joint Aviation Requirements JC VP Joint Certification Validation Procedure PCA...

Page 37: ...S 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 ...

Page 38: ...M Dimension SI Units US Units Conversion Page 1 18 Rev 8 15 Dec 2017 Doc No 7 01 05 E Intensity of electric current A ampères Electric charge battery capacity Ah ampère hours Electric potential V volts Time sec seconds ...

Page 39: ... 2 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 40: ...15 Dec 2017 Doc No 7 01 05 E 1 7 THREE VIEW DRAWING 2950 mm 9 ft 8 in 1 8 7 0 m m 6 f t 2 i n 13420 mm 44 ft 0 in 1735 mm 8560 mm 28 ft 1 in 2490 mm 8 ft 2 in 1950 mm 6 ft 5 in 2205 mm 7 ft 3 in 5 ft 8 in 13550 mm 44 5 ft including ACL ...

Page 41: ...r flight planning The audio panel is used for selection of radios for transmitting and listening intercom functions and marker beacon functions 3 The primary function of the VHF Communication portion of the G1000 is to enable external radio communication The primary function of the VOR ILS Receiver portion of the equipment is to receive and demodulate VOR Localizer and Glide Slope signals The prim...

Page 42: ...omplies with the equipment requirements of FAA AC 90 105 and meets the equipment performance and functional requirements to conduct RNP terminal departure and arrival procedures and RNP approach procedures without RF radius to fix legs RNP1 RNP APCH0 3 LNAV e The Garmin GNSS navigation system as installed in this airplane has been found to comply with the requirements for primary means of Class II...

Page 43: ...and not for penetrating severe weather Pulse type weather radar systems like the GWX 68 detect precipitation only not clouds or turbulence The display may indicate clear areas between intense returns but this does not necessarily mean it is safe to fly between them As installed on the DA 42 the Garmin GWX 68 has a demonstrated range of 160 nautical miles Refer to Garmin G1000 Pilot s Guide for the...

Page 44: ...ual and indicates the respective publisher However only the information given in the Airplane Flight Manual is valid 1 9 1 ENGINE Address Technify Motors GmbH Platanenstrasse 14 D 09356 St Egidien GERMANY Phone 49 37204 696 0 Fax 49 37204 696 2910 Website www technify de Documents TAE 125 01 Operation and Maintenance Manual or TAE 125 02 99 Operation and Maintenance Manual if MÄM 42 198 carried ou...

Page 45: ... 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 9 3 AVIONICS SYSTEM Address Garmin International Inc 1200 East 151st Street Olathe Kansas 66062 USA Phone 1 913 3978200 Fax 1 913 3978282 Website www garmin com Documents G1000 Cockpit Reference Guide P N 190 00406 latest effective issue G1000 Pilot s Guide P N 1...

Page 46: ...General DA 42 AFM Page 1 26 Rev 8 15 Dec 2017 Doc No 7 01 05 E Intentionally left blank ...

Page 47: ...2 12 2 6 1 WARNING CAUTION AND ADVISORY ALERTS ON THE G1000 2 12 2 6 2 OTHER WARNING ALERTS 2 15 2 7 MASS WEIGHT 2 16 2 8 CENTER OF GRAVITY 2 18 2 9 APPROVED MANEUVERS 2 19 2 10 MANEUVERING LOAD FACTORS 2 20 2 11 OPERATING ALTITUDE 2 21 2 12 FLIGHT CREW 2 21 2 13 KINDS OF OPERATION 2 21 2 14 FUEL 2 25 2 15 LIMITATION PLACARDS 2 27 2 16 OTHER LIMITATIONS 2 31 2 16 1 FUEL TEMPERATURE 2 31 2 16 2 BAT...

Page 48: ... Dec 2017 EASA approved Doc No 7 01 05 E 2 16 6 GARMIN G1000 AVIONICS SYSTEM 2 33 2 16 7 SMOKING 2 37 2 16 8 GROUND OPERATION 2 37 2 16 9 USE OF THE SUN VISORS 2 37 2 16 10 STRUCTURAL TEMPERATURE 2 37 2 16 11 GARMIN GWX 68 WEATHER RADAR OPERATION 2 38 ...

Page 49: ...FlightManualprovidesoperatinglimitations instrumentmarkings and placards necessary for the safe operation of the airplane its powerplants standard systems and standard equipment The limitations included in this Chapter are approved WARNING Operation of the airplane outside of the approved operating limitations is not permissible ...

Page 50: ...4 incorporated above 1468 kg 3236 lb up to 1700 kg 3748 lb 124 KIAS 1250 kg 2756 lb to 1468 kg 3236 lb 121 KIAS vFE Max flaps extended speed LDG 111 KIAS Donot exceedthese speeds with the given flap setting APP 137 KIAS vLO Max landing gear operating speed Extension vLOE 194 KIAS Do not operate the landing gear above this speed Retraction vLOR 156 KIAS vLE Max landing gear extended speed 194 KIAS ...

Page 51: ... No 7 01 05 E Rev 8 15 Dec 2017 EASA approved Page 2 5 vNO Max structural cruising speed 155 KIAS Do not exceed this speed except in smooth air and then only with caution vNE Never exceed speed in smooth air 194 KIAS Do not exceed this speed in any operation ...

Page 52: ...icance White arc 56 111 KIAS Operatingrange with flaps fully extended Green arc 62 155 KIAS Normal operating range Yellow arc 155 194 KIAS Caution range Only in smooth air Blue radial 82 KIAS Best rate of climb speed single engine Red radial 68 KIAS Minimum control speed single engine Red radial 194 KIAS Maximum speed for all operations vNE ...

Page 53: ...r RPM Maximum 2300 RPM Maximum overspeed 2500 RPM max 20 sec e Engine power Max take off power 99 kW 135 DIN hp at 2300 RPM 100 load Max continuous power 99 kW 135 DIN hp at 2300 RPM 100 load f Fuel temperature TAE 125 01 TAE 125 02 99 MÄM 42 198 carried out Minimum 30 o C 30 o C Maximum 75 o C 75 o C g Oil pressure indicated values are corrected for pressure altitude Minimum 1 0 bar Maximum 6 5 b...

Page 54: ... temperature Maximum 120 C k Coolant temperature TAE 125 01 TAE 125 02 99 MÄM 42 198 carried out Minimum 32 o C 30 o C Maximum 105 o C 105 o C l Voltage Minimum 24 1 V Maximum 32 0 V m Amperage Maximum 60 A n Propeller manufacturer mt Propeller o Propeller designation MTV 6 A C F CF 187 129 p Propeller diameter 187 cm 6 ft 2 in q Prop pitch angle 0 75 R 12 low pitch 15 start lock position 81 feath...

Page 55: ...ELL SPIRAX S4 G 75W 90 SHELL SPIRAX S6 GXME 75W 80 APT GL 4 Additionally if MÄM 42 198 is incorporated CENTURION Gearbox Oil N1 SHELL SPIRAX S6 ATF ZM API GL 4 u Coolant Water Cooler protection BASF Glysantin Protect Plus G48 1 1 The freezing point of the coolant is 36 C 32 8 F CAUTION If the coolant or gearbox oil level is low the reason must be determined and the problem must be corrected by aut...

Page 56: ... RPM Oil pressure below 1 0 bar 1 0 to 2 3 bar 2 3 to 5 2 bar 5 2 to 6 5 bar above 6 5 bar Oil temp below 32 C 32 to 50 C 50 to 125 C 1 50 to 130 C 2 125 to 140 C 1 131 to 140 C 2 above 140 C Coolant temp below 32 C 32 to 60 C 60 to 96 C 1 60 to 101 C 2 96 to 105 C 1 102 to 105 C 2 above 105 C Gearbox temp up to 115 C 115 to 120 C above 120 C Load 0 to 100 Fuel temp below 30 C 30 to 22 C 1 30 to 4...

Page 57: ... range RPM up to 2300 RPM above 2300 RPM Oil pressure below 1 0 bar 1 0 to 2 3 bar 2 3 to 5 8 bar 5 8 to 6 5 bar above 6 5 bar Oil temp below 30 C 30 to 50 C 50 to 130 C 131 to 140 C above 140 C Coolant temp below 30 C 30 to 60 C 60 to 101 C 102 to 105 C above 105 C Gearbox temp up to 115 C 115 to 120 C above 120 C Load 0 to 100 Fuel temp below 30 C 30 to 4 C 5 to 69 C 70 to 75 C above 75 C Ammete...

Page 58: ... the Warning Alerts on the G1000 Warning Alerts red Meaning Cause WARNING One of the warnings listed below is being indicated L R ENG TEMP Left Right engine coolant temperature is in the upper red range too high 105 C L R OIL TEMP Left Right engine oil temperature is in the upper red range too high 140 C L R OIL PRES Left Right engine oil pressure is in the lower red range too low 1 0 bar L R FUEL...

Page 59: ...guidance ATTITUDE FAIL The display system is not receiving attitude reference information from the AHRS AIRSPEED FAIL The display system is not receiving airspeed input from the air data computer ALTITUDE FAIL The display system is not receiving altitude input from the air data computer VERT SPEED FAIL The display system is not receiving vertical speed input from the air data computer HDG The disp...

Page 60: ...t procedure during the before take off check L R FUEL LOW Left Right main tank fuel quantity is low L R ALTN FAIL Left Right engine alternator has failed L R VOLTS LOW Left Right bus voltage is less than 25 Volts L R COOL LVL Left Right engine coolant level is low PITOT FAIL Pitot heat has failed PITOT HT OFF Pitot heat is OFF STAL HT FAIL Stall warning heat has failed STAL HT OFF Stall warning he...

Page 61: ...o main tank is in progress PFD FAN FAIL Cooling fan for the PFD is inoperative MFD FAN FAIL Cooling fan for the MFD is inoperative GIA FAN FAIL Cooling fan for the GIAs is inoperative 2 6 2 OTHER WARNING ALERTS Warning Alerts on the Instrument Panel GEAR UNSAFE WARNING LIGHT red Illuminates if the landing gear is neither in the final up nor in the down locked position Audible Warning Alerts GEAR R...

Page 62: ...88 and OÄM 42 195 are carried out see Note below 1730 kg 3814 lb Maximum landing mass see NOTE below 1700 kg 3748 lb Maximum landing mass if OÄM 42 195 is carried out 1785 kg 3935 lb Max load in nose baggage compartment in fuselage nose 30 kg 66 lb Max load in cabin baggage compartment behind rear seats 45 kg 100 lb Max load in baggage extension behind cabin baggage compartment 18 kg 40 lb Max loa...

Page 63: ...M 8 kg MTOM 18 lb is approved At the time of lift off the maximum permitted take off mass must not be exceeded NOTE If MÄM 42 088 is carried out and OÄM 42 195 is not carried out a landing with a mass between 1700 kg 3748 lb and 1785 kg 3935 lb constitutes an abnormal operating procedure NOTE For a zero fuel mass above 1650 kg 3638 lb a structural temperature limit has been established which must ...

Page 64: ...figure in Section 6 2 Center of Gravity Limitations The center of gravity CG position for flight conditions must be between the following limits Most forward flight CG 2 35 m 92 52 in aft of Datum Plane at 1250 kg 2756 lb 2 35 m 92 52 in aft of Datum Plane at 1468 kg 3236 lb 2 40 m 94 49 in aft of Datum Plane at max take off mass see Section 2 7 linear variation in between Most rearward flight CG ...

Page 65: ...ers 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 Stalling with asymmetric power or one engine inoperative is not perm...

Page 66: ...ne CAUTION Avoidextendednegativeg loads duration Extended negative g loads can cause propeller control problems and engine surging at vA at vNE With Flaps in APP or LDG Position Positive 3 8 3 8 2 0 Negative 1 52 0 WARNING Exceeding the maximum structural load factors will lead to overstressing of the airplane CAUTION Exceeding the maximum powerplant load factors and time limits listed below will ...

Page 67: ... the appropriate equipment night flights according to Visual Flight Rules NVFR With the appropriate equipment flights according to Instrument Flight Rules IFR Take off and landing on paved surfaces Take off and landing on grass surfaces If OÄM 42 054 is carried out flight into known or forecast icing conditions Refer to Supplement S03 latest revision Flights into known thunderstorms are prohibited...

Page 68: ... on G1000 PFD or backup Magnetic compass 1 Headset used by pilot in command Vertical speed indicator VSI Attitude gyro artificial horizon on G1000 PFD or backup Turn bank indicator on G1000 PFD Directional gyro VHF radio COM with speaker and microphone Chronometer with indication of hours minutes and seconds VOR receiver Transponder XPDR Mode A and Mode C GPS receiver part of G1000 Second airspeed...

Page 69: ...ts Doc No 7 01 05 E Rev 8 15 Dec 2017 EASA approved Page 2 23 Engine Instru ments Fuel qty 2x Oil press 2x Oil temp 2x Coolant temp 2x Coolant level indicator 2x Gearbox temp 2x Load 2x Prop RPM 2x Fuel temp left right tank Ammeter Voltmeter Lighting Position lights Strobe lights anti collision lights Landing light Instrument lighting Flood light Flashlight ...

Page 70: ...A approved Doc No 7 01 05 E Other Opera tional Mini mum Equip ment Stall warning system Variable elevator stop Alternate means for fuel quantity indication see Section 7 9 Safety belts for each occupied seat Airplane Flight Manual Pitot heating system Alternate static valve Emergency battery for backup attitude gyro and flood light NOTE A list of approved equipment can be found in Chapter 6 ...

Page 71: ... TS 1 Ukraine GSTU 320 00 1U9943011 99 and blends of the above listed Jet Fuel grades Diesel Fuel Only if MÄM 42 037 is incorporated Diesel EN 590 and blends of the above listed Jet Fuel grades and Diesel CAUTION Limitations for DA 42 registered and or operated in the following countries Indonesia Malaysia Use of Diesel Fuel is NOT approved CAUTION If the airplane is operated with Diesel Fuel or a...

Page 72: ...Fuel or blends of Diesel Fuel with Jet Fuel Refer to Section 2 16 1 NOTE Use only uncontaminated fuel from reliable sources Main Tanks Auxiliary Tanks if installed Total US gal liter US gal liter US gal liter Total fuel quantity 2 x 26 0 2 x 98 4 2 x 13 7 2 x 52 0 2 x 39 7 2 x 150 4 Usable fuel 2 x 25 0 2 x 94 6 2 x 13 2 2 x 50 0 2 x 38 2 2 x 144 6 Max permissible difference LH RH 5 0 18 9 ...

Page 73: ...HT INTO KNOWN OR FORECAST ICING CONDITIONS ALL AEROBATIC MANEUVERS INCLUDINGSPINNINGAREPROHIBITED FORFURTHEROPERATIONALLIMITATIONS REFER TO THE AIRPLANE FLIGHT MANUAL MANEUVERING SPEED VA 126 KIAS ABOVE 1542 KG 3400 LB VA 120 KIAS UP TO 1542 KG 3400 LB Neither MÄM 42 088 nor OÄM 42 054 incorporated THIS AIRPLANE MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANE FLIGHT MANUAL IT CANBEOPERATED IN...

Page 74: ...max usable fuel main tank 2 x 25 US gal auxiliary tank 2 x 13 US gal max difference LH RH main tank 5 US gal WARNING APPROVED FUEL JET A1 On the Instrument Panel Next to the Fuel Quantity Indication a Standard Tank b Auxiliary Tank if installed If MÄM 42 037 Is Carried Out on the Garmin G1000 MFD Next to the Fuel Temperature Indication a Next to Each of the Two Fuel Filler Necks b In Addition Next...

Page 75: ...5 E Rev 8 15 Dec 2017 EASA approved Page 2 29 OIL Shell Helix Ultra 5W 30 or see AFM UP Flaps APP 137 KIAS LDG 111 KIAS In Each Cowling on the Door for the Oil Filler Neck Next to the Flap Selector Switch In the Cabin on the Left Fuselage Sidewall ...

Page 76: ... Cabin Baggage Compartment In the Nose Baggage Compartment Beside the Door Locking Device Installed in the Passengers Door On the Right Hand Side of the Instrument Panel Above the Circuit Breakers Max Baggage 30 kg 66 lb EMERGENCY EXIT The keylock must be unlocked during flight ______ NO SMOKING ______ ...

Page 77: ...ed Diesel Fuel Blends of Diesel Fuel with Jet Fuel or unknown fuel grade Engine starting fuel temperature min 5 C 23 F Take off fuel temperature min 5 C 41 F Maximum fuel temperature 75 C 167 F 2 16 2 BATTERY CHARGE Taking off for a Night VFR or IFR flight with an empty battery is not permitted The use of an external power supply for engine starting with an empty airplane battery is also not permi...

Page 78: ...g on of electronic equipment other than that which is part of the equipment of the airplane is not permitted as it could lead to interference with the airplane s avionics Examples of undesirable items of equipment are Mobile phones Remote radio controls Video screens employing CRTs Minidisc recorders in record mode This list is not exhaustive The use of laptop computers including those with CD ROM...

Page 79: ...t version 3 If MÄM 42 198 TAE 125 02 99 engines refer to Section 1 1 is implemented the G1000 must utilize the software Garmin P N 010 00370 15 or later approved software in accordance with the Mandatory Service Bulletin DAI MSB42 008 latest version Software Part Number Approved Version Function System for approved version see DAI MSB 42 008 latest version 010 00370 Manifest 006 B0093 GPS1 GPS2 00...

Page 80: ...the G1000 GPS receiver is prohibited unless the pilot verifies the currency of the database or verifies each selected way point for accuracy by reference to current approved data 5 Instrument approach navigation predicated upon the G1000 GPS receiver must be accomplished in accordance with approved instrument approach procedures that are retrieved from the GPS equipment database The GPS equipment ...

Page 81: ...mation only Use of VNAV information for Instrument Approach Procedures does not guarantee step down fix altitude protection or arrival at approach minimums innormal position to land f RNAV GPS approaches must be conducted utilizing the GPS sensor g RNP RNAV operations are not authorized except as noted in Chapter 1 of this AFM 6 If not previously defined the following default settings must be made...

Page 82: ...e MFD must be in a non Heading Up orientation 8 If the CDI source is changed when the autopilot is engaged in NAV mode the autopilot lateral mode will revert to ROLL ATTITUDE mode and NAV mode must be manually reselected by the pilot 9 The fuel quantity fuel required and fuel remaining functions on the Fuel Page displayed when pushing the FUEL button as shown in Section 7 13 of the FMS are supplem...

Page 83: ...installed OÄM 42 101 or OÄM 42 142 may only be used during cruise During all other phases of flight the sun visors must be locked in the fully upward position 2 16 10 STRUCTURAL TEMPERATURE CAUTION The max zero fuel mass of 1650 kg 3638 lb may only be exceeded if OÄM 42 188 is carried out If the zero fuel mass exceeds 1650 kg 3638 lb the maximum permissible structural temperature of 55 C 131 F mus...

Page 84: ...PERATION WARNING The Garmin GWX 68 Weather Radar System if installed must not be operated on ground If the system is transmitting it may result in bodily injury if persons are within the minimum safe distance of 2 8 m 9 16 ft Never operate the radar in a hangar or other enclosure as radiation can be reflected throughout the area ...

Page 85: ...3 6 3 2 1 WARNINGS GENERAL 3 6 3 2 2 L R ENG TEMP 3 6 3 2 3 L R OIL TEMP 3 8 3 2 4 L R OIL PRES 3 9 3 2 5 L R GBOX TEMP 3 10 3 2 6 L R FUEL TEMP 3 11 3 2 7 L R ALTN AMPS 3 12 3 2 8 L R ENG FIRE 3 12 3 2 9 L R STARTER 3 13 3 2 10 DOOR OPEN 3 13 3 3 G1000 SYSTEM WARNINGS 3 14 3 3 1 RED X 3 14 3 3 2 POSN ERROR 3 14 3 3 3 ATTITUDE FAIL 3 14 3 3 4 AIRSPEED FAIL 3 14 3 3 5 ALTITUDE FAIL 3 15 3 3 6 VERT ...

Page 86: ... 5 4 UNFEATHERING RESTARTING THE ENGINE IN FLIGHT 3 25 3 5 5 ENGINE FAILURE DURING TAKE OFF 3 33 3 5 6 ENGINE FAILURES IN FLIGHT 3 36 3 5 7 LANDING WITH ONE ENGINE INOPERATIVE 3 39 3 5 8 GO AROUND BALKED LANDING WITH ONE ENGINE INOPERATIVE 3 42 3 5 9 FLIGHT WITH ONE ENGINE INOPERATIVE 3 45 3 6 LANDING GEAR SYSTEM FAILURES 3 46 3 6 1 LANDING GEAR UNSAFE WARNING 3 46 3 6 2 MANUAL EXTENSION OF THE LA...

Page 87: ... IN FLIGHT 3 58 3 9 OTHER EMERGENCIES 3 59 3 9 1 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN 3 59 3 9 2 UNLOCKED DOORS 3 60 3 9 3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM 3 62 3 9 4 UNINTENTIONAL FLIGHT INTO ICING 3 64 3 9 5 FUEL SUPPLY FAILURE 3 65 3 9 6 RECOVERY FROM AN UNINTENTIONAL SPIN 3 66 3 9 7 EMERGENCY DESCENT 3 67 3 9 8 EMERGENCY EXIT 3 67 NOTE Procedures for uncritical syst...

Page 88: ...over them in this 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...

Page 89: ...control speed air vmCA 68 KIAS One engine inoperative speed for best rate of climb vYSE 82 KIAS 3 1 3 SELECTING EMERGENCY FREQUENCY In an in flight emergency depressing and holding the Com transfer button º on the G1000 for 2 seconds will tune the emergency frequency of 121 500 MHz If the display is available it will also show it in the Active frequency window ...

Page 90: ...d by the crew 3 2 2 L R ENG TEMP L R ENG TEMP Left Right engine coolant temperature is in the upper red range too high above 105 C Coolant temperatures above the limit value of 105 C can lead to a total loss of power due to engine failure Check G1000 for L R COOL LVL caution message low coolant level L R COOL LVL caution message not displayed During Climb Reduce power on affected engine by 10 or m...

Page 91: ...bovementionedprocedurecandecreasethetemperature s This might not be the case if the coolant temperature does not return to the green range In this case perform a precautionary landing on the nearest suitable airfield Prepare for an engine failure in accordance with 3 5 6 ENGINE FAILURES IN FLIGHT END OF CHECKLIST L R COOL LVL caution message displayed Reduce power on affected engine Expect loss of...

Page 92: ... lead to a total loss of power due to engine failure Check oil pressure If the oil pressure is outside of the green range lower limit Reduce power on affected engine Expect loss of engine oil WARNING A further increase in oil temperature must be expected Prepare for an engine failure in accordance with 3 5 6 ENGINE FAILURES IN FLIGHT If the oil pressure is within the green range Reduce power on af...

Page 93: ...the green range In this case perform a precautionary landing on the nearest suitable airfield Prepare for an engine failure in accordance with 3 5 6 ENGINE FAILURES IN FLIGHT END OF CHECKLIST 3 2 4 L R OIL PRES L R OIL PRES Left Right engine oil pressure is in the lower red range too low below 1 bar Oil pressures below the limit value of 1 bar can lead to a total loss of power due to engine failur...

Page 94: ...ed engine Increase airspeed CAUTION At high ambient temperature conditions and or at low airspeeds with high power settings it can be assumed that there is no technical defect in the gearbox and that the above mentioned procedure will decrease the temperature s This might not be the case if the gearbox temperature does not return to the green range In this case perform a precautionary landing on t...

Page 95: ...ION At high ambient temperature conditions and or at low airspeeds with high power settings and low fuel quantities it can be assumed that the above mentioned procedure will decrease the temperature s If the fuel temperature does not return to the green range perform a precautionary landing on the nearest suitable airfield NOTE Increased fuel temperature can occur when the fuel quantity in the mai...

Page 96: ... high above 60 amps Proceed according to 3 7 2 HIGH CURRENT 3 2 8 L R ENG FIRE L R ENG FIRE Left Right engine fire detected Engine fire can lead to a total loss of power due to engine failure as well as severe structural damage Proceed according to the following procedures as applicable 3 8 1 ENGINE FIRE ON GROUND 3 8 2 ENGINE FIRE DURING TAKE OFF 3 8 3 ENGINE FIRE IN FLIGHT ...

Page 97: ... Page 3 13 3 2 9 L R STARTER L R STARTER Left Right engine starter is engaged Proceed according to 3 7 3 STARTER MALFUNCTION 3 2 10 DOOR OPEN DOOR OPEN Front and or rear canopy and or baggage door are is not closed and locked Proceed according to 3 9 2 UNLOCKED DOORS ...

Page 98: ...ce Revert to the G1000 VOR ILS receivers or an alternate means of navigation other than the G1000 GPS receivers 3 3 3 ATTITUDE FAIL ATTITUDE FAIL The display system is not receiving attitude reference information from the AHRS accompanied by the removal of sky ground presentation and a red X over the attitude area Revert to the standby attitude indicator 3 3 4 AIRSPEED FAIL AIRSPEED FAIL The displ...

Page 99: ...VERT SPEED FAIL The display system is not receiving vertical speed input from the air data computer accompanied by a red X through the vertical speed display Determine vertical speed based on the change of altitude information 3 3 7 HDG HDG The display system is not receiving valid heading input from the AHRS accompanied by a red X through the digital heading display Revert to the emergency compas...

Page 100: ...play Reversionary Mode If the PFD and MFD have automatically entered reversionary mode use the following procedure a DISPLAY BACKUP Button on Audio Panel PUSH Button will be OUT NOTE After automatic entry of reversionary mode the pilot must press the DISPLAY BACKUP button on the audio panel After the DISPLAY BACKUP button has been pushed the system will remain in reversionary mode even if the prob...

Page 101: ...tton to the OUT position END OF CHECKLIST 3 4 3 AHRS FAILURE NOTE A failure of the Attitude and Heading Reference System AHRS is indicated by a removal of the sky ground presentation and a red X and a yellow AHRS FAILURE shown on the PFD The digital heading presentation will be replaced with a yellow HDG and the compass rose digits will be removed The course pointer will indicate straight up and c...

Page 102: ...DC FAILURE NOTE Complete loss of the Air Data Computer is indicated by a red X and yellow text over the airspeed altimeter vertical speed TAS and OAT displays Some FMS functions such as true airspeed and wind calculations will also be lost 1 Use standby airspeed indicator and altimeter END OF CHECKLIST ...

Page 103: ...formation Erroneous indications may be determined by comparing a display with other displays and other system information 1 Set power based on throttle lever position engine noise and speed 2 Monitor other indications to determine the health of the engine 3 Use known power settings and performance data refer to 5 3 2 FUEL FLOW DIAGRAM for approximate fuel flow values 4 Use other system information...

Page 104: ...r displays or system information 1 If an annunciator appears treat it as if the condition exists Refer to Chapter 3 EMERGENCY PROCEDURES or Chapter 4B ABNORMAL OPERATING PROCEDURES 2 If a display indicates an abnormal condition but no annunciator is present use other system information such as engine displays GPS fuel quantity and flow to determine if the condition exists If it cannot be determine...

Page 105: ...THE INOPERATIVE ENGINE NOTE One engine inoperative means an asymmetric loss of thrust resulting in uncommanded yaw and roll in direction of the so called dead engine withcoordinatedcontrols Tohandle this situation it is vital to maintain directional control by mainly rudder and additional aileron input The following mnemonic can help to identify the failed engine Dead foot dead engine This means t...

Page 106: ... situation the following attempts can be made to restore engine power prior to securing the engine CAUTION Once the engine has been shut down for longer than 30 seconds it can only be restarted below 8000 ft TAE 125 02 99 engine or 6000 ft TAE 125 01 engine pressure altitude Proceed in accordance with 3 5 4 UNFEATHERING RESTARTINGTHEENGINEINFLIGHT 1 POWER lever IDLE NOTE If the loss of power was d...

Page 107: ...ontinue your flight but have the proper function of the restrainer locks checked prior to next flight 5 ECU SWAP ECU B NOTE If the swap to ECU B has restored engine power land as soon as possible If selecting ECU B does not solve the problem switch back to AUTOMATIC in order to maintain the engine control system redundancy 6 Circuit breakers check reset if necessary NOTE If resetting the circuit b...

Page 108: ...t shut down an engine with the FUEL SELECTOR valve The high pressure fuel pump can otherwise be damaged Securing the feathered engine 3 Alternator inoperative engine OFF 4 FUEL SELECTOR inoperative engine OFF NOTE The remaining fuel in the tank of the failed engine can be used for the remaining engine to extend range and maintain lateral balance by setting its FUEL SELECTOR in the CROSSFEED positi...

Page 109: ...thered propeller causes increased drag and reduces increases climb sink rate up to 200 ft min If the reason of the engine failure can be identified as the result of an improper handling by the pilot and there is no indication of malfunction or engine fire a restart may be attempted Refer to 3 5 2 ENGINE TROUBLE SHOOTING to check for possible causes If TAE 125 01 engines are installed NOTE Restarti...

Page 110: ... at airspeeds of 80 KIAS and above To avoid propeller overspeeds shortly after unfeathering and restarting maintain airspeeds below 120 KIAS 7 Starter affected engine engage if propeller does not start windmilling by itself CAUTION Do not engage the starter if the propeller is windmilling This might damage the starter CAUTION After the engine has started the power lever should be set to a moderate...

Page 111: ... the first attempt do not carry out further attempts to feather the propeller to avoid further loss of altitude NOTE In order to feather the propeller the propeller RPM must be above 1800 RPM Below 1800 RPM the centrifugal latches of the start locks will not disengage and the propeller will keep wind milling 9 Airspeed 82 KIAS 10 POWER lever affected engine 100 11 ENGINE MASTER affected engine che...

Page 112: ... INOPERATIVE NOTE The remaining fuel in the tank of the failed engine can be used for the remaining engine to extend range and maintain lateral balance by setting the fuel selector of the remaining engine to the CROSSFEED position If one of the power levers is set to low settings the landing gear warning horn is activated Set the power lever of the secured engine forward as required to mute the wa...

Page 113: ...low 90 KIAS 2 POWER lever affected engine IDLE 3 FUEL SELECTOR affected engine check ON 4 ALTERNATE AIR as required 5 Alternator ON 6 ENGINE MASTER affected engine ON 7 Starter affected engine engage until propeller speed reaches 500 RPM if propeller does not start windmilling by itself CAUTION If the dual mass flywheel is installed disengaging the starter below 500 RPM propeller speed might damag...

Page 114: ...gine IDLE 11 FUEL SELECTOR affected engine check ON 12 ALTERNATE AIR as required 13 Alternator ON 14 ENGINE MASTER affected engine ON CAUTION After the engine has started the power lever should be set to a moderate power setting until engine temperatures have reached the green range 15 Circuit breakers check Feathering the engine if engine does not start WARNING One attempt to feather the engine r...

Page 115: ...and the propeller will keep wind milling Increase the airspeed swiftly to minimize altitude loss In case of shaking rotation continue to accelerate the airplane until 1800 RPM is reached 16 Airspeed 82 KIAS 17 POWER lever affected engine 100 18 ENGINE MASTER affected engine check ON 19 Airspeed increase to propeller wind milling speed of above 1800 RPM 20 ENGINE MASTER affected engine OFF 21 Airsp...

Page 116: ... for the remaining engine to extend range and maintain lateral balance by setting the fuel selector of the remaining engine to the CROSSFEED position If one of the power levers is set to low settings the landing gear warning horn is activated Set the power lever of the secured engine forward as required to mute the warning horn END OF CHECKLIST ...

Page 117: ...e During Ground Roll Abort take off 1 POWER lever IDLE BOTH 2 Rudder maintain directional control 3 Brakes as required CAUTION If sufficient time is remaining the risk of fire in the event of a collision with obstacles can be reduced as follows 4 ENGINE MASTER both OFF 5 FUEL SELECTOR both OFF 6 ELECT MASTER OFF END OF CHECKLIST ...

Page 118: ...f is not recommended if the steady rate of climb according to Section 5 3 9 ONE ENGINE INOPERATIVECLIMBperformanceislessthan3 3 Under certain combinations of ambient conditions such as turbulence crosswinds and wind shear as well as pilot skill the resulting climb performance may nevertheless be insufficient to continue the take off successfully Therefore a continued take off with a failed engine ...

Page 119: ... FEATHERING PROCEDURE Continue according to Section 3 5 9 FLIGHT WITH ONE ENGINE INOPERATIVE and land as soon as possible according to 3 5 7 LANDING WITH ONE ENGINE INOPERATIVE If the situation allows you may climb to a safe altitude for troubleshooting 3 5 2 ENGINE TROUBLESHOOTING in order to try to restore engine power END OF CHECKLIST ...

Page 120: ... Power levers retard as required to maintain directional control 3 Airspeed vYSE 82 KIAS above vmCA 68 KIAS as required 4 Operative engine increase power as required if directional control has been re established Establish minimum zero sideslip condition approx half ball towards good engine 3 to 5 bank 5 Inoperative engine Secure according to 3 5 3 ENGINE SECURING FEATHERING PROCEDURE Continue acc...

Page 121: ...en established Establish minimum zero sideslip condition approx half ball towards good engine 3 to 5 bank 4 Inoperative engine Secure according to 3 5 3 ENGINE SECURING FEATHERING PROCEDURE Continue according to Section 3 5 9 FLIGHT WITH ONE ENGINE INOPERATIVE and land as soon as possible according to Section 3 5 7 LANDING WITH ONE ENGINE INOPERATIVE If the situation allows you may climb to a safe...

Page 122: ...inimum zero sideslip condition approx half ball towards good engine 3 to 5 bank 4 Inoperative engine Secure according to 3 5 3 ENGINE SECURING FEATHERING PROCEDURE Continue according to Section 3 5 9 FLIGHT WITH ONE ENGINE INOPERATIVE and land as soon as possible according to Section 3 5 7 LANDING WITH ONE ENGINE INOPERATIVE If the situation allows you may climb to a safe altitude for troubleshoot...

Page 123: ...ition 1 Adjustable backrests if installed adjust to the upright position described by a placard on the roll over bar and verify proper fixation 2 Safety harnesses check fastened tightened 3 Landing light as required 4 Gear warning horn check function Operative engine 5 FUEL SELECTOR check ON CROSSFEED as required Inoperative engine 6 Engine check secured feathered according to 3 5 3 ENGINE SECURIN...

Page 124: ...REF FLAPS UP 82 KIAS vREF FLAPS APP 76 KIAS vREF FLAPS LDG at 1785 kg 3935 lb 86 KIAS vREF FLAPS UP 82 KIAS vREF FLAPS APP 78 KIAS vREF FLAPS LDG WARNING One engine inoperative approaches for landing with flap settings of more than flaps UP are not recommended unless a safe landing is assured Making the field Higher flap settings increase the loss of altitude during the transition to a one engine ...

Page 125: ... NOTE Higherapproachspeedsresultin asignificantlylongerlanding distance during flare CAUTION In conditions such as e g strong wind danger of wind shear or turbulence a higher approach speed should be selected Perform normal touchdown and deceleration on ground END OF CHECKLIST ...

Page 126: ...d gear UP refer to 5 3 9 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE Under certain combinations of ambient conditions such as turbulence cross wind and windshear as well as pilot skill the resulting climb performance may nevertheless be insufficient for a successful go around balked landing 1 POWER lever MAX as required 2 Rudder maintain directional control 3 Airspeed vYSE 82 KIAS as required 4 Landi...

Page 127: ...required NOTE If landing is performed off airfield depending on the surface condition it may be beneficial to land with the gear UP Note that the energy absorbing function of the landing gear is lost in such cases NOTE Extending the gear and extending the flaps to LDG will increase drag and incur a high sink rate Only when the landing area can be reached safely landing with flaps LDG is advisable ...

Page 128: ... DOWN check 3 green 11 ELECT MASTER OFF 12 Touch down lowest practical speed If landing with landing gear retracted 10 LANDING GEAR UP 11 Touch down lowest practical speed Immediately after touchdown 12 ELECT MASTER OFF NOTE If the ELECT MASTER is switched OFF before touchdown the landing gear will extend slowly END OF CHECKLIST ...

Page 129: ...y 3 Fuel quantity monitor continuously 4 FUEL SELECTOR remaining engine set CROSSFEED or ON so as to keep fuel quantity laterally balanced NOTE If the FUEL SELECTOR is set on CROSSFEED the engine will be supplied with fuel from the main tank on the opposite side This will extend range and helps to keep the wings laterally balanced see 2 14 FUEL Land as soon as possible according to Section 3 5 7 L...

Page 130: ... up or down locked position Illumination of this light is therefore normal during transit If the light remains on for longer than 20 seconds during landing gear retraction extension 1 Airspeed check below vLOR 156 KIAS 2 Gear selector re cycle if continued illumination occurs If the landing gear cannot be extended to the down locked position or red light does not extinguish Continue with 3 6 2 MAN...

Page 131: ...ulting in degraded flight performance increased fuel consumption and decreased range With the landing gear extended and at aft CG locations with flaps up and full power applied the airplane will easily recover from sideslip if the trim is set to neutral normal procedure Otherwise it may require corrective action with a moderate amount of rudder input In cold ambient temperatures it may help to red...

Page 132: ... Gear indicator lights test push test button 2 ELECT MASTER check ON 3 Bus voltage check in normal range 4 Circuit breaker check in reset if necessary Manual landing gear extension procedure 5 Gear selector select DOWN 6 Manual gear extension handle pull out NOTE The landing gear should now extend by gravity and relief of hydraulic pressure from the system If one or more landing gear indicator lig...

Page 133: ...n lights NOTE If the landing gear is correctly extended and locked as indicated by the 3 green lights the red light is illuminated additionally if the GEAR circuit breaker is pulled If the landing gear cannot be extended to the down locked position continue according to 3 6 3 LANDING WITH GEAR UP END OF CHECKLIST ...

Page 134: ...ch airspeeds and flap settings 2 POWER lever IDLE just before touchdown If the time situation allows the following steps can help to reduce the risk of fire 3 ENGINE MASTER both OFF 4 FUEL SELECTOR both OFF 5 ELECT MASTER OFF Touchdown 6 Touchdown contact surface with minimum airspeed 7 On ground maintain directional control with rudder as long as possible so as to avoid collision with obstacles E...

Page 135: ...airplane 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 th...

Page 136: ...E BRAKES Consider the greater rolling distance Safety harness check fastened and tightened CAUTION If sufficient time is remaining the risk of fire in the event of a collision can be reduced as follows after a safe touch down ENGINE MASTER both OFF FUEL SELECTOR both OFF ELECT MASTER OFF END OF CHECKLIST ...

Page 137: ...iven position Refer to 4B 5 FAILURES IN FLAP OPERATING SYSTEM 6 Land on the nearest suitable airfield WARNING Engine stoppage may occur depending on the failure mode NOTE The landing gear uplock is no longer ensured The landing gear may slowly extend The landing gear can be extended manually according to 3 6 2 MANUAL EXTENSION OF THE LANDING GEAR NOTE The backup artificial horizon and the flood li...

Page 138: ...ontinued safe flight 3 Land on the nearest suitable airfield END OF CHECKLIST 3 7 3 STARTER MALFUNCTION If the starter does not disengage from the engine after starting starter engaged warning STARTER L R on the G1000 annunciator field illuminates after the engine has started 1 POWER lever affected engine IDLE 2 ENGINE MASTER affected engine OFF 3 ELECT MASTER OFF Terminate flight preparation END ...

Page 139: ...as cleared or not land immediately at the nearest suitable airfield or landing site NOTE The cabin hand fire extinguisher is located inside the airplane passenger compartment on the RH side of the cabin floor behind the co pilot seat To release the fire extinguisher from of the bracket it is necessary to grasp the bottle at the agent outlet nozzle near the Y spring 3 8 1 ENGINE FIRE ON GROUND 1 EN...

Page 140: ... remain open in this position Flight characteristics will not be affected significantly END OF CHECKLIST 3 8 3 ENGINE FIRE IN FLIGHT 1 Cabin heat defrost OFF Proceed according to 3 5 6 ENGINE FAILURES IN FLIGHT and shut down the engine according to 3 5 3 ENGINE SECURING FEATHERING PROCEDURE CAUTION In case of extreme smoke development the front canopy may be unlatched during flight This allows it ...

Page 141: ...Page 3 57 3 8 4 ELECTRICAL FIRE ON GROUND 1 ELECT MASTER OFF If the engine is running 2 POWER lever both IDLE 3 ENGINE MASTER both OFF 4 FUEL SELECTOR both OFF When the engine has stopped after standstill 5 Canopy open 6 Airplane evacuate immediately END OF CHECKLIST ...

Page 142: ...tude and heading reference system AHRS will also be affected However by switching the EMERGENCY switch ON the emergency battery will supply power to the standby attitude gyro artificial horizon and the flood light In case of extreme smoke development the front canopy may be unlatched during flight This allows it to be partially opened in order to improve ventilation The canopy will remain open in ...

Page 143: ...centration of carbon monoxide gas can be fatal The occurrence of CO in the cabin is possible only due to a defect If a smell similar to exhaust gases is noticed in the cabin the following measures should be taken 1 Cabin heat defrost OFF 2 Ventilation open 3 Emergency windows open 4 Forward canopy unlatch push up and lock in cooling gap position CAUTION Themaximum demonstratedairspeedforemergencyo...

Page 144: ...py Unlocked 5 Airspeed below 140 KIAS 6 Land at next suitable airfield END OF CHECKLIST Rear Passenger Door Unlocked 5 Airspeed below 140 KIAS 6 Land at next suitable airfield WARNING Do not try to lock the rear passenger 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 door has been lost the airplane can be...

Page 145: ...v 8 15 Dec 2017 Page 3 61 Front Baggage Door Open 5 Airspeed reduce so that door is in a stable position 6 Land at next suitable airfield WARNING Separation of the baggage door may damage the propeller and may lead to an engine failure END OF CHECKLIST ...

Page 146: ...roduce more rapid RPM changes than metal blades WARNING In case of a malfunction of the engine control unit it is possible that the propeller blades will remain in the position of highest pitch In this case the reduced engine performance should be taken into consideration a Oscillating RPM 1 POWER setting change If the problem does not clear 2 ECU SWAP ECU B NOTE If the problem does not clear itse...

Page 147: ...a malfunction in the propeller constant speed unit or a engine control unit malfunction 1 POWER setting reduce as required If the problem does not clear 2 ECU SWAP ECU B CAUTION If the problem does not clear itself switch back to AUTO and land on the nearest suitable airfield Prepare for engine malfunction according to 3 5 6 ENGINE FAILURES IN FLIGHT END OF CHECKLIST ...

Page 148: ...emperature 2 PITOT HEAT ON 3 Cabin heat defrost ON 4 POWER lever increase power in order to prevent ice build up on the propeller blades apply power changes periodically 5 ALTERNATE AIR OPEN 6 Emergency windows open if required CAUTION Ice build up increases the stalling speed 7 ATC advise if an emergency is expected CAUTION If the Pitot heating fails Alternate static valve OPEN Emergency windows ...

Page 149: ...5 Dec 2017 Page 3 65 3 9 5 FUEL SUPPLY FAILURE 1 FUEL SELECTOR CROSSFEED affected engine WARNING When the high pressure fuel pump of the engine takes in air an inspection of the pump is necessary prior to next flight 2 Fuel quantity monitor END OF CHECKLIST ...

Page 150: ... method is based on general experience CAUTION Intentional spins are prohibited in this airplane In the event a spin is encountered unintentionally immediate recovery actions must be taken Single engine stalling is not permitted CAUTION Steps 1 to 4 must be carried out immediately and simultaneously 1 POWER lever IDLE 2 Rudder full deflection against direction of spin 3 Elevator control stick full...

Page 151: ...eed vNE 194 KIAS END OF CHECKLIST 3 9 7 EMERGENCY DESCENT 1 FLAPS UP 2 Gear DOWN 3 POWER lever IDLE 4 Airspeed as required WARNING Max structural cruising speed vNO 155 KIAS Never exceed speed in smooth air vNE 194 KIAS END OF CHECKLIST 3 9 8 EMERGENCY EXIT In case of a roll over of the airplane on ground the rear side door can be used as exit For this purpose unlock the front hinge of the rear si...

Page 152: ...Emergency Procedures DA 42 AFM Page 3 68 Rev 8 15 Dec 2017 Doc No 7 01 05 E Intentionally left blank ...

Page 153: ...N 4A 5 4A 3 3 L R FUEL XFER 4A 5 4A 3 4 PFD MFD GIA FAN FAIL 4A 5 4A 4 FLIGHT CHARACTERISTICS 4A 6 4A 5 DAILY CHECK 4A 6 4A 6 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4A 7 4A 6 1 PRE FLIGHT INSPECTION 4A 7 4A 6 2 BEFORE STARTING ENGINE 4A 22 4A 6 3 STARTING ENGINE 4A 25 4A 6 4 BEFORE TAXIING 4A 27 4A 6 5 TAXIING 4A 28 4A 6 6 BEFORE TAKE OFF 4A 29 4A 6 7 TAKE OFF 4A 34 4A 6 8 CLIMB 4A 36 4A 6 9 C...

Page 154: ...5 Dec 2017 Doc No 7 01 05 E 4A 6 13 AFTER LANDING 4A 41 4A 6 14 SHUT DOWN 4A 42 4A 6 15 EXIT AIRPLANE 4A 43 4A 6 16 POST FLIGHT INSPECTION 4A 43 4A 6 17 PARKING 4A 43 4A 6 18 FLIGHT IN RAIN 4A 44 4A 6 19 REFUELING 4A 44 4A 6 20 FLIGHT AT HIGH ALTITUDE 4A 45 ...

Page 155: ...lb Airspeed for rotation take off run vR UP min 70 KIAS min 72 KIAS Airspeed for take off climb best rate of climb speed vY UP min 77 KIAS min 79 KIAS Airspeed for best angle of climb2 UP 77 KIAS 79 KIAS Airspeed for cruise climb UP min 85 KIAS min 86 KIAS Reference landing approach speed UP 85 KIAS 86 KIAS APP min 82 KIAS min 82 KIAS Final approach speed LDG min 76 KIAS min 78 KIAS Minimum speed ...

Page 156: ... 42 195 is not carried out a landing with a mass between 1700 kg 3748 lb and 1785 kg 3935 lb constitutes an abnormal operating procedure NOTE vx is always less than vy For the DA 42 however the actual value of vx would be below the minimum safe speed The minimumairspeedforbestangleofclimbwasthereforeraised to the value of vy ...

Page 157: ...d text 4A 3 2 L R GLOW ON L R GLOW ON Left Right engine glow plug active 4A 3 3 L R FUEL XFER L R FUEL XFER Fuel transfer from auxiliary to main tank is in progress if aux tanks are installed 4A 3 4 PFD MFD GIA FAN FAIL PFD FAN FAIL Cooling fan for the PFD is inoperative MFD FAN FAIL Cooling fan for the MFD is inoperative GIA FAN FAIL Cooling fan for the GIA is inoperative The flight may be contin...

Page 158: ...nt of rudder input 4A 5 DAILY CHECK Before the first flight of a day it must be ensured that the following checks are performed On condition check of the canopy the side door and the baggage compartment doors for cracks and major scratches On condition check of the hinges for the canopy the side door and the baggage compartment doors Visual inspection of the locking bolts for proper movement with ...

Page 159: ...opy and rear door clean undamaged check locking mechanism function e Baggage stowed and secured f Foreign objects check g Emergency axe if OÄM 42 205 installed stowed and secured h Emergency egress hammer if OÄM 42 304 installed stowed and secured Center Console a FUEL SELECTOR check ON b POWER lever check condition freedom of movement and full travel adjust friction set IDLE Below Instrument Pane...

Page 160: ...NATOR check ON b ECU SWAP check AUTOMATIC c PITOT HEAT check OFF d ENGINE MASTER check both OFF e START KEY check key is pulled out f ELECT MASTER check OFF g AVIONIC MASTER check OFF h GEAR SELECTOR check DOWN i FLAP SELECTOR check UP j Circuit breakers set in if one has been pulled check reason k All electrical equipment OFF l EMERGENCY SWITCH check OFF and guarded m ELT armed CONTINUED ...

Page 161: ... continuously or periodically terminate flight There is a malfunction in the landing gear system b Fuel quantity check indication verify using alternate means see Section 7 9 5 FUEL SYSTEM c Position lights strobe lights ACL check for correct function CAUTION Do not look directly into the anti collision lights d Landing Taxi light check for correct function e Stall warning stall heat Pitot heat ch...

Page 162: ...on the PFD does not appear terminate flight Unscheduled maintenance is necessary g Control stick pull fully aft hold at backstop h FLAPS set LDG position i POWER lever set MAX j Variable elevator backstop check function control stick must move slightly forward during POWER lever forward movement k POWER lever set IDLE l Variable elevator backstop check function control stick must regain full movem...

Page 163: ... as the handling qualities during power on stalls are degraded significantly For more details see Chapter 7 AIRPLANE DESCRIPTION AND SYSTEMS If the variable elevator backstop does not function properly terminate flight n ELECT MASTER OFF o Flight controls check free and correct movement up to full deflection p Trims check free and correct movement up to full deflection END OF CHECKLIST ...

Page 164: ... load transmission correct attachment and general condition In addition control surfaces 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 to Section 8 7 GROUND DE ICING CAUTION Prior to flight remove such items as control surfaces gust lock Pitot cover tow b...

Page 165: ...ve h Landing gear door visual inspection i Structural temperature indicator only if zero fuel mass exceeds 1650 kg 3638 lb check that structural temperature does not exceed 55 C 131 F a red 55 indicates a temperature above the limit 2 Left Engine Nacelle a 3 air inlets 2 air outlets clear b Engine oil level check dipstick inspection hole in the upper cowling CAUTION Do not check the engine oil lev...

Page 166: ...and while the ENGINE MASTER switch is ON Also do not move the propeller by hand while the ENGINE MASTER is OFF immediately after operation remaining pressure in the injection system rail Serious personal injury may result i De Icing boots on propeller if OÄM 42 053 or and OÄM 42 054 carried out check for de bonding j Nacelle underside check for excessive contamination particularly by oil fuel and ...

Page 167: ...gh the tank vent e Stall warn device visual inspection f Tank filler visual inspection check closed g Pitot probe clean orifices clear cover removed no deformation h Wing tip visual inspection i Static dischargers visual inspection j Position light strobe light ACL visual inspection k Tie down check clear l Aileron and linkage visual inspection m Aileron hinges and safety pin visual inspection n F...

Page 168: ...installed check for blockage 5 Empennage a Stabilizers and control surfaces elevator tips visual inspection b Hinges visual inspection c Elevator trim tab visual inspection check safetying d Rudder trim tab visual inspection check safetying e Tie down check clear f Tail skid and lower fin visual inspection g Static dischargers visual inspection 6 Fuselage Right Side a Fuselage skin visual inspecti...

Page 169: ...inspection g Chocks remove h Landing gear door visual inspection i Structural temperature indicator only if zero fuel mass exceeds 1650 kg 3638 lb check that structural temperature does not exceed 55 C 131 F a red 55 indicates a temperature above the limit 8 Right Wing a Entire wing surface visual inspection b Tank air outlet on lower surface visual inspection c Tank drain tank air inlet drain off...

Page 170: ...jects in aileron paddle visual inspection m Flap and linkage visual inspection n Flap hinges and safety pin visual inspection o Nacelle underside fuel cooler air in outlet check clear p Step visual inspection q Cabin vent air inlet check clear if OÄM 42 279 is installed Verify the outside air temperature determine the recommended use of the winter kit ventilation r Winter kit ventilation check for...

Page 171: ...heck visually inspection hole in the lower cowling d Cowling visual inspection e Gascolator air inlet drain off to check for water and sediment drain until no water comes out clear f Venting pipe check for blockage g Exhaust visual inspection WARNING The exhaust can cause burns when hot h Propeller visual inspection WARNING Never move the propeller by hand while the ENGINE MASTER switch is ON Also...

Page 172: ...ank filler visual inspection tank filler closed 10 Front Fuselage and Nose Landing Gear a Left and right front baggage door visual inspection closed and locked b Nose landing gear strut visual inspection sufficient height typical visible length of bare piston at least 15 cm 5 9 in c Down uplock switches visual inspection d Wear tread depth of tire check e Slip marks visual inspection f Gear door a...

Page 173: ...DA 42 AFM Normal Operating Procedures Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 4A 21 k OAT sensor check l EPU connector check m Tow bar remove END OF CHECKLIST ...

Page 174: ...moking 3 Rear door closed and locked CAUTION Whenoperatingthecanopy pilots operators must ensure that there are no obstructions between the canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward pressure on the canopy may be required to ease the handle operation 4 Front canopy Position 1 or 2 cooling gap WARNING ...

Page 175: ...anual pedal adjustment is installed verify proper locking 7 Safety harnesses all on and fastened 8 POWER lever check IDLE 9 Parking brake set 10 AVIONIC MASTER check OFF 11 GEAR selector check DOWN 12 ECU SWAP check AUTOMATIC 13 ALTERNATORS check ON 14 ELECT MASTER ON CAUTION When switching the ELECT MASTER ON the electrically driven hydraulic gear pump may activate itself for 5 to 20 seconds in o...

Page 176: ...d approved only if MÄM 42 037 is incorporated or if the fuel grade is unknown the engine must not be started if the fuel temperature indication prior to operation is below 5 C 23 F Operation with a fuel temperature below 5 C 23 F is not permitted as safe operation of the engine under those conditions cannot be ensured and the engine can stop NOTE Make sure which fuel grade is being used see Sectio...

Page 177: ...unciations check L R GLOW ON 4 Annunciations Engine System Page check OK normal range WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered After the L R GLOW ON indication is extinguished 5 START KEY START L R as required release when propeller speed has reached 500 RPM CAUTION If TAE 125 02 engines with dual mass flywheel are in...

Page 178: ...been released set the ENGINE MASTER to OFF and investigate the problem 6 Annunciations Engine System Page check OK normal range 7 Annunciations Starter check OFF 8 Annunciations Oil pressure check OK WARNING If the oil pressure has not moved from the red range within 3 seconds after starting set the ENGINE MASTER switch to OFF and investigate problem When starting the cold engine the oil pressure ...

Page 179: ...5 Pitot and stall warn heating ON check annunciation NOTE The STAL HT FAIL caution is indicated on the PFD on ground 6 Pitot and stall warn heating OFF 7 Strobe lights ACL check ON 8 Position lights landing and taxi lights as required CAUTION When taxiing at close range to other aircraft or during night flight in clouds fog or haze the strobe lights should be switched OFF The position lights must ...

Page 180: ...ROSSFEED LH RH CAUTION The fuel crossfeed function can be tested simultaneously with both engines Proper function can be tested by running the engines for approx 30 seconds with CROSSFEED selected The operation of both engines with both FUEL SELECTORS in CROSSFEED position other than for this test is prohibited 6 FUEL SELECTOR ON LH RH CAUTION When taxiing on a poor surface select the lowest possi...

Page 181: ...sed and locked CAUTION Whenoperatingthecanopy pilots operators must ensure that there are no obstructions between the canopy and the mating frame for example seat belts clothing etc When operating the locking handle do NOT apply undue force A slight downward pressure on the canopy may be required to ease the handle operation 6 Front canopy closed and locked 7 Front baggage doors closed visual chec...

Page 182: ...e following test sequence can be executed for both engines simultaneously or in sequence FADEC Test Sequence CAUTION If the L R ECU A B FAIL do not illuminate and extinguish during the test sequence there is a malfunction in the engine control system Terminate flight preparation The whole test procedure must be completed without any error In case of an error terminate flight preparation even when ...

Page 183: ...eller RPM decrease increase 11 ECU A FAIL LIGHT OFF 12 Propeller RPM decrease to idle Test sequence completed CAUTION When switching from one ECU to the other a slight shake of the engine may occur In case of longer dropouts of the engine or if the engine stops during the test terminate flight preparation 13 ECU TEST BUTTON release 14 ECU SWAP ECU B 15 Engine check running without a change 16 ECU ...

Page 184: ...2 Annunciations check OK normal range 3 Instruments check within normal range 4 RPM stabilizes at 2240 to 2300 RPM 5 LOAD indication stabilizes at 90 to 100 6 POWER lever IDLE CAUTION Under high temperature and high altitude conditions load indications below 90 are possible If the engine does not stabilize at the target RPM of 2240 to 2300 RPM terminate flight preparation 7 Engine instruments chec...

Page 185: ...c 2017 Page 4A 33 WARNING If the airplane is operated with Diesel Fuel or a blend of Diesel Fuel with Jet Fuel only approved if MÄM 42 037 is incorporated or if the fuel grade is unknown the fuel temperature must be in the green range before take off END OF CHECKLIST ...

Page 186: ...4 Rudder maintain direction NOTE In strong crosswinds steering can be augmented by use of the toe brakes It should be noted however that this method increases the take off roll and should not generally be used 5 Nose wheel lift off up to 1700 kg 3748 lb vR minimum 70 KIAS above 1700 kg 3748 lb vR minimum 72 KIAS 6 Airspeed for initial climb up to 1700 kg 3748 lb minimum 77 KIAS recommended 82 KIAS...

Page 187: ...05 E Rev 8 15 Dec 2017 Page 4A 35 When safe climb is established 7 Landing gear apply brakes UP check unsafe light off NOTE To avoid damage and excessive wear of the main landing gear wheels firmly apply brakes before selecting gear up END OF CHECKLIST ...

Page 188: ...ired for en route cruise climb above 1700 kg 3748 lb 79 KIAS best rate of climb 86 KIAS as required for en route cruise climb 5 POWER lever MAX 6 Trim as required ball centered 7 Annunciations Engine System Page monitor CAUTION If the oil temperature and or coolant temperature reaches the yellow range during climb flight should be continued with the airspeed increased by 10 kts and power reduced b...

Page 189: ... required 3 Annunciations Engine System Page monitor Use of the Auxiliary Fuel Tanks if installed The auxiliary fuel tanks are optional equipment OÄM 42 056 CAUTION When operating the FUEL TRANSFER LH RH switch make sure not to exceed the fuel imbalance limitations given in Section 2 14 FUEL To avoid additional imbalance in the auxiliary tanks both FUELTRANSFERswitchesmustbeoperatedsimultaneously ...

Page 190: ...l per minute If the fuel quantity in a main tank does not increase during fuel transfer proceed according to Section 4B 11 L R FUEL TRANSFER FAIL 2 Transfer the second half of the auxiliary fuel Repeat the procedure described above NOTE Transfer the fuel from the auxiliary tanks to the main tanks as soon as possible The fuel in the auxiliary tanks must be transferred to the main tanks to become av...

Page 191: ...and verify proper fixation NOTE If the landing mass exceeds 1700 kg 3748 lb and OÄM 42 195 is not installed the landing constitutes an abnormal operating procedure Refer to Section 4B 10 LANDINGWITHMASSABOVEMAXIMUMLANDINGMASS 2 Safety harnesses check fastened and tightened 3 Controls no interference by foreign objects 4 Landing light as required 5 Gear warning horn check function 6 FUEL SELECTOR c...

Page 192: ...3748 lb min 86 KIAS with FLAPS UP 11 FLAPS as required 12 POWER lever as required 13 Trim as required directional trim neutral 14 Final approach speed up to 1700 kg 3748 lb min 76 KIAS with FLAPS LDG above 1700 kg 3748 lb min 78 KIAS with FLAPS LDG NOTE Higherapproachspeedsresult inasignificantlylongerlanding distance during flare CAUTION In conditions such as e g strong wind danger of wind shear ...

Page 193: ...LAPS position APP 3 Airspeed min 82 KIAS When a positive rate of climb is established 4 Landing gear UP check unsafe light off 5 FLAPS retract position UP END OF CHECKLIST 4A 6 13 AFTER LANDING 1 POWER lever IDLE 2 Brakes as required 3 Pitot heating OFF 4 Avionics as required 5 Lights as required 6 FLAPS UP END OF CHECKLIST ...

Page 194: ...ing on 121 5 MHz 5 AVIONIC MASTER OFF 6 Electrical consumers OFF 7 ENGINE MASTER OFF 8 Anti collision lights ACL OFF 9 ELECT MASTER OFF CAUTION Before shut down the engine must run for at least 2 minutes with the POWER lever at IDLE to avoid heat damage of the turbo charger CAUTION Do not shut down an engine with the FUEL SELECTOR valve The high pressure fuel pump can otherwise be damaged END OF C...

Page 195: ... the inner wing section LH or RH 4A 6 16 POST FLIGHT INSPECTION 1 Record any problem found in flight and during the post flight check in the log book 2 Park the airplane 3 If necessary moor the airplane END OF CHECKLIST 4A 6 17 PARKING 1 Parking brake release use chocks 2 Airplane moor if unsupervised for extended period 3 PITOT probe cover END OF CHECKLIST ...

Page 196: ... CAUTION Before refueling the airplane must be connected to electrical ground Grounding points exhausts left and right Refer to Section 2 14 FUEL for approved fuel grades NOTE If the airplane is operated with Diesel Fuel only approved if MÄM 42 037 is incorporated additional temperature limitations refer to Section 2 16 1 FUEL TEMPERATURE must be observed If Jet Fuel is used make sure that no Dies...

Page 197: ...s If the auxiliary tanks are not in use make sure that they are empty refer to Section 6 4 FLIGHT MASS CENTER OF GRAVITY CAUTION If the airplane is operated with Diesel Fuel or a blend of Diesel Fuel with Jet Fuel only approved if MÄM 42 037 is incorporated the use of the auxiliary tanks is not permitted 4A 6 20 FLIGHT AT HIGH ALTITUDE At high altitudes the provision of oxygen for the occupants is...

Page 198: ...Normal Operating Procedures DA 42 AFM Page 4A 46 Rev 8 15 Dec 2017 Doc No 7 01 05 E Intentionally left blank ...

Page 199: ... 4B 7 4B 3 4 OIL PRESSURE 4B 8 4B 3 5 GEARBOX TEMPERATURE 4B 9 4B 3 6 FUEL TEMPERATURE 4B 9 4B 3 7 VOLTAGE 4B 10 4B 4 CAUTION ALERTS ON THE G1000 4B 11 4B 4 1 CAUTIONS GENERAL 4B 11 4B 4 2 L R ECU A FAIL 4B 12 4B 4 3 L R ECU B FAIL 4B 13 4B 4 4 L R FUEL LOW 4B 14 4B 4 5 LOW VOLTAGE CAUTION LOW VOLTS 4B 15 4B 4 6 L R ALTN FAIL 4B 16 4B 4 7 L R COOL LVL 4B 17 4B 4 8 PITOT FAIL HT OFF 4B 18 4B 4 9 ST...

Page 200: ...ECTRICAL RUDDER PEDAL ADJUSTMENT 4B 25 4B 7 FAILURES IN HYDRAULIC SYSTEM 4B 26 4B 7 1 CONTINUOUS HYDRAULIC PUMP OPERATION 4B 26 4B 7 2 HYDRAULIC PUMP FAILURE 4B 27 4B 8 STARTING ENGINE WITH EXTERNAL POWER 4B 28 4B 8 1 BEFORE STARTING ENGINE 4B 28 4B 8 2 STARTING ENGINE 4B 30 4B 9 LIGHTNING STRIKE 4B 32 4B 10 LANDING WITH MASS ABOVE MAXIMUM LANDING MASS 4B 33 4B 11 L R FUEL TRANSFER FAIL IF AUX TAN...

Page 201: ...a controlled landing in a field represents a lower risk than the attempt to reach the nearest airfield under all circumstances NOTE If no level landing area is available a landing on an upward slope 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 ...

Page 202: ...15 Dec 2017 Doc No 7 01 05 E CAUTION If sufficient time is remaining the risk of fire in the event of a collision with obstacles can be reduced as follows after a safe touch down ENGINE MASTER both OFF FUEL SELECTOR both OFF ELECT MASTER OFF END OF CHECKLIST ...

Page 203: ...close the canopy in flight Land the airplane and close the canopy on ground 4B 3 ENGINE INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE ON THE G1000 4B 3 1 RPM High RPM 1 Reduce power of affected engine 2 Keep RPM within the green range using the POWER lever If the above mentioned measures do not solve the problem refer to 3 9 3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM 3 Land at the nearest suitabl...

Page 204: ...w coolant level NOTE During an extended descent from high altitudes with a low power setting coolant temperature may decrease In this case an increase in power and a decrease in airspeed can help L R COOL LVL caution message displayed Reduce power on affected engine Expect loss of coolant WARNING A further decrease in coolant temperature must be expected Prepare for an engine failure in accordance...

Page 205: ...L TEMPERATURE a High Oil Temperature Proceed according to 3 2 3 L R OIL TEMP b Low Oil Temperature NOTE During an extended descent from high altitudes with a low power setting oil temperature may decrease In this case an increase in power can help Increase power Reduce airspeed END OF CHECKLIST ...

Page 206: ...ressure indication Keep monitoring temperatures If the temperatures are outside of the green range Reduce power on affected engine WARNING Land at the nearest suitable airfield Prepare for an engine failure in accordance with 3 5 6 ENGINE FAILURES IN FLIGHT CAUTION When starting a cold engine the oil pressure can be as high as 6 5 bar for a maximum of 20 seconds END OF CHECKLIST b Low Oil Pressure...

Page 207: ...ow Fuel Temperature Increase power on affected engine Reduce airspeed CAUTION At low ambient temperature conditions and or at high airspeeds with low power settings it can be assumed that the above mentioned procedure will increase the temperature s If the fuel temperature does not return to the green range perform a precautionary landing on the nearest suitable airfield Prepare for an engine fail...

Page 208: ... POWER lever increase RPM if LOW VOLTAGE CAUTION 4B 4 5 LOW VOLTS is still indicated on the G1000 Terminate flight preparation END OF CHECKLIST b Low Voltage During Flight 1 Circuit breakers check 2 Electrical equipment OFF if not needed if LOW VOLTAGE CAUTION 4B 4 5 LOW VOLTS is still indicated on the G1000 Follow procedure in 4B 4 6 L R ALTN FAIL END OF CHECKLIST ...

Page 209: ...5 E Rev 8 15 Dec 2017 Page 4B 11 4B 4 CAUTION ALERTS ON THE G1000 The G1000 provides the following CAUTION alerts on the PFD in the ALERT area 4B 4 1 CAUTIONS GENERAL CHARACTERISTICS Amber color coded text Single warning chime tone of 1 5 seconds duration ...

Page 210: ... b ECU A Caution During Flight NOTE In case of a failure in the electronic ECU Engine Control Unit A the system automatically switches to ECU B 1 Press the ECU TEST button for more than 2 seconds to reset the caution message If the ECU A caution message reappears or cannot be reset 2 Land on the nearest suitable airfield 3 The engine must be serviced after landing If the ECU A caution message can ...

Page 211: ...ECU B Caution on the Ground Terminate flight preparation b ECU B Caution During Flight 1 Press the ECU TEST button for more than 2 seconds to reset the caution message If the ECU B caution message reappears or cannot be reset 2 Land on the nearest suitable airfield 3 The engine must be serviced after landing If the ECU B caution message can be reset 2 Continue flight 3 The engine must be serviced ...

Page 212: ... low a caution message is displayed The indication is calibrated for straight and level flight The caution message may be triggered during turns which are flown with slip or while taxiing in curves If fuel quantities of LH RH engines show remarkable different fuel quantities in flight Expect loss of fuel on side with lower indication Use CROSSFEED function to ensure fuel supply 2 FUEL SELECTOR CRO...

Page 213: ...TAGE CAUTION LOW VOLTS L R VOLTS LOW Left Right bus voltage is less than 25 Volts Possible reasons are A fault in the power supply RPM too low Continue with 4B 3 7 VOLTAGE CAUTION If both low voltage indications are ON expect failure of both alternators and follow 4B 4 6 L R ALTN FAIL END OF CHECKLIST ...

Page 214: ...uce as practicable END OF CHECKLIST b Both Alternators Failed WARNING If both alternators fail at the same time reduce all electrical equipment to a minimum Expect battery power to last 30 minutes and land the airplane as soon as possible Expect engine stoppage after this period of time 1 Avionics Master OFF 2 LH RH Alternator OFF 3 XPDR STBY 4 LANDING GEAR down when down and locked pull emergency...

Page 215: ...ndicate a loss of coolant This will subsequently lead to decreased engine cooling capability loss of engine power due to engine failure 1 Annunciations Engine instruments monitor See 4B 3 2 COOLANT TEMPERATURE NOTE The indication is calibrated for straight and level flight The caution message may be triggered during turns which are flown with slip or while taxiing in curves END OF CHECKLIST ...

Page 216: ...ot heating system Prolonged operation of the Pitot heating on the ground can also cause the Pitot heating caution message to be displayed In this case it indicates the activation of the thermal switch which prevents overheating of the Pitot heating system on the ground This is a normal function of the system After a cooling period the heating system will be switched on again automatically If in ic...

Page 217: ...AIL when there is a failure of the stall warning heating system Operation of the stall warning heating on the ground also causes the stall warning heating failed caution message to be displayed In this case it indicates the activation of the thermal protection relay which prevents overheating of the stall warning heating system on the ground This is a normal function of the system If in icing cond...

Page 218: ...LIARY FUEL TANK EMPTY IF AUX TANKS INSTALLED L R AUX FUEL E Left Right auxiliary fuel tank empty displayed only when FUEL TRANSFER pump is ON The auxiliary tank empty caution message indicates an empty auxiliary fuel tank while the fuel pump is switched ON 1 L R auxiliary fuel pump OFF END OF CHECKLIST ...

Page 219: ...rative In case of stalling with power on the handling qualities and stall characteristics are degraded significantly Do not stall the airplane in any configuration b At least one POWER lever is in a position for a power setting of less than approximately 20 LOAD or the FLAP selector switch is not in LDG position CAUTION The variable elevator backstop is active all the time reducing the maximum ele...

Page 220: ...IM UNAVAIL INTEG RAIM not available RAIM Receiver Autonomous Integrity Monitor is not available a Enroute Oceanic Terminal or Initial Approach Phase of Flight If the RAIM UNAVAIL annunciation is displayed in the enroute oceanic terminal or initial approach phase of flight continue to navigate using the GPS equipment or revert to an alternate means of navigation other than the G1000 GPS receiver ap...

Page 221: ...tivity 0 3 nautical miles After 5 minutes the system will flag and no longer provide course guidancewithapproachsensitivity Missedapproachcourseguidancemaystillbeavailable with 1 nautical mile CDI sensitivity and integrity by executing the missed approach END OF CHECKLIST 4B 4 14 AHRS ALIGNING KEEP WINGS LEVEL AHRS ALIGN Keep Wings Level The AHRS Attitude and Heading Reference System is aligning K...

Page 222: ...sitions Modified Approach Procedure Depending on the Available Flap Setting a Only UP available Airspeed up to 1700 kg 3748 lb min 85 KIAS above 1700 kg 3748 lb min 86 KIAS see Section 4B 10 Land at a flat approach angle use POWER lever to control airplane speed and rate of descent b Only APP available Airspeed min 82 KIAS Land at a flat approach angle use POWER lever to control airplane speed and...

Page 223: ...6 FAILURES IN ELECTRICAL RUDDER PEDAL ADJUSTMENT Runaway of Electrical Rudder Pedal Adjustment Optional Equipment OÄM 42 070 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 224: ...ights check 2 Prepare for manual landing gear extension Refer to Section 3 6 2 MANUAL EXTENSION OF THE LANDING GEAR NOTE The landing gear might extend as the hydraulic system pressure decreases Consider for higher aerodynamic drag resulting in degraded flight performance increased fuel consumption and decreased range Unscheduled maintenance action is required after landing END OF CHECKLIST ...

Page 225: ...r manual landing gear extension Refer to Section 3 6 2 MANUAL EXTENSION OF THE LANDING GEAR NOTE The landing gear might extend as the hydraulic system pressure decreases Consider for higher aerodynamic drag resulting in degraded flight performance increased fuel consumption and decreased range Unscheduled maintenance action is required after landing END OF CHECKLIST ...

Page 226: ...s adjustable backrests if installed doors and emergency exits and the ban on smoking 3 Rear door closed and locked 4 Front canopy position 1 or 2 cooling gap 5 Rudder pedals adjusted and locked 6 Safety harnesses all on and fastened 7 POWER lever check IDLE 8 Parking brake set 9 AVIONIC MASTER check OFF 10 GEAR selector check DOWN 11 ECU SWAP check AUTOMATIC 12 ALTERNATORS check ON 13 ELECT MASTER...

Page 227: ...ystem pressure Should the pump continue to operate continuously or periodically terminate flight There is a malfunction in the landing gear system NOTE When switching the external power unit ON all electrical equipment connected to the LH and RH main busses is powered 17 G1000 wait until power up completed Press ENT on MFD to acknowledge NOTE The engine instruments are only available on the MFD af...

Page 228: ... persons can be endangered After the L GLOW ON indication is extinguished 6 START KEY START L as required release when engine has started 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 If the L STARTER a...

Page 229: ... has not moved from the red range within 3 seconds after starting set the ENGINE MASTER switch to OFF and investigate problem When starting the cold engine the oil pressure can be as high as 6 5 bar for a maximum of 20 seconds 10 Circuit breakers check all in as required 11 Idle RPM check 900 20 RPM 12 External power disconnect 13 Opposite engine start with normal procedure 14 Warm up IDLE for 2 m...

Page 230: ...eck 4 PFD backup instruments verify periodically 5 Continue flight under VMC 6 Land on next suitable airfield CAUTION Due to possible damage to the airplane obey the following instructions Avoid abrupt or full control surface movements Avoid high g loads on the airframe Avoid high yaw angles Avoid turbulent air as far as possible e g lee effects Do not fly into areas of known or forecast icing Mai...

Page 231: ... if OÄM 42 195 is carried out and for landings with a mass up to 1700 kg 3748 lb Perform landing approach according to Section 4A 6 11 APPROACH LANDING but maintain an increased airspeed during final landing approach Approach speed min 82 KIAS with FLAPS APP min 86 KIAS with FLAPS UP Final approach speed min 78 KIAS with FLAPS LDG Minimum speed on go around 82 KIAS END OF CHECKLIST ...

Page 232: ...s CAUTION An imbalance in the auxiliary tanks is approved when the imbalance in the main tanks is less than 1 US gal 3 8 liter 2 Check fuel imbalance in the main tanks use CROSSFEED function to keep the LH and RH main tank imbalance within the permissible limit of 1 US gal 3 8 liter 3 Switch the remaining fuel pump ON 4 Use CROSSFEED function to keep the LH and RH main tank imbalance within the pe...

Page 233: ...3 5 3 2 FUEL FLOW DIAGRAM 5 6 5 3 3 INTERNATIONAL STANDARD ATMOSPHERE 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 17 5 3 8 CLIMB PERFORMANCE CRUISE CLIMB 5 20 5 3 9 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE 5 23 5 3 10 CRUISING TRUE AIRSPEED TAS 5 26 5 3 11 LANDING DISTANCE 5 28 5 3 12 GRADIENT OF CLIMB ON GO AROUND 5...

Page 234: ...s of the International Standard Atmosphere ISA 15 EC 59 F and 1 013 25 hPa 29 92 inHg at sea level The performance diagrams do not take into account variations in pilot experience 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...

Page 235: ...ance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 3 5 3 PERFORMANCE TABLES AND DIAGRAMS 5 3 1 AIRSPEED CALIBRATION NOTE The position of the landing gear extended retracted has no influence on the airspeed indicator system ...

Page 236: ...Performance DA 42 AFM Page 5 4 Rev 8 15 Dec 2017 Doc No 7 01 05 E ...

Page 237: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 5 ...

Page 238: ...e NOTE The fuel calculations on the FUEL CALC portion of the G1000 MFD do not use the airplane s fuel quantity indicators The values shown are numbers which are calculated from the last fuel quantity update done by the pilot and actual fuel flow data Therefore the endurance and range data is for information only and must not be used for flight planning ...

Page 239: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 7 5 3 3 INTERNATIONAL STANDARD ATMOSPHERE ...

Page 240: ...ling Speeds at Various Flight Masses Airspeeds in KIAS at idle power 1400 kg 3086 lb Bank Angle Gear Flaps 0 30 45 60 UP UP 56 60 68 83 DOWN APP 53 58 65 78 DOWN LDG 49 53 61 75 1700 kg 3748 lb Bank Angle Gear Flaps 0 30 45 60 UP UP 62 67 76 92 DOWN APP 59 64 72 87 DOWN LDG 55 60 68 84 if MÄM 42 088 is carried out 1785 kg 3935 lb Bank Angle Gear Flaps 0 30 45 60 UP UP 64 69 78 95 DOWN APP 61 66 74...

Page 241: ...2 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 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 242: ...ed for initial climb up to 1700 kg 3748 lb 77 KIAS above 1700 kg 3748 lb 79 KIAS Runway level hard paved surface concrete asphalt etc Values for ISA and MSL at 1700 kg 3748 lb Take off distance over a 50 ft 15 m obstacle 530 m 1739 ft Take off ground roll 348 m 1142 ft if MÄM 42 088 is carried out Values for ISA and MSL at 1785 kg 3935 lb Take off distance over a 50 ft 15 m obstacle 691 m 2267 ft ...

Page 243: ...n the following NOTE are typical values On wet ground or wet soft grass covered runways the take off roll may become significantly longer than stated below In any case the pilot must allow for the condition of the runway to ensure a safe take off NOTE For take off from dry short cut grass covered runways the following corrections must be taken into account compared to paved runways typical values ...

Page 244: ...01 05 E NOTE For wet grass an additional 10 increase in take off roll must be expected NOTE An uphill slope of 2 2 m per 100 m or 2 ft per 100 ft results in an increase in the take off distance of approximately 10 The effect on the take off roll can be greater ...

Page 245: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 13 Conditions Flaps UP Power both MAX 2300 RPM v R 70 KIAS Airspeed 77 KIAS Runway hard paved ...

Page 246: ...Performance DA 42 AFM Page 5 14 Rev 8 15 Dec 2017 Doc No 7 01 05 E Conditions Flaps UP Power both MAX 2300 RPM v R 72 KIAS Airspeed 79 KIAS Runway hard paved ...

Page 247: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 15 ...

Page 248: ...Performance DA 42 AFM Page 5 16 Rev 8 15 Dec 2017 Doc No 7 01 05 E Conditions Flaps UP Power both MAX 2300 RPM v R 72 KIAS Airspeed 79 KIAS Runway hard paved ...

Page 249: ...FORMANCE TAKE OFF CLIMB Conditions POWER lever both MAX 2300 RPM Flaps UP Landing gear retracted Airspeed up to 1700 kg 3748 lb 77 KIAS above 1700 kg 3748 lb 79 KIAS NOTE The charts on the following pages show the rate of climb The gradient of climb cannot easily be determined with a chart but it can be calculated using the following formulae ...

Page 250: ...Performance DA 42 AFM Page 5 18 Rev 8 15 Dec 2017 Doc No 7 01 05 E Conditions Flaps UP Power both MAX 2300 RPM Landing gear retracted Airspeed 77 KIAS ...

Page 251: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 19 ...

Page 252: ...3 8 CLIMB PERFORMANCE CRUISE CLIMB Conditions POWER lever both MAX 2300 RPM Flaps UP Airspeed up to 1700 kg 3748 lb 85 KIAS above 1700 kg 3748 lb 86 KIAS NOTE The graphs on the following pages show the rate of climb The gradient of climb cannot easily be determined with a graph but it can be calculated using the following formulae ...

Page 253: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 21 Conditions Flaps UP Power both MAX 2300 RPM Airspeed 85 KIAS ...

Page 254: ...Performance DA 42 AFM Page 5 22 Rev 8 15 Dec 2017 Doc No 7 01 05 E Conditions Flaps UP Power both MAX 2300 RPM Airspeed 86 KIAS ...

Page 255: ... 2300 RPM Dead engine feathered and secured Flaps UP Airspeed 82 KIAS Landing gear retracted Zero sideslip established NOTE With respect to handling and performance the left hand engine pilots view is considered the critical engine NOTE The graphs on the following pages show the rate of climb The gradient of climb cannot easily be determined with a graph but it can be calculated using the followin...

Page 256: ...Performance DA 42 AFM Page 5 24 Rev 8 15 Dec 2017 Doc No 7 01 05 E Conditions Flaps UP Power remaining engine MAX 2300 RPM Dead engine feathered secured Airspeed 82 KIAS ...

Page 257: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 25 ...

Page 258: ... DA 42 AFM Page 5 26 Rev 8 15 Dec 2017 Doc No 7 01 05 E 5 3 10 CRUISING TRUE AIRSPEED TAS Conditions Engines all operating POWER lever as required to adjust selected displayed LOAD Flaps UP Landing gear retracted ...

Page 259: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 27 Conditions Engines all operating Power as required to adjust selected LOAD Flaps UP Landing gear retracted ...

Page 260: ...7 ft Ground roll 323 m 1060 ft NOTE If MÄM 42 088 is carried out and OÄM 42 195 is not carried out a landing with a mass between 1700 kg 3748 lb and 1785 kg 3935 lb constitutes an abnormal operating procedure Values for ISA and MSL at 1785 kg 3935 lb Approach Speed 78 KIAS Landing distance over a 50 ft 15 m obstacle 710 m 2329 ft Ground roll 397 m 1302 ft WARNING For a safe landing the available r...

Page 261: ...ow In any case the pilot must allow for the condition 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 ...

Page 262: ...Performance DA 42 AFM Page 5 30 Rev 8 15 Dec 2017 Doc No 7 01 05 E Conditions Flaps LDG Power both IDLE Runway level and hard dry surface Approach Speed 76 KIAS ...

Page 263: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 31 Conditions Flaps LDG Power both IDLE Runway level and hard dry surface Approach Speed 78 KIAS ...

Page 264: ...Performance DA 42 AFM Page 5 32 Rev 8 15 Dec 2017 Doc No 7 01 05 E Conditions Flaps LDG Power both IDLE Runway level and hard dry surface Approach Speed 76 KIAS ...

Page 265: ...DA 42 AFM Performance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 5 33 Conditions Flaps LDG Power both IDLE Runway level and hard dry surface Approach Speed 78 KIAS ...

Page 266: ...e 1700 kg 3748 lb 78 KIAS Value for ISA and MSL at 1700 kg 3748 lb Constant gradient of climb 5 25 equals 3 0 climb angle or 400 ft min NOTE If MÄM 42 088 is carried out and OÄM 42 195 is not carried out a landing with a mass between 1700 kg 3748 lb and 1785 kg 3935 lb constitutes an abnormal operating procedure Value for ISA and MSL at 1785 kg 3935 lb Constant gradient of climb 4 30 equals 2 5 cl...

Page 267: ... 76 8 dB A JAR 36 Subpart C 76 8 dB A Max Flight Mass 1700 kg 3748 lb if MÄM 42 198 is carried out ICAO Annex 16 Chapter X App 6 77 6 dB A JAR 36 Subpart C 77 6 dB A Max Flight Mass 1785 kg 3935 lb if MÄM 42 088 and MÄM 42 198 are carried out ICAO Annex 16 Chapter X App 6 79 1 dB A JAR 36 Subpart C 79 1 dB A Max Flight Mass 1785 kg 3935 lb if MÄM 42 088 is carried out and TAE 125 02 99 MÄM 42 198 ...

Page 268: ...Performance DA 42 AFM Page 5 36 Rev 8 15 Dec 2017 Doc No 7 01 05 E Intentionally left blank ...

Page 269: ... 6 2 6 2 DATUM PLANE 6 3 6 3 MASS AND BALANCE REPORT 6 4 6 4 FLIGHT MASS AND CENTER OF GRAVITY 6 6 6 4 1 MOMENT ARMS 6 8 6 4 2 LOADING DIAGRAM 6 9 6 4 3 CALCULATION OF LOADING CONDITION 6 10 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 270: ...g the flight mass CG position is described in this chapter Additionally a comprehensive list of the equipment approved for this airplane exists Equipment List The set of items marked as installed constitutes the Equipment Inventory Before the airplane is delivered the empty mass and the corresponding CG position are determined and entered in Section 6 3 MASS AND BALANCE REPORT NOTE Following equip...

Page 271: ...ss and balance data of the airplane therefore remain unchanged 6 2 DATUM PLANE The Datum Plane DP is a plane which is normal to the airplane s longitudinal axis and in front of the airplane as seen from the direction of flight The airplane s longitudinal axis is parallel with the floor of the nose baggage compartment When the floor of the nose baggage compartment is aligned horizontally the Datum ...

Page 272: ...t mass and corresponding CG position or moment the current empty mass and the corresponding CG position or moment in accordance with the Mass and Balance Report must always be used Condition of the airplane for establishing the empty mass Equipment as per Equipment Inventory see Section 6 5 Including the following operating fluids Brake fluid Hydraulic fluid for the retractable gear Engine oil 2 x...

Page 273: ... 6 5 MASS AND BALANCE REPORT Page No Current empty mass Mo ment Mo ment Arm Mass Registration Changes in mass Subtraction Mo ment Mo ment Arm Mass Serial No Addition Mo ment Mo ment Arm Mass DA 42 Description of part or Modification Upon delivery Entry No OUT IN Date ...

Page 274: ...Your DA 42 in Table 6 4 3 CALCULATION OF LOADING CONDITION 2 Read the fuel quantity indicators to determine the fuel quantity in the main fuel tanks 3 Determine the fuel quantity in the auxiliary fuel tanks if installed To verify an empty auxiliary fuel tank set the ELECT MASTER switch and the FUEL TRANSFER switch to ON and check the PFD for the L R AUX FUEL E caution message To verify a full auxi...

Page 275: ...he total moment by the total mass using row 8 for the condition with empty fuel tanks and row 11 for the pre take off condition The resulting CG position must be inside the limits 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 rang...

Page 276: ...ft of the Datum Plane Item Lever Arm m in Occupants on front seats 2 30 90 6 Occupants on rear seats 3 25 128 0 Fuel In main tanks 2 63 103 5 In auxiliary tanks 3 20 126 0 De Icing Fluid if equipment installed OÄM 42 053 or OÄM 42 054 1 00 39 4 Baggage in Compartments Nose 0 60 23 6 Cabin 3 89 153 1 Extension 4 54 178 7 ...

Page 277: ...DA 42 AFM Mass and Balance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 6 9 6 4 2 LOADING DIAGRAM ...

Page 278: ...own in the example and without considering the on board de icing fluid All four CG positions fuel tank full empty de icing fluid tank full empty must fall into the permitted area 1 Complete the form on the next page 2 Divide the total moments from rows 8 and 11 by the related total mass to obtain the CG positions In our example empty tanks 3625 1 kgm 1527 5 kg 2 373 m 314 656 in lb 3368 lb 93 43 i...

Page 279: ...n 5 11 3 0 260 5 Cabin baggage compt Lever arm 3 89 m 153 1 in 10 22 38 9 3 368 6 Baggage extension Lever arm 4 54 m 178 7 in 5 11 22 7 1 966 7 De Icing fluid if installed see NOTE on previous page 1 1 kg liter 9 2 lb US gal Lever arm 1 00 m 39 4 in 27 5 61 27 5 2 403 8 Total mass total moment with empty fuel tanks Total of 1 through 7 Note Maximum zero fuel masses 1650 kg 3638 lb 1674 kg 3690 lb ...

Page 280: ...No 7 01 05 E 10 Usable fuel auxiliary tanks if installed OÄM 42 056 0 84 kg liter 7 01 lb US gal Lever arm 3 20 m 126 0 in 84 185 268 8 23 310 11 Total mass total moment with fuel de icing fluid Total of 8 through 10 1770 5 3904 4312 1 374 295 The CG s shown in the following diagrams are those from the example in Section 6 4 3 CALCULATION OF LOADING CONDITION rows 8 and 11 ...

Page 281: ...0 1300 1350 1400 1450 1500 1550 1600 1650 1700 1750 1800 Center of Gravity Position m 2 35 2 40 2 45 2 50 Flight Mass lb Center of Gravity Position in 96 95 94 93 92 97 98 shaded area only for 1785 kg 3935 lb max take off mass MÄM 42 088 carried out 6 4 4 PERMISSIBLE CENTER OF GRAVITY RANGE ...

Page 282: ... kg 2756 lb 2 35 m 92 52 in aft of Datum Plane at 1468 kg 3236 lb 2 40 m 94 49 in aft of Datum Plane at max take off mass see Section 2 7 linear variation in between Most rearward flight CG 2 42 m 95 28 in aft of Datum Plane at 1250 kg 2756 lb 2 49 m 98 03 in aft of Datum Plane at 1600 kg 3527 lb 2 49 m 98 03 in aft of Datum Plane at max take off mass see Section 2 7 linear variation in between ...

Page 283: ...0 3500 3400 3300 3200 3100 3000 2900 Flight Mass kg Flight Mass lb Flight Mass Moment kg m Flight Mass Moment in lb 260 000 280 000 300 000 320 000 340 000 360 000 380 000 shaded area only for 1785 kg 3935 lb max take off mass MÄM 42 088 carried out 6 4 5 PERMISSIBLE MOMENT RANGE The flight mass moments shown in the diagram are those from the example in Table 6 4 3 a CALCULATION OF LOADING CONDITI...

Page 284: ...t below 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 an unit by an identical unit 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 In...

Page 285: ...70 C 065 00178 2500 Bendix King 2 290 1 040 175 400 4 455 Pitch servo mount KM 275 065 00030 0000 Bendix King 1 077 0 489 175 400 4 455 Roll servo KS 271 C 065 00179 0500 Bendix King 2 290 1 040 124 800 3 170 Roll servo mount KM 275 065 00030 0000 Bendix King 1 077 0 489 124 800 3 170 Trim servo KS 272 C 065 00180 3500 Bendix King 2 290 1 040 88 190 2 240 Trim servo mount KM 277 065 00041 0000 Ben...

Page 286: ... Concorde 26 5 12 0 49 170 1 249 Main Battery RG24 15M Concorde 29 5 13 4 49 170 1 249 Excitation Battery 2 pcs LC R121R3P Panasonic Emergency Battery D60 2560 91 00 Diamond Aircraft ECU Backup Battery LH 2 pcs LC R121R3P Panasonic ECU Backup Battery RH 2 pcs LC R121R3P Panasonic ECU Backup Battery LH 2 pcs LC R127R2P Panasonic ECU Backup Battery RH 2 pcs LC R127R2P Panasonic External Power Connec...

Page 287: ...20 2 350 Safety belt copilot 5 01 Series 5 01 2G5710 Schroth 2 110 0 960 92 520 2 350 Safety belt LH pax 5 01 Series 5 01 2H5710 Schroth 2 250 1 020 126 800 3 220 Safety belt RH pax 5 01 Series 5 01 2H0710 Schroth 2 250 1 020 126 800 3 220 Safety belt pilot 5 01 Series 5 01 2G0701 Schroth 2 110 0 960 92 520 2 350 Safety belt copilot 5 01 Series 5 01 2G5701 Schroth 2 110 0 960 92 520 2 350 Safety b...

Page 288: ... Flaps actuator assy 43055 Krutz Lift detector C 99701 1 Safe Flight Instr Stall warning buzzer SC Series SC 628 ND Mallory Variable elevator stop D60 2733 12 00 Diamond Aircraft Variable elevator stop D60 2733 12 00_01 Diamond Aircraft HYDRAULIC Motor pump unit X11 0001 00 00 00 Hydraulik Mayer Hydraulic fluid tank X11 0002 00 00 00 Hydraulik Mayer Hydraulic control unit X11 0003 00 00 00 Hydraul...

Page 289: ...0 011 00972 02 Garmin 6 400 2 910 70 080 1 780 Primary Flight Display PFD GDU 1040 011 00972 03 Garmin 6 400 2 910 70 080 1 780 Multi Function Display MFD GDU 1040 011 00972 02 Garmin 6 400 2 910 70 080 1 780 Multi Function Display MFD GDU 1040 011 00972 03 Garmin 6 400 2 910 70 080 1 780 LANDING GEAR Main landing gear LH D60 3217 11 00 Diamond Aircraft Main landing gear RH D60 3217 12 00 Diamond ...

Page 290: ...len Strobe Pos light assy RH OR6002G 01 0771733 11 Whelen Strobe light power supply LH RH A490ATS CF 14 28 01 0770062 05 Whelen Taxi light Xenon D1S Aero Vision Int 0 990 0 449 79 920 2 030 Taxi light power supply XV1 28 Aero Vision Int 0 880 0 400 82 290 2 090 Taxi light power supply XV4D 35 XeVision 0 880 0 400 82 290 2 090 Landing light Xenon D1S Aero Vision Int 0 990 0 449 79 920 2 030 Landing...

Page 291: ...5 Sennheiser Headset copilot Echelon 100 Telex Headset copilot HMEC25 KAP 2 025 230 715 Sennheiser Headset LH pax Echelon 100 Telex Headset LH pax HMEC25 KAP 2 025 230 715 Sennheiser Headset RH pax Echelon 100 Telex Headser RH pax HMEC25 KAP 2 025 230 715 Sennheiser Speaker FRS8 4 Ohms Visaton Handmic 100 TRA 62800 001 Telex Pitot Static probe heated DAI 9034 57 00 Diamond Aircraft Pitot Static pr...

Page 292: ...DC 74A 011 00882 00 Garmin 1 580 0 720 70 080 1 780 Digital Air Data System GDC 74A 011 00882 10 Garmin 1 580 0 720 70 080 1 780 Integrated Avionics 1 GIA 63 011 00781 01 Garmin 5 290 2 400 154 900 3 935 Integrated Avionics 2 GIA 63 011 00781 01 Garmin 5 290 2 400 154 900 3 935 Transponder GTX 33 011 00779 00 Garmin 3 030 1 380 153 100 3 890 Transponder GTX 33 011 00779 10 Garmin 3 030 1 380 153 1...

Page 293: ...165 400 4 200 ADF antenna AN 3500 0832 601 912 Becker 3 450 1 560 133 900 3 400 Stormscope WX 500 805 11500 001 L 3 Goodrich 2 290 1 040 140 100 3 560 Stormscope antenna NY 163 805 10930 001 L 3 Goodrich 0 820 0 370 280 700 7 130 TAS Processor TAS 600 70 2420 x TAS600 Avidyne Ryan TAS Processor TAS 605 70 2420 x TAS605 Avidyne Ryan TAS Processor TAS 610 70 2420 x TAS610 Avidyne Ryan 6 800 3 100 16...

Page 294: ...04 69 690 1 770 Single outlet manifold RH 4110 401 2 Aerox 0 230 0 104 69 690 1770 Dual outlet manifold 4110 400 2 Aerox 0 420 0 191 109 300 2 775 Oxygen pressure regulator 4110 110 Aerox 0 740 0 336 21 260 0 540 Filling block 4110 405 Aerox 0 540 0 245 28 150 0 715 Pressure gauge 4110 490 Aerox 0 110 0 050 70 080 1 780 Oxygen cylinder empty 4110 200 2 Aerox 7 400 3 357 32 280 0 820 Single outlet ...

Page 295: ...7610 55181R Thielert Technify ECU Firmware Thielert Technify ECU Mapping Thielert Technify RH ENGINE CONTROL UNIT ECU 02 7610 55003R Thielert Technify ECU 02 7610 55181R Thielert Technify ECU Firmware Thielert Technify ECU Mapping Thielert Technify ENGINE STARTING Glow Power Control Unit LH RH 02 7150 55005R1 Thielert Technify Starter LH RH 02 8010 13210R1 Thielert Technify ELECTRICAL POWER LH Alt...

Page 296: ...rt Technify TAE 125 02 99 if installed LH Engine TAE 125 02 99 125 02 99 0003 01 Thielert Technify RH Engine TAE 125 02 99 125 02 99 0003 01 Thielert Technify LH ENGINE CONTROL UNIT ECU 05 7610 E000201 Thielert Technify LH ENGINE CONTROL UNIT ECU 05 7611 001903 Technify LH ENGINE CONTROL UNIT ECU 05 7611 001904 Technify ECU Firmware Thielert Technify ECU Mapping Thielert Technify RH ENGINE CONTROL...

Page 297: ...rt Technify LH Alternator 05 7150 E0006 02 Thielert Technify RH Alternator 05 7150 E0006 01 Thielert Technify RH Alternator 05 7150 E0006 02 Thielert Technify LH Alternator Regulator 05 7150 E0007 01 Thielert Technify RH Alternator Regulator 05 7150 E0007 01 Thielert Technify ENGINE FIRE WARNING LH overheat detector X 2003 2 Control Products Inc RH overheat detector X 2003 2 Control Products Inc L...

Page 298: ...or LH P 893 mt propeller Unfeathering accumulator RH P 893 mt propeller FUEL TANK SYSTEM Fuel probe assy LH inboard D60 2817 13 00 Diamond Aircraft Fuel probe assy LH inboard D60 2817 13 00_1 Diamond Aircraft Fuel probe assy RH inboard D60 2817 13 00 Diamond Aircraft Fuel probe assy RH inboard D60 2817 13 00_1 Diamond Aircraft Fuel probe assy LH outboard D60 2817 14 00 Diamond Aircraft Fuel probe ...

Page 299: ... B Weldon 1 940 0 878 151 400 3 846 ICE PROTECTION SYSTEM Porous panel outer wing LH 12102 21 CAV Aerospace Porous panel outer wing RH 12102 22 CAV Aerospace Porous panel center wing LH 12102 23 CAV Aerospace Porous panel center wing RH 12102 24 CAV Aerospace Porous panel horizontal tail LH 12102 25 CAV Aerospace Porous panel horizontal tail RH 12102 26 CAV Aerospace Porous panel vertical tail 121...

Page 300: ...etering pump 2 9513A 386 CAV Aerospace 4 180 1 896 40 160 1 020 De icing fluid tank D60 3013 24 50 Diamond Aircraft 8 140 3 692 38 390 0 975 Filter 1 F908R CAV Aerospace 0 680 0 308 40 160 1 020 Filter 2 F908R CAV Aerospace 0 680 0 308 40 160 1 020 Solenoid valve FV158H 28V CAV Aerospace 0 870 0 395 40 160 1 020 Solenoid valve FV158H 28V CAV Aerospace 0 870 0 395 40 160 1 020 High pressure switch ...

Page 301: ...HT MANUAL Doc No 7 01 05 E Diamond Aircraft Refer to Service Bulletin SB 42 007 latest effective issue for approved ECU firmware and mapping 1 The Amerex A620T is UL approved and may be used in airplanes registered in Canada and the USA For airplanes registered in other countries contact the local Airworthiness Authority Place ________________ Date ____________________ Signature __________________...

Page 302: ...DA 42 AFM Mass and Balance Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 6 34 Intentionally left blank ...

Page 303: ... COMPARTMENT 7 24 7 8 CANOPY REAR DOOR AND CABIN INTERIOR 7 24 7 9 POWER PLANT 7 28 7 9 1 ENGINES GENERAL 7 28 7 9 2 PROPELLER 7 29 7 9 3 OPERATING CONTROLS 7 32 7 9 4 ENGINE INSTRUMENTS 7 36 7 9 5 FUEL SYSTEM 7 38 7 9 6 COOLING SYSTEM 7 49 7 9 7 OIL SYSTEMS 7 50 7 9 8 TURBO CHARGER SYSTEM 7 51 7 9 9 FIRE DETECTION SYSTEM 7 52 7 10 ELECTRICAL SYSTEM 7 53 7 10 1 GENERAL 7 54 7 10 2 ENGINE CONTROL U...

Page 304: ...000 INTEGRATED AVIONICS SYSTEM 7 69 7 13 1 GENERAL 7 69 7 13 2 PRIMARY FLIGHT DISPLAY PFD 7 70 7 13 3 MULTI FUNCTION DISPLAY MFD 7 72 7 13 4 AUDIO PANEL 7 73 7 13 5 ATTITUDE AND HEADING REFERENCE SYSTEM AHRS 7 73 7 13 6 AIR DATA COMPUTER ADC 7 73 7 13 7 GWX 68 WEATHER RADAR 7 73 7 14 STRUCTURAL TEMPERATURE INDICATOR 7 74 ...

Page 305: ...he engine compartment ineach nacelle is separated from the other structure with a firewall The fire protection on the firewall is of a special fire resistant matting which is covered on the engine side by stainless steel cladding Wings The wings have a front and rear spar each wing has a top shell and a bottom shell The whole wing is fail safe design The wings as well as the ailerons and flaps are...

Page 306: ...P CFRP composite sandwich Hinges There are 4 hinges 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 jam nut which has locking varnish applied to it Damage to thi...

Page 307: ...of this roll pin can lead to the loss of the hinge pin and a consequent loss of flight safety Operation Each part is connected with a flap control horn to the push rods of the flap control system A rod end bearing is screwed into a steel push rod and locked by means of a jam nut which has locking varnish applied to it Damage to this varnish can indicate a twisting and thus a change to the adjustme...

Page 308: ...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 309: ...both engines exceeds approximately 20 approach power setting and the flap selector switch is set to LDG This is 2 5 less than the 15 5 full deflection The linear actuator acts as a movable stop and is controlled by three switches one for each power lever and one for the flap selector When the power of one engine is reduced below approximately 20 or the flap selector is not in the LDG position full...

Page 310: ...t 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 inspection Operation Steel cables the eyes of which are connected to the bolts on the bracket ...

Page 311: ...onsole below the instrument panel A mark on the wheel shows the center position and the direction of movement Turn wheel to the right right turn Turn wheel to the left left turn Pedal Adjustment NOTE The pedals 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 ...

Page 312: ... on the ground The pedals are adjusted using a rocker switch located on the rear wall of the 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 cor...

Page 313: ...DA 42 AFM Airplane Description Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 7 11 7 4 INSTRUMENT PANEL ...

Page 314: ...iver 9 Rotary buttons for instrument lighting and flood light 25 Multi Function Display MFD 10 Light switches 26 De Ice control panel 11 Emergency switch 27 Autopilot control unit 12 Flap selector switch 28 Alt air lever 13 Landing gear switch 29 Landing gear emergency extension lever 14 Alternate static valve 30 Oxygen pressure indicator 15 Microphone socket 31 Oxygen control knob 16 Ventilation ...

Page 315: ...ell as on the central console above the passengers heads The spherical nozzles are opened and closed by twisting Unconditioned ambient air is supplied to the interior through an inlet on the lower side of the RH center wing stub To increase cabin temperatures when operating at low outside air temperatures a winter kit ventilation may be installed at the inlet The winter kit ventilation consists of...

Page 316: ...keeps the landing gear in the retracted position A pressurized gas container acts as an accumulator which keeps the systempressure constant by replacing the volume lost due to the normal actuator leakages This prevents a permanent starting of the hydraulic pump in flight Springs assist the hydraulic system in gear extension and locking the gear in the down position After the gears are down and the...

Page 317: ...e retracted position by hydraulic pressure gravity will allow the gear to extend if the system fails for any reason To extend and lock the gears in the event of failure it is only necessary to relieve the hydraulic pressure by means of the emergency gear extension lever which is located under the instrument panel to the left of the center console Pulling this lever releases the hydraulic pressure ...

Page 318: ...ders The following schematic Figures show the system conditions for each operating mode In Figure 1 the extension of the landing gear is shown To reduce the amount of pumped hydraulic fluid during this operation the return flow is partly led into the feeding flow of the system TheFigurebelowshowsthesystemstatuswhen the landing gear is extended All hydraulic cylinders are under high pressure ...

Page 319: ...right hydraulic valve the fluid flow in the hydraulic system is started due to different piston areas of the landing gear cylinders although the pressure on both sides of the system is equal While the landing gear is retracted both valves are energized and excessive hydraulic fluid on one side is drained into the tank This configuration of the system is shown in the following Figure ...

Page 320: ...ev 8 15 Dec 2017 Doc No 7 01 05 E For an emergency extension of the landing gear the hydraulic fluid can pass through an emergency extension valve so that the gear is extended by gravity The condition of the system is shown in the Figure below ...

Page 321: ...ng 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 catches Brake pressure is built up by multiple operation of the toe brake pedals and is maintained until the parkin...

Page 322: ... belt lock The backs of the rear seats can be laid forward after pulling upwards on the locking bolt knob If front seats with adjustable backrests are installed OÄM 42 067 or OÄM 42 259 the angle of the backrest and the lumbar can be adjusted for best comfort The backrest control lever is situated on the outboard side of the backrest if OÄM 42 067 is installed The backrest release button in case o...

Page 323: ... the backrest lever or release the button If OÄM 42 259 is installed and in case of a malfunction of the release button the backrest can be moved into the upright position by pulling the backrest 48 daN 108 lbf in flight FWD direction If OÄM 42 067 is installed and in case of a defective adjustment mechanism the outboard friction adjustment screw can be tightened with a10mmhexagonnutinclockwisedir...

Page 324: ... AFM Page 7 22 Rev 8 15 Dec 2017 Doc No 7 01 05 E Outboard Hinge Inboard Hinge Lamella Package Friction Adjustment Screw Seat Lever Lumbar Support Lever Lumbar Support If seats with adjustable backrests are installed OÄM 42 067 ...

Page 325: ...plane Description Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 7 23 If seats with adjustable backrest are installed OÄM 42 259 Lumbar Support Inboard Hinge Lumbar Support Lever Outboard Hinge Bowden Cable Release Button ...

Page 326: ...lts lock into mating holes in polyethylene blocks Cooling gap position A second setting allows the bolts to lock in leaving a gap under the forward canopy The canopy can be blocked by a locking device on the left side near the canopy opening lever by turning the key clockwise The closed and blocked canopy can be opened from inside by pulling the lever inside the opening handle WARNING The airplane...

Page 327: ...y before flight in order to assure emergency access from outside Heating and Ventilation Heating and ventilation are operated using two levers located on the small center console under the instrument panel Right lever up HEATING ON Seats Floor down HEATING OFF Center lever up DEFROST ON Airflow to canopy down DEFROST OFF The heat of the RH engine is used for the front seats and floor the heat of t...

Page 328: ...orated an emergency axe is installed on the floor panel under the co pilot s seat see Figure below If the canopy can not be opened in case of an emergency use the emergency axe to break through the canopy WARNING Make sure not to harm other persons by using the emergency axe WARNING Beware of sharp edges and fragments of the broken canopy ...

Page 329: ...gency egress hammer is installed on the floor panel under the co pilot s seat If the canopy can not be opened in case of an emergency use the emergency egress hammer to break through the canopy WARNING Make sure not to harm other persons by using the emergency egress hammer WARNING Beware of sharp edges and fragments of the broken canopy ...

Page 330: ...er with Intercooler Displacement TAE 125 01 engine 1689 cm 103 in TAE 125 02 99 engine MÄM 42 198 carried out 1991 cm 121 5 in Max power 99 kW 135 DIN HP at 2300 RPM at sea level and ISA Max continuous power 99 kW 135 DIN HP at 2300 RPM at sea level and ISA Theindicationsformonitoringimportantengineparametersduringoperationareintegrated within the Garmin G1000 display Each engine can only be opera...

Page 331: ...owest weight whilst minimizing vibration Propeller Control The propeller pitch control system is integrated into the engine The pitch is controlled automatically by the ECU To change the blade pitch angle gearbox oil is pumped into the propeller hub The oil pressure is regulated by an electrically operated valve the governor valve which is controlled by the ECU Increasing the oil pressure leads to...

Page 332: ... to negative acceleration The hydraulic pressure keeps the propeller pitch angle below the start lock position or moves the propeller blades beyond the start lock position Feathering To feather the propeller the engine must be shut down with the appropriate ENGINE MASTER switch This will open the electric governor valve All oil will flow back from the propeller hub allowing the blades to move into...

Page 333: ...cumulator will move the propeller blades into a low pitch position As soon as the propeller starts turning and the gearbox oil operates the accumulator will be refilled Ground Operation CAUTION Operation on the ground at high RPM should be avoided as far as possible as the blades could suffer stone damage For this reason a suitable site for engine runs should be selected where there are no loose s...

Page 334: ...th the power lever If the power lever is in a low power position as for a landing approach while the landing gear is retracted an aural warning alerts the pilot to the retracted landing gear If installed a CHECK GEAR caution is indicated on the PFD additionally A propeller governor which is controlled by the ECU is flanged onto the front of each engine The propeller governor oil circuit is supplie...

Page 335: ... of a malfunction of the engine control unit In this case the reduced engine performance should be taken into consideration ELECT MASTER The electric master switch has two positions OFF disconnecting battery power ON connecting battery power to the power distribution system ENGINE MASTER Each engine can only be cranked with its ENGINE MASTER switched to ON When activated the ENGINE MASTER provides...

Page 336: ...erent functions Power lever at IDLE and RPM below approximately 900 By pushing and holding the button until the end of the procedure the self test of each engine control unit is started The procedure is possible on the ground as well as during flight but only if the power lever is in the IDLE position Otherwise the test will not start During the procedure the ECU performs a switch from ECU A to EC...

Page 337: ... The ALTERNATE AIR operating lever which serves both engines simultaneously is located under the instrument panel to the right of the center console To open the alternate air source the lever is pulled to the rear Normally the alternate air source is closed with the lever in the forward position Placard on the lever forward position ALTERNATE AIR Placard on the lever visible when lever is in the r...

Page 338: ...gine instruments are displayed on the Garmin G1000 MFD Also refer to Section 7 13 3 MULTI FUNCTION DISPLAY MFD Indications for the LH engine are on the left side indications for the RH engine are on the right side Default page Display when pushing Display when pushing Engine the SYSTEM button the FUEL button ...

Page 339: ...ane s fuel quantity indicators The values shown are numbers which are calculated from the last fuel quantity update done by the pilot and actual fuel flow data Therefore the endurance and range data is for information only and must not be used for flight planning Designation Indication Unit LOAD Available power RPM Propeller RPM 1 min FUEL FLOW Fuel flow US gal hr OIL TEMP Engine oil temperature C...

Page 340: ...Airplane Description DA 42 AFM Page 7 38 Rev 8 15 Dec 2017 Doc No 7 01 05 E 7 9 5 FUEL SYSTEM General ...

Page 341: ...tion nozzles one per cylinder are supplied with fuel by the common rail Pressure inside the rail is generated by a high pressure pump which receives fuel from a low pressure pump Depending on the power setting the rail pressure is controlled by the ECU through an electric valve Both pumps are powered mechanically by the engine Fuel that is not injected is fed back into the appropriate wing tank Bo...

Page 342: ...extend range and keep fuel weight balanced during single engine operation With the fuel selector valve both the feeding and the return line are switched The desired position is reached by pulling the lever back To reach the OFF position a safety guard must be twisted This is to ensure that this selection is not made unintentionally NOTE If one engine is inoperative the fuel selector valve for this...

Page 343: ...ector Valve Positions Possible operating modes of the three fuel selector valve positions are outlined systematically in the following scheme The Figures below show fuel flows for the RH engine fuel flows LH are alike Figure 1 Normal Operation Figure 2 CROSS FEED Operation Figure 3 Shut off Position ...

Page 344: ...ition of the RH fuel selector valve the RH tank then feeds both engines as shown in Figure 4 below or only the LH engine when the fuel selector valve of the RH engine is in shut off position as shown in Figure 5 below Figure 4 Fuel selector valve RH normal operation position fuel selector valve LH CROSSFEED position Figure 5 Fuel selector RH valve shut off position fuel selector valve LH CROSSFEED...

Page 345: ... check valve with capillary allows air to enter the tank but prevents flow of fuel to the outside The capillary equalizes the air pressure during climb The hose terminals are located on the underside of the wing approximately 2 m 7 ft from the wing tip In each tank a coarse filter finger filter is fitted before the outlet To allow draining of the tank there is an outlet valve at its lowest point A...

Page 346: ...to the auxiliary tank The vent line for the auxiliary fuel tank has a check valve with capillary It allows air to enter the tank but prevents flow of fuel to the outside The capillary equalizes the air pressure during climb A fuel drain valve is located at the rear of each auxiliary tank Operation Two FUEL TRANSFER switches in the cockpit are used to activate the fuel transfer pumps and to open th...

Page 347: ... R FUEL TRANSFER FAIL The flight plan must be amended accordingly The fuel transfer pumps and the solenoid valves are electrically connected to the LH main bus and protected by a 5 A or 7 5 A circuit breaker if no ice protection system OÄM 42 053 is installed Otherwise the fuel transfer pumps and the ice protection system OÄM 42 053 are protected by a 10 A circuit breaker The fuel transfer pumps a...

Page 348: ...he fuel quantity measuring device has a recess which fits the airfoil of the wing in front of the fuel tank drain which lies approximately 10 cm 4 in outboard of the engine nacelle The metal connector is pressed against the drain of the tank The amount of fuel in the tank can now be read off from the vertical ascending pipe For an exact indication the airplane must stand on level ground and the me...

Page 349: ...Diesel Fuel with Jet Fuel is used If the fuel blend is uncertain the engine must not be started in this temperature range either If the airplane is being operated with Jet Fuel operation in the yellow temperature range is permissible Fuel Grade Approved fuel grades are listed in Section 2 14 FUEL As the fuel grade is important concerning operating temperature limitations the pilot must be sure abo...

Page 350: ...provide information about the fuel grade it is recommended to enter the fuel grade in the airplane log each time fuel is refilled CAUTION If the airplane is operated with Diesel Fuel or a blend of Diesel Fuel with Jet Fuel the use of the auxiliary tanks if installed OÄM 42 056 is not permitted ...

Page 351: ...w It therefore allows the engine towarm up quickly Upon reaching a certain temperature approximately 88 C or 190 F the radiator is activated by a thermostat valve Additionally a coolant to air heat exchanger is provided for the cabin heat system The flow through the heat exchanger is independent of the coolant temperature An expansion tank helps to adjust the pressure in the system The system is p...

Page 352: ...er cowling If required oil can also be filled in there for approved oil grades refer to Section 2 4 POWER PLANT LIMITATIONS Gearbox and Propeller Governor System The second oil circuit lubricates the gearbox and serves the governor system and the regulation of the propeller The gearbox oil quantity can be checked with the help of an inspection glass which can be reached through an inspection hole ...

Page 353: ...the exhaust gases are guided through the lower cowling to the exterior of the airplane Excess exhaust gases bypass the turbine The bypass is controlled by the ECU through the waste gate valve A manifold pressure sensor behind the compressor allows the ECU to calculate the correct position of the waste gate valve This prevents excessive manifold pressures at low density altitudes The intake air is ...

Page 354: ... F the overheat detector closes the electric circuit and a warning message appears in the annunciation window of the G1000 PFD To test the fire detectors refer to Section 4A 6 1 PREFLIGHT INSPECTION push the test button located next to the gear selector switch An aural alert and the fire warning message for the LH and RH engine should appear in the annunciation window of the G1000 PFD CAUTION If t...

Page 355: ...DA 42 AFM Airplane Description Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 7 53 7 10 ELECTRICAL SYSTEM ...

Page 356: ... Ampère circuit breaker Both main busses are connected to the BATTERY BUS via a 90 Ampère circuit breaker Both generator power output lines also run through a current sensor for each alternator which provides an indication of the power being supplied to the electrical system by an alternator including the current for battery charging on the G1000 In the event of a main battery failure the field of...

Page 357: ...eratures Thus the load is partly shifted to the alternator with the lower internal temperature This system is able to balance the actual load within a few amps between the two alternators installed Storage Main battery power is stored in a 24 V 10 Ah lead acid battery mounted on the right aft side of the front baggage compartment The main battery is connected to the HOT BATTERY BUS and to the BATT...

Page 358: ... RH MAIN BUS and heavy duty power to both starters ECU BUS The LH RH ECU BUS is connected to the LH RH MAIN BUS via a diode and connected to the power output line of the alternator via diode and a 30 Ampère circuit breaker and provides power for the ECU A and ECU B via the LH RH ECU A B relays which are controlled by the LH RH ENGINE MASTER switch The LH RH ENGINE MASTER switch must be set to ON t...

Page 359: ...adio position lights etc are connected to the appropriate bus via automatic circuit breakers Designations and abbreviations used to identify the circuit breakers are explained in Section 1 5 DEFINITIONS AND ABBREVIATIONS Voltmeter The voltmeter displays the voltage of the electrical system Under normal operating conditions the alternator voltage is shown otherwise it displays the main battery volt...

Page 360: ...nt panel Instrument Lighting With a rotary button INSTRUMENT in the LH section of the instrument panel the internal lighting of the instruments is switched on and its brightness is adjusted Pitot Heating The Pitot probe which provides measurement for the Pitot static system is electrically heated The heating is activated with a switch PITOT HEAT located on the row of switches on the instrument pan...

Page 361: ...8 Volt DC power socket located on the lower surface of the fuselage nose section When external power is connected the control relay is energized and the external power comes online The socket itself has three pins A large negative pin A large positive pin A small positive pin A diode protects the system from reverse polarity ...

Page 362: ... Oil temperature lubrication system engine OIL TEMP Oil pressure lubrication system engine OIL PRES Coolant temperature COOLANT TEMP Gearbox temperature GEARBOX Camshaft RPM twice Crankshaft RPM twice Fuel pressure in the common rail Manifold pressure Manifold air temperature Ambient air pressure Propeller governor oil pressure Power lever position twice Voltage Starter switch signal Fuel pressure...

Page 363: ... Status ECU B Normally each engine is controlled and regulated by the appropriate ECU A The ECU B is a backup system to ensure redundancy In case of an internal error during operation or the loss of a sensor signal the system automatically switches to ECU B If the loss of the sensor signal was the cause for the error the system automatically switches back to ECU A A fault in one of the ECUs is ind...

Page 364: ...r from newest top to oldest bottom At the low right corner of the display there is a MSG message soft key The MSG key provides two functions in the CAS 1 Pressing the MSG key acknowledges a new master warning caution advisory indication 2 An additional MSG key press with no master alert indication active will open a pop up Auxiliary Flight Display AFD page that contains information for all active ...

Page 365: ...ble Tone Warning Red May require immediate corrective action Warning chime tone which repeats without delay until acknowledged by the crew Caution Amber May require future corrective action Single warning chime tone Annunciation Advisory White None Message Advisory White None Safe Operation Annunciation Green Lowest None ...

Page 366: ... FIRE The annunciation is active when an engine fire is detected L R STARTER This annunciation is used to indicate to the pilot that the starter is engaged when it should not be DOOR OPEN The annunciation is used to indicate to the pilot if the baggage canopy or rear door is open POSN ERROR The annunciation is active when the G1000 will no longer provide GPS based navigational guidance ATTITUDE FA...

Page 367: ...ng input from the AHRS WARN This annunciation constitutes a RAIM position warning The nav deviation bar is removed Audible Warning Alerts Warning Alerts Meaning Cause Landing Gear Retracted A warning chime tone which repeats without delay is active when the landing gear is retracted while the flaps move into the LDG position or when the POWER lever is placed in a position below approx 20 ...

Page 368: ...iation is active when engine coolant level is low PITOT FAIL The annunciation is active when the Pitot heater is failed PITOT HT OFF The annunciation is active when the Pitot heat is off STAL HT FAIL The annunciation is active when the stall heater is failed STAL HT OFF The annunciation is active when the stall heater is off STICK LIMIT Control stick limiting system variable elevator stop has fail...

Page 369: ...plugs are powered L R FUEL XFER The annunciation is active when fuel transfer from auxiliary to main tank is in progress Message Advisory Alerts on the G1000 Advisory Alerts Meaning Cause PFD FAN FAIL The annunciation is active when the PFD fan is inoperative MFD FAN FAIL The annunciation is active when the MFD fan is inoperative GIA FAN FAIL The annunciation is active when the GIA fan is inoperat...

Page 370: ... the static pressure in the cabin can be used as static pressure source in the event of a failure of the Pitot static system If an autopilot system is installed additional static sources may be installed 7 12 STALL WARNING SYSTEM The lift detector of the DA 42 is located on the front edge of the left wing below the wing chord line It is supplied electrically and provides a stall warning before the...

Page 371: ...on system to alert the pilot of certain abnormal conditions A remote avionic box is located behind the aft baggage compartment frame A push to talk PTT button for the COM portion of the G1000 is mounted on the end of each control stick There are connection facilities for up to 4 headsets between the front seats Refer to the Garmin G1000 Cockpit Reference Guide Garmin P N 190 00406 latest effective...

Page 372: ...scale above the compass rose full scale deflection is equal to a standard rate turn The following controls are available on the PFD clockwise from top right Communications frequency volume and squelch knob Communications frequency set knobs Communications frequency transfer button Altimeter setting knob baro set Course knob Map range knob and cursor control FMS control buttons and knob PFD softkey...

Page 373: ... caution annunciator will flash on the PFD accompanied by an aural tone A warning is accompanied by a repeating tone and a caution is accompanied by a single tone Acknowledging the alert will cancel the flashing and provide a text description of the message Refer to Chapter 3 EMERGENCY PROCEDURES Chapter 4B ABNORMALOPERATINGPROCEDURES andSection7 10 3 WARNING CAUTION AND ADVISORY LIGHTS ...

Page 374: ...rgency use by pressing the DISPLAY BACKUP button on the audio panel In the composite mode the full crew alerting function remains but no map functions are available 7 13 3 MULTI FUNCTION DISPLAY MFD The Multi Function Display MFD typically displays engine data maps terrain traffic and topography displays and flight planning and progress information The display unit is identical to the PFD and cont...

Page 375: ...of these inputs Status messages alert the crew of the loss of any of these inputs The AHRS will align while the airplane is in motion but will align quicker if the wings are kept level during the alignment process 7 13 6 AIR DATA COMPUTER ADC The Air Data Computer ADC provides airspeed altitude vertical speed and air temperature to the display system In addition to the primary displays this inform...

Page 376: ...zero fuel mass exceeds 1650 kg 3638 lb At temperatures below the 55 C 131 F limit the indicator appears all red with a faint indication of 55 C At temperatures exceeding the 55 C 131 F limit the indicator displays a clearly contrasting red 55 C on a black background see Figure below NOTE At temperatures approaching the limit the background will progressively darken prior to turning black this indi...

Page 377: ...DA 42 AFM Airplane Description Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 7 75 TEMPERATURE INDICATOR PLACARD Location of Temperature Indicator and Placard LH MLG bay shown RH MLG bay opposite ...

Page 378: ...Airplane Description DA 42 AFM Page 7 76 Rev 8 15 Dec 2017 Doc No 7 01 05 E Intentionally left blank ...

Page 379: ...RVICING 8 3 8 4 1 REFUELING 8 3 8 4 2 ENGINE OIL LEVEL CHECK 8 5 8 4 3 GEARBOX OIL LEVEL CHECK 8 6 8 4 4 TIRE INFLATION PRESSURE CHECK 8 6 8 5 GROUND HANDLING ROAD TRANSPORT 8 7 8 5 1 GROUND HANDLING 8 7 8 5 2 PARKING 8 10 8 5 3 MOORING 8 13 8 5 4 JACKING 8 13 8 6 CLEANING AND CARE 8 14 8 6 1 PAINTED SURFACES 8 14 8 6 2 CANOPY AND REAR DOOR 8 14 8 6 3 PROPELLER 8 15 8 6 4 ENGINE 8 15 8 6 5 INTERIO...

Page 380: ...non recurring engine inspection must be performed on new engines after 3 to 6 hours The respective inspection checklists are prescribed in the Airplane Maintenance Manual Chapter 05 For maintenance work on engine and propeller the currently effective Operator s Manuals Service Instructions Service Letters and Service Bulletins of TAE and mt Propeller must be followed For airframe inspections the c...

Page 381: ...t allow fire sparks or heat near fuel Fuel burns violently and can cause injury to persons and damage to the airplane WARNING Do not get fuel on your skin Fuel can cause skin disease WARNING Connect the airplane and the fuel supply vehicle to electrical ground before refueling If you do not ground the airplane static electricity can cause fire during refueling WARNING Make sure that a suitable fir...

Page 382: ...only approved fuel types given in Chapter 2 1 Ground the airplane and the fuel supply vehicle electrically 2 Remove the fuel filler cap located on top of the outer wing Check cap retaining cable for damage 3 Refuel the airplane 4 Install the fuel filler cap 5 Repeat steps 2 to 4 for the other wing 6 Remove the ground cable from the airplane and the fuel supply vehicle ...

Page 383: ...90 and after 30 minutes 100 of the engine oil has returned to the oil pan Do not overfill the engines with engine oil 1 Open the inspection door on top of the upper left cowling 2 Remove the filler cap 3 Clean the oil dip stick 4 Install the filler cap 5 Remove the filler cap again 6 Read the oil level from the dip stick 7 If necessary add engine oil and repeat steps 3 to 6 8 Install the filler ca...

Page 384: ...w 3 Close the inspection door 4 Repeat steps 1 to 3 for the other engine 8 4 4 TIRE INFLATION PRESSURE CHECK 1 Remove dust cap from valve stem by turning counterclockwise 2 Connect tire gauge to valve stem read pressure 3 Correct pressure if necessary nose tire 6 0 bar 87 PSI main tires 4 7 bar 68 PSI if OÄM 42 195 is installed 4 5 bar 65 PSI if OÄM 42 195 is not installed 4 Install dust cap on va...

Page 385: ... Do not push on the spinners as you may damage the spinner which can cause vibration and damage to the engine Do not use force on the propeller tips or on the airplane control surfaces and do not push on the de icing nozzles if installed on the propeller blade root as you may damage the propeller the control surfaces or the de icing nozzles It is recommended to use the steering bar or a tow bar wh...

Page 386: ...Handling Care Maintenance DA 42 AFM Page 8 8 Rev 8 15 Dec 2017 Doc No 7 01 05 E Steering Bar or Tow Bar Attachment Max 40 Max 40 Nose Landing Gear Leg Tow Bar Steering Bar ...

Page 387: ...w vehicle should always be started and stopped slowly to avoid shock loads on the nose landing gear The maximum steering angle of 40 degrees to either side must not be exceeded WARNING The tow bar must be removed before starting the engine If the airplane must be pulled out of soft ground or deep snow towing lines must be used The towing lines should be attached to the main landing gear struts as ...

Page 388: ...entheairplanewillbeparked for less than 5 days Use the long term parking procedure when the airplane will be parked for 5 to 30 days Use the storage procedure when the airplane will be parked for more than 30 days NOTE If the airplane is not used for more than 4 weeks an engine ground run must be performed Refer to the Engine Operation and Maintenance Manual latest revision Control Surfaces Gust L...

Page 389: ...8 11 The control surfaces gust lock is installed as follows 1 Move the rudder pedals fully forward 2 Engage the control surfaces gustlock with the pedals 3 Engage the stick wrap straps around stick once 4 Attach the locks and tighten the straps For removal reverse the sequence ...

Page 390: ...Handling Care Maintenance DA 42 AFM Page 8 12 Rev 8 15 Dec 2017 Doc No 7 01 05 E ...

Page 391: ...e there is a hole which can be used to tie down the airplane to the ground Also on each wing near the wing tip an eyelet with a metric M8 thread can be installed and used as tie down points 8 5 4 JACKING The airplane can be jacked at the two jackpoints located on the lower side of the center wing s LH and RH root ribs as well as at the tail fin ...

Page 392: ...r alone and if necessary with a mild detergent An automotive paint cleaner can be used for stubborn spots For best results clean the airplane after the day s flying is ended so that the dirt will not become ingrained Oil stains exhaust stains etc on the lower fuselage skin can be removed with a cold detergent Before starting ensure that the detergent does not affect the surface finish Use commerci...

Page 393: ...t be consulted 8 6 4 ENGINE Engine cleaning is part of the scheduled inspections 8 6 5 INTERIOR SURFACES The interior should be cleaned using a vacuum cleaner All loose items pens bags etc should be removed or properly stored and secured All instruments can be cleaned using a soft dry cloth Plastic surfaces should be wiped clean using a damp cloth without any cleaning agents The leather interior s...

Page 394: ...ING Approved deicing fluids are Manufacturer Name Kilfrost TKS 80 Aeroshell Compound 07 Any source AL 5 DTD 406B 1 Remove any snow from the airplane using a soft brush 2 Spray deicing fluid onto ice covered surfaces using a suitable spray bottle 3 Use a soft piece of cloth to wipe the airplane dry ...

Page 395: ...DA 42 AFM Supplements Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 9 1 CHAPTER 9 SUPPLEMENTS Page 9 1 INTRODUCTION 9 2 9 2 LIST OF SUPPLEMENTS 9 3 ...

Page 396: ...e 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 397: ...P 140 0 01 Dec 2004 9 9 M00 DA 42 M 2 05 Sep 2011 9 9 M01 Belly Pod 2 30 Apr 2008 9 9 M02 Riegl Laserscanner System 1 18 Feb 2008 9 9 M10 Operator Desk 2 20 Apr 2015 9 9 M30 Universal Nose 3 23 Jan 2012 9 9 M32 Cobolt 350 with Scotty Satcom System 0 26 Aug 2008 9 9 M60 Nose Pod 1 19 Nov 2010 9 9 M130 Universal Nose 2 20 Dec 2010 9 9 M160 Nose Pod with Standard Baggage Compartment 0 18 Feb 2011 9 9...

Page 398: ...em if OÄM 42 053 is installed and OÄM 42 054 is not installed 2 12 Jan 2007 9 9 S03 Ice Protection System Known Icing if OÄM 42 053 and OÄM 42 054 are installed 3 27 May 2015 9 9 S04 Continuous Flow Oxygen System 3 10 Nov 2011 9 9 S05 Mission Power Supply System 1 18 Jul 2007 9 9 S06 G1000 Synthetic Vision Technology 0 01 May 2010 9 9 S07 TAE 125 02 114 Engine 2 17 Oct 2016 9 9 S10 Flight Data Log...

Page 399: ...DA 42 AFM Supplements Airplane S N Registration Date Sup No Title Rev No Date applicable YES NO Doc No 7 01 05 E Rev 8 15 Dec 2017 Page 9 5 9 9 9 9 9 9 9 9 ...

Page 400: ...nts DA 42 AFM Page 9 6 Rev 8 15 Dec 2017 Doc No 7 01 05 E NOTE The Supplement S05 is only valid if VÄM 42 002 has not been carried out If VÄM 42 002 was carried out Supplement S05 is replaced by Supplement M00 ...

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