DA 42 NG AFM

3-49 18-Feb-2009 3-50 18-Feb-2009 3-51 18-Feb-2009 3-52 18-Feb-2009 3-53 18-Feb-2009 3-54 18-Feb-2009 3-55 18-Feb-2009 3-56 18-Feb-2009 DA 42 NG AFM Introduction Doc. # 7.01.15-E Rev. 1 18-Feb-2009 Page 0 - 7 Ch. Page Date 3 3-57 18-Feb-2009 3-58 18-Feb-2009 3-59 18-Feb-2009 3-60 18-Feb-2009 3-61 18-Feb-2009 3-62 18-Feb-2009 3-63 18-Feb-2009 3-64 18-Feb-2009 3-65 18-Feb-2009 3-66 18-Feb-2009 3-67 18-Feb-2009 3-68 18-Feb-2009 3-69 18-Feb-2009 3-70 18-Feb-2009 Ch. Page Date 4A 4A-1 18-Feb-2009 4A-2 18-Feb-2009 4A-3 18-Feb-2009 4A-4 18-Feb-2009 4A-5 18-Feb-2009 4A-6 18-Feb-2009 4A-7 18-Feb-2009 4A-8 18-Feb-2009 4A-9 18-Feb-2009 4A-10 18-Feb-2009 Ch. Page Date 4A 4A-11 18-Feb-2009 4A-12 18-Feb-2009 4A-13 18-Feb-2009 4A-14 18-Feb-2009 4A-15 18-Feb-2009 4A-16 18-Feb-2009 4A-17 18-Feb-2009 4A-18 18-Feb-2009 4A-19 18-Feb-2009 4A-20 18-Feb-2009 4A-21 18-Feb-2009 4A-22 18-Feb-2009 4A-23 18-Feb-2009 4A-24 18-Feb-2009 4A-25 18-Feb-2009 4A-26 18-Feb-2009 4A-27 18-Feb-2009 4A-28 18-Feb-2009 4A-29 18-Feb-2009 4A-30 18-Feb-2009 4A-31 18-Feb-2009 4A-32 18-Feb-2009 4A-33 18-Feb-2009 4A-34 18-Feb-2009 4A-35 18-Feb-2009 4A-36 18-Feb-2009 4A-37 18-Feb-2009 4A-38 18-Feb-2009 Introduction DA 42 NG AFM Page 0 - 8 Rev. 1 18-Feb-2009 Doc. # 7.01.15-E Ch. Page Date 4A 4A-39 18-Feb-2009 4A-40 18-Feb-2009 4A-41 18-Feb-2009 4A-42 18-Feb-2009 4A-43 18-Feb-2009 4A-44 18-Feb-2009 4A-45 18-Feb-2009 4A-46 18-Feb-2009 4A-47 18-Feb-2009 4A-48 18-Feb-2009 4A-49 18-Feb-2009 4A-50 18-Feb-2009 4A-51 18-Feb-2009 4A-52 18-Feb-2009 4A-53 18-Feb-2009 4A-54 18-Feb-2009 4A-55 18-Feb-2009 4A-56 18-Feb-2009 4A-57 18-Feb-2009 4A-58 18-Feb-2009 4A-59 18-Feb-2009 4A-60 18-Feb-2009 4A-61 18-Feb-2009 4A-62 18-Feb-2009 4A-63 18-Feb-2009 4A-64 18-Feb-2009 Ch. Page Date 4B 4B-1 18-Feb-2009 4B-2 18-Feb-2009 4B-3 18-Feb-2009 4B-4 18-Feb-2009 4B-5 18-Feb-2009 4B-6 18-Feb-2009 4B-7 18-Feb-2009 4B-8 18-Feb-2009 4B-9 18-Feb-2009 4B-10 18-Feb-2009 4B-11 18-Feb-2009 4B-12 18-Feb-2009 4B-13 18-Feb-2009 4B-14 18-Feb-2009 4B-15 18-Feb-2009 4B-16 18-Feb-2009 4B-17 18-Feb-2009 4B-18 18-Feb-2009 4B-19 18-Feb-2009 4B-20 18-Feb-2009 4B-21 18-Feb-2009 4B-22 18-Feb-2009 4B-23 18-Feb-2009 4B-24 18-Feb-2009 4B-25 18-Feb-2009 4B-26 18-Feb-2009 4B-27 18-Feb-2009 4B-28 18-Feb-2009 DA 42 NG AFM Introduction Doc. # 7.01.15-E Rev. 1 18-Feb-2009 Page 0 - 9 Ch. Page Date 4B 4B-29 18-Feb-2009 4B-30 18-Feb-2009 4B-31 18-Feb-2009 4B-32 18-Feb-2009 4B-33 18-Feb-2009 4B-34 18-Feb-2009 4B-35 18-Feb-2009 4B-36 18-Feb-2009 4B-37 18-Feb-2009 4B-38 18-Feb-2009 4B-39 18-Feb-2009 4B-40 18-Feb-2009 4B-41 18-Feb-2009 4B-42 18-Feb-2009 4B-43 18-Feb-2009 4B-44 18-Feb-2009 Ch. Page Date 5 5-1 18-Feb-2009 5-2 18-Feb-2009 5-3 18-Feb-2009 5-4 18-Feb-2009 5-5 18-Feb-2009 5-6 18-Feb-2009 5-7 18-Feb-2009 5-8 18-Feb-2009 5-9 18-Feb-2009 5-10 18-Feb-2009 5-11 18-Feb-2009 5-12 18-Feb-2009 5-13 18-Feb-2009 5-14 18-Feb-2009 5-15 18-Feb-2009 5-16 18-Feb-2009 5-17 18-Feb-2009 5-18 18-Feb-2009 5-19 18-Feb-2009 5-20 18-Feb-2009 5-21 18-Feb-2009 5-22 18-Feb-2009 5-23 18-Feb-2009 5-24 18-Feb-2009 5-25 18-Feb-2009 5-26 18-Feb-2009 Introduction DA 42 NG AFM Page 0 - 10 Rev. 1 18-Feb-2009 Doc. # 7.01.15-E Ch. Page Date 6 6-1 18-Feb-2009 6-2 18-Feb-2009 6-3 18-Feb-2009 6-4 18-Feb-2009 6-5 18-Feb-2009 6-6 18-Feb-2009 6-7 18-Feb-2009 6-8 18-Feb-2009 6-9 18-Feb-2009 6-10 18-Feb-2009 6-11 18-Feb-2009 6-12 18-Feb-2009 6-13 18-Feb-2009 6-14 18-Feb-2009 6-15 18-Feb-2009 6-16 18-Feb-2009 6-17 18-Feb-2009 6-18 18-Feb-2009 6-19 18-Feb-2009 6-20 18-Feb-2009 6-21 18-Feb-2009 6-22 18-Feb-2009 6-23 18-Feb-2009 6-24 18-Feb-2009 6-25 18-Feb-2009 6-26 18-Feb-2009 Ch. Page Date 7 7-1 18-Feb-2009 7-2 18-Feb-2009 7-3 18-Feb-2009 7-4 18-Feb-2009 7-5 18-Feb-2009 7-6 18-Feb-2009 7-7 18-Feb-2009 7-8 18-Feb-2009 7-9 18-Feb-2009 7-10 18-Feb-2009 7-11 18-Feb-2009 7-12 18-Feb-2009 7-13 18-Feb-2009 7-14 18-Feb-2009 7-15 18-Feb-2009 7-16 18-Feb-2009 7-17 18-Feb-2009 7-18 18-Feb-2009 7-19 18-Feb-2009 7-20 18-Feb-2009 7-21 18-Feb-2009 7-22 18-Feb-2009 7-23 18-Feb-2009 7-24 18-Feb-2009 7-25 18-Feb-2009 7-26 18-Feb-2009 7-27 18-Feb-2009 7-28 18-Feb-2009 DA 42 NG AFM Introduction Doc. # 7.01.15-E Rev. 1 18-Feb-2009 Page 0 - 11 Ch. Page Date 7 7-29 18-Feb-2009 7-30 18-Feb-2009 7-31 18-Feb-2009 7-32 18-Feb-2009 7-33 18-Feb-2009 7-34 18-Feb-2009 7-35 18-Feb-2009 7-36 18-Feb-2009 7-37 18-Feb-2009 7-38 18-Feb-2009 7-39 18-Feb-2009 7-40 18-Feb-2009 7-41 18-Feb-2009 7-42 18-Feb-2009 7-43 18-Feb-2009 7-44 18-Feb-2009 7-45 18-Feb-2009 7-46 18-Feb-2009 7-47 18-Feb-2009 7-48 18-Feb-2009 7-49 18-Feb-2009 7-50 18-Feb-2009 7-51 18-Feb-2009 7-52 18-Feb-2009 7-53 18-Feb-2009 7-54 18-Feb-2009 7-55 18-Feb-2009 7-56 18-Feb-2009 Ch. Page Date 7 7-57 18-Feb-2009 7-58 18-Feb-2009 7-59 18-Feb-2009 7-60 18-Feb-2009 7-61 18-Feb-2009 7-62 18-Feb-2009 7-63 18-Feb-2009 7-64 18-Feb-2009 7-65 18-Feb-2009 7-66 18-Feb-2009 7-67 18-Feb-2009 7-68 18-Feb-2009 7-69 18-Feb-2009 7-70 18-Feb-2009 7-71 18-Feb-2009 7-72 18-Feb-2009 7-73 18-Feb-2009 7-74 18-Feb-2009 7-75 18-Feb-2009 7-76 18-Feb-2009 Introduction DA 42 NG AFM Page 0 - 12 Rev. 1 18-Feb-2009 Doc. # 7.01.15-E Ch. Page Date 8 8-1 18-Feb-2009 8-2 18-Feb-2009 8-3 18-Feb-2009 8-4 18-Feb-2009 8-5 18-Feb-2009 8-6 18-Feb-2009 8-7 18-Feb-2009 8-8 18-Feb-2009 8-9 18-Feb-2009 8-10 18-Feb-2009 8-11 18-Feb-2009 8-12 18-Feb-2009 Ch. Page Date 9 9-1 18-Feb-2009 9-2 18-Feb-2009 DA 42 NG AFM Introduction Doc. # 7.01.15-E Rev. 1 18-Feb-2009 Page 0 - 13 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 OPERATING LIMITATIONS (an approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 EMERGENCY 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 Introduction DA 42 NG AFM Page 0 - 14 Rev. 1 18-Feb-2009 Doc. # 7.01.15-E Intentionally left blank. DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 1 CHAPTER 1 GENERAL Page 1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2 CERTIFICATION BASIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.3 WARNINGS, CAUTIONS AND NOTES . . . . . . . . . . . . . . . . . . . . . . 1-4 1.4 DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 1.5 DEFINITIONS AND ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . 1-7 1.6 UNITS OF MEASUREMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-16 1.6.1 CONVERSION FACTORS . . . . . . . . . . . . . . . . . . . . . . . . . . 1-16 1.6.2 CONVERSION CHART LITERS / US GALLONS . . . . . . . . . 1-18 1.7 THREE-VIEW DRAWING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-19 1.8 G1000 AVIONICS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-20 1.9 SOURCE DOCUMENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-22 1.9.1 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-22 1.9.2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-23 1.9.3 AVIONICS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-23 General DA 42 NG AFM Page 1 - 2 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 1.1 INTRODUCTION This Airplane Flight Manual has been prepared in order to provide pilots and instructors with all the information required for the safe and efficient operation of the airplane. The Airplane Flight Manual includes all the data which must be made available to the pilot according to the JAR-23 requirement. Beyond this, it contains further data and operating instructions which, in the manufacturer’s opinion, could be of value to the pilot. Equipment and modification level (design details) 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 Source Installed Ice Protection System OÄM 42-053 9 yes 9 no Oxygen System OÄM 42-055 9 yes 9 no Auxiliary Fuel Tanks OÄM 42-056 9 yes 9 no Front Seats with Adjustable Backrest OÄM 42-067 9 yes 9 no Electrical Rudder Pedal Adjustment OÄM 42-070 9 yes 9 no Sun Visors OÄM 42-101 9 yes 9 no DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 3 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 Cockpit Reference Guide is the bag on the rear side of the forward left seat. CAUTION The DA 42 NG is a twin engine airplane. When the operating limitations and maintenance requirements are complied with, it has the high degree of reliability which is required by the certification basis. Nevertheless, an engine failure is not completely impossible. For this reason it is highly recom- mended 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. General DA 42 NG AFM Page 1 - 4 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 1.2 CERTIFICATION BASIS The certification basis is JAR-23, published on 11-Mar-1994, including Amdt. 1, and additional requirements as laid down in CRI A-01. 1.3 WARNINGS, CAUTIONS AND NOTES Special statements in the Airplane Flight Manual concerning the safety or operation of the airplane are highlighted by being prefixed by one of the following terms: WARNING means that the non-observation of the corresponding procedure leads to an immediate or important degradation in flight safety. CAUTION means that the non-observation of the corresponding procedure leads to a minor or to a more or less long term degradation in flight safety. NOTE draws the attention to any special item not directly related to safety but which is important or unusual. DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 5 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall Dimensions Span : 13.42 m 44 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 m² 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 m² 7.1 sq.ft. General DA 42 NG AFM Page 1 - 6 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E Wing Flaps Area (total, left + right) : 2.18 m² 23.5 sq.ft. Horizontal Tail Area : 2.35 m 2 25.3 sq.ft. Elevator area : 0.66 m² 7.1 sq.ft. Angle of incidence : -1.1° relative to longitudinal axis of airplane Vertical Tail Area : 2.43 m² 26.2 sq.ft. Rudder area : 0.78 m² 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; 10 PR, 120 mph Main wheel : 15x6.0-6; 6 PR, 120 mph DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 7 1.5 DEFINITIONS AND ABBREVIATIONS (a) Airspeeds CAS: Calibrated Airspeed. Indicated airspeed, corrected for installation and instrument errors. CAS equals TAS at standard atmospheric conditions (ISA) at MSL. IAS: Indicated Airspeed as shown on an airspeed indicator. KCAS: CAS in knots. KIAS: IAS in knots. TAS: True Airspeed. The speed of the airplane relative to the air. TAS is CAS corrected for errors due to altitude and temperature. v O: Operating Maneuvering Speed. Full or abrupt control surface movement is not permissible above this speed. v FE: Maximum Flaps Extended Speed. This speed must not be exceeded with the given flap setting. v LE: Maximum Landing Gear Extended Speed. This speed may not be exceeded if the landing gear is extended. vLOE: Maximum Landing Gear Operating Speed for Extension. This speed may not be exceeded during the extension of the landing gear. vLOR : Maximum Landing Gear Operating Speed for Retraction. This speed may not be exceeded during the retraction of the landing gear. vMC : Minimum Control Speed. Minimum speed necessary to be able to control the airplane in case of one engine inoperative. vNE: Never Exceed Speed in smooth air. This speed must not be exceeded in any operation. General DA 42 NG AFM Page 1 - 8 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E vNO: Maximum Structural Cruising Speed. This speed may be exceeded only in smooth air, and then only with caution. v S: Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration. v S0 : Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the landing configuration. v S1 : Stalling Speed, or the minimum continuous speed at which the airplane is still controllable with flaps and landing gear retracted. v SSE: Minimum Control Speed for Schooling. Minimum speed necessary in case of one engine intentionally inoperative / idle (training purposes). vx: Best Angle-of-Climb Speed. vy: Best Rate-of-Climb Speed. vYSE: Best Rate of-Climb Speed for one engine inoperative. (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 1013.25 hPa (29.92 inHg); the temperature gradient up to the altitude at which the temperature reaches -56.5 °C (-69.7 °F) is -0.0065 °C/m (-0.00357 °F/ft), and above this 0 °C/m (0 °F/ft). MSL: Mean Sea Level. OAT: Outside Air Temperature. DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 9 QNH: Theoretical atmospheric pressure at MSL, calculated from the elevation of the measuring point above MSL and the actual atmospheric pressure at the measuring point. Density Altitude: Altitude in ISA conditions at which the air density is equal to the current air density. Indicated Pressure Altitude: Altitude reading with altimeter set to 1013.25 hPa (29.92 inHg). Pressure Altitude: Altitude indicated by a barometric altimeter, which is set to 1013.25 hPa (29.92 inHg). The Pressure Altitude is the Indicated Pressure Altitude corrected for installation and instrument 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 speed of the crosswind component at which adequate maneuverabil- ity for take-off and landing has been demonstrated during type certification. General DA 42 NG AFM Page 1 - 10 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E MET: Weather, weather advice. NAV: Navigation, route planning. RoC: Rate of Climb. (d) Mass and Balance CG: Center of Gravity, also called 'center of mass'. Imaginary point in which the airplane mass is assumed to be concentrated for mass and balance calculations. Its distance from the Datum Plane is equal to the Center of Gravity Moment Arm. Center of Gravity Moment Arm: The Moment Arm which is obtained if one divides the sum of the individual moments of the airplane by its total mass. Center of Gravity Limits: The Center of Gravity range within which the airplane, at a given mass, must be operated. DP: Datum Plane; an imaginary vertical plane from which all horizontal distances for center of gravity calculations are measured. Empty Mass: The mass of the airplane including unusable fuel, all operating fluids and the maximum quantity of oil. Maximum Take-off Mass: The maximum permissible mass for take-off. DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 11 Maximum Landing Mass: The highest mass for landing conditions at the maximum descent velocity. This velocity was used in the strength calculations to determine the landing gear loads during a particularly hard landing. Moment Arm: The horizontal distance from the Datum Plane to the Center of Gravity of a component. Moment: The mass of a component multiplied by its moment arm. Usable fuel: The quantity of fuel available for flight planning. Unusable fuel: The quantity of fuel remaining in the tank which cannot be used for flight. Useful load: The difference between take-off mass and empty mass. (e) Engine EECU: Electr. Engine Control Unit RPM: Revolutions per minute (rotational speed of the propeller) Engine starting fuel temperature: Above this fuel temperature the engine may be started. Take-off fuel temperature: Above this fuel temperature take-off power setting is permitted. OEI: One engine inoperative General DA 42 NG AFM Page 1 - 12 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E (f) Designation of the Circuit Breakers on the Instrument Panel LH MAIN BUS: COM1 COM Radio No. 1 GPS/NAV1 Global Positioning System and NAV Receiver No. 1 XPDR Transponder ENG INST Engine Instruments PITOT Pitot Heating System XFER PUMP/DE-ICE Aux Fuel Pump / De-Icing System TAXI/MAP/ACL Taxi-, Map-, Anti Collision Light FLOOD Flood Light 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 / Start INST LT/ NAV LT Instrument-, Navigation (Position) Light AV/CDU/FAN Avionic-, CDU-Cooling Fans AVIONIC BUS Avionic Bus AV CONT./AP. WRN. Avionic Control / Autopilot Warning (not used) DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 13 AVIONICS BUS: COM2 COM Radio No. 2 GPS/NAV2 Global Positioning System and NAV Receiver No. 2 AUDIO 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 LH ECU BUS: ECU A LH ECU A ECU B LH ECU B General DA 42 NG AFM Page 1 - 14 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E FUEL PUMPS LH ENGINE: FUEL PUMP A LH ECU A Fuel Pump FUEL PUMP B LH ECU B Fuel Pump RH ENG ECU BUS: ECU BUS RH ECU Bus ECU B RH ECU B ECU A RH ECU A RH BUS: ALT.RH RH Alternator BATT Battery RH ECU BUS: ECU A RH ECU A ECU B RH ECU B FUEL PUMPS RH ENGINE: FUEL PUMP A RH ECU A Fuel Pump FUEL PUMP B RH ECU B Fuel Pump DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 15 (g) Equipment ELT: Emergency Locator Transmitter (h) Design Change Advisories MÄM: Mandatory Design Change Advisory OÄM: Optional Design Change Advisory VÄM: Variant Design Change Advisory (i) Miscellaneous ACG: Austro Control GmbH (Austrian Airworthiness Authority) 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: Primary Certification Authority General DA 42 NG AFM Page 1 - 16 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 1.6 UNITS OF MEASUREMENT 1.6.1 CONVERSION FACTORS Dimension SI-Units US Units Conversion Length [mm] millimeters [m] meters [km] kilometers [in] inches [ft] feet [NM] nautical miles [mm] / 25.4 = [in] [m] / 0.3048 = [ft] [km] / 1.852 = [NM] Volume [l] liters [US gal] US gallons [qts] US quarts [l] / 3.7854 = [US 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 square inch [hPa] = [mbar] [hPa] / 33.86 = [inHg] [bar] x 14.504 = [psi] Tempera- ture [°C] degrees Celsius [°F] degrees Fahrenheit [°C]x1.8 + 32 = [°F] ([°F] - 32)/1.8 = [°C] DA 42 NG AFM General Dimension SI-Units US Units Conversion Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 17 Intensity of electric current [A] ampères -- Electric charge (battery capacity) [Ah] ampère-hours -- Electric potential [V] volts -- Time [sec] seconds -- General DA 42 NG AFM Page 1 - 18 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 1.6.2 CONVERSION CHART LITERS / US GALLONS Liters US Gallons US Gallons Liters 5 1.3 1 3.8 10 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 DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 19 1.7 THREE-VIEW DRAWING General DA 42 NG AFM Page 1 - 20 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 1.8 G1000 AVIONICS SYSTEM 1. The G1000 Integrated Avionics System is a fully integrated flight, engine, communication, navigation and surveillance instrumentation system. The system consists of a Primary Flight Display (PFD), Multi-Function Display (MFD), audio panel, Air Data Computer (ADC), Attitude and Heading Reference System (AHRS), engine sensors and processing unit (GEA), and integrated avionics (GIA) containing VHF communications, VHF navigation, and GPS (Global Positioning System). 2. The primary function of the PFD is to provide attitude, heading, air data, navigation, and alerting information to the pilot. The PFD may also be used for flight planning. The primary function of the MFD is to provide engine information, mapping, terrain information, autopilot operation, and for 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 primary function of the GPS portion of the system is to acquire signals from the GPS satellites, recover orbital data, make range and Doppler measurements, and process this information in real-time to obtain the user's position, velocity, and time. 4. Provided a Garmin G1000 GPS receiver is receiving adequate usable signals, it has been demonstrated capable of and has been shown to meet the accuracy specifications for: (a) VFR/IFR enroute, oceanic, terminal, and non-precision instrument approach (GPS, Loran-C, VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV) operation within the U.S. National Airspace System in accordance with AC 20-138A. DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 21 (b) RNAV (GPS) Approaches - The G1000 GPS meets the requirements of AC 20-138(A) for GPS based RNAV approaches. This includes RNAV approaches labeled as RNAV (GPS), provided GPS sensor data is valid. (c) The system meets the accuracy of RNP5 airspace (BRNAV) requirements of AC 90-96 and in accordance with AC 20-138A, EASA AMC 20-4, and FAA Order 8110.60 for oceanic and remote airspace operations, provided it is receiving usable navigation information from the GPS receiver. Navigation is accomplished using the WGS-84 (NAD-83) coordinate reference datum. GPS navigation data is based upon use of only the GPS operated by the United States of America. General DA 42 NG AFM Page 1 - 22 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 1.9 SOURCE DOCUMENTATION This section lists documents, manuals and other literature that were used as sources for the Airplane Flight Manual, and indicates the respective publisher. However, only the information given in the Airplane Flight Manual is valid. 1.9.1 ENGINE Address: Austro Engine GmbH Rudolf Diesel-Str. 11 A-2700 Wiener Neustadt AUSTRIA Phone: +43-2622-23 000 Fax: +43-2622-23 000 - 2711 Internet: www.austroengine.at Documents: Operation Manual, E4.01.01 Rev. 1 or later Engine TC-Holder: Diamond Aircraft Industries GmbH N.A. Otto-Straße 5 A-2700 Wiener Neustadt AUSTRIA DA 42 NG AFM General Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 1 - 23 1.9.2 PROPELLER Address: mt-propeller Airport Straubing Wallmühle D-94348 Atting GERMANY Phone: +49-9429-9409-0 E-mail: sales@mt-propeller.com Website: www.mt-propeller.de Documents: E-124, Operation and Installation Manual Hydraulically controlled variable pitch propeller MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25 1.9.3 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 190-00963-00, latest revision G1000 Pilot´s Guide P/N 190-00962-00, latest revision General DA 42 NG AFM Page 1 - 24 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E Intentionally left blank. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 1 CHAPTER 2 OPERATING LIMITATIONS Page 2.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 2.2 AIRSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 2.3 AIRSPEED INDICATOR MARKINGS . . . . . . . . . . . . . . . . . . . . . . . . 2-5 2.4 POWER-PLANT LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 2.5 ENGINE INSTRUMENT MARKINGS . . . . . . . . . . . . . . . . . . . . . . . 2-11 2.6 WARNING, CAUTION AND ADVISORY ALERTS . . . . . . . . . . . . . 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-26 2.16 OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 2.16.1 FUEL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 2.16.2 BATTERY CHARGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 2.16.3 EMERGENCY SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 2.16.4 DOOR LOCKING DEVICE . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 Operating Limitations DA 42 NG AFM Page 2 - 2 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.16.5 ELECTRONIC EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . 2-33 2.16.6 GARMIN G1000 AVIONICS SYSTEM . . . . . . . . . . . . . . . 2-34 2.16.7 AUTOPILOT LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . 2-38 2.16.8 SMOKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-40 2.16.9 GROUND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . 2-40 2.16.10 USE OF THE SUN VISORS . . . . . . . . . . . . . . . . . . . . . . 2-40 DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 3 2.1 INTRODUCTION Chapter 2 of this Airplane Flight Manual provides operating limitations, instrument markings 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. Operating Limitations DA 42 NG AFM Page 2 - 4 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.2 AIRSPEED Airspeed KIAS Remarks vO Operating maneuvering speed above 1800 kg (3968 lb) 122 KIAS Do not make full or abrupt control surface movement above this speed. above 1700 kg (3748 lb) to 1800 kg (3968 lb) 119 KIAS up to 1700 kg (3748 lb) 112 KIAS v FE Max. flaps extended speed LDG 113 KIAS Do not exceed these speeds with the given flap setting. APP 133 KIAS v LO Max. landing gear operating speed Extension v LOE 188 KIAS Do not operate the landing gear above this speed. Retraction v LOR 152 KIAS v LE Max. landing gear extended speed 188 KIAS Do not exceed this speed with the landing gear extended. vMCA Minimum control speed airborne 76 KIAS With one engine inoperative, keep airspeed above this limit. vNO Max. structural cruising speed 151 KIAS Do not exceed this speed except in smooth air, and then only with caution. vNE Never exceed speed in smooth air 188 KIAS Do not exceed this speed in any operation. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 5 2.3 AIRSPEED INDICATOR MARKINGS Marking KIAS Significance White arc 62 - 113 KIAS Operating range with flaps fully extended. Green arc 69 - 151 KIAS Normal operating range. Yellow arc 151 - 188 KIAS ‘Caution’ range - “Only in smooth air”. Blue radial 85 KIAS Best rate of climb speed, single engine. Red radial 76 KIAS Minimum control speed, single engine. Red radial 188 KIAS Maximum speed for all operations - v NE. Operating Limitations DA 42 NG AFM Page 2 - 6 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.4 POWER-PLANT LIMITATIONS a) Number of engines : 2 b) Engine manufacturer : Austro Engine c) Engine designation : E4-B d) RPM limitations (shown as propeller RPM) Maximum take-off (rpm) : 2300 RPM max. 5 min. Maximum continuous (rpm) : 2100 RPM Maximum overspeed : 2500 RPM max. 20 sec e) Engine power Max. take-off power : 100% (123.5 kW) max. 5 min. Max. continuous power : 92% (114 kW) f) Oil pressure (absolute) Minimum < 1500 RPM : 1.5 bar Minimum >= 1500 RPM : 2.5 bar Maximum : 6.5 bar Normal range : 2.5 bar - 6 bar DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 7 g) Oil quantity Minimum : 5.0 l Maximum : 7.0 l Maximum oil consumption : 0.1 liters/hr h) Oil temperature Minimum : - 30 °C Maximum : 140 °C Normal range : 50 °C - 125 °C i) Gearbox temperature Minimum : - 30 °C Minimum (full load) : 35 °C Maximum : 120 °C NOTE A cautionary (yellow) gearbox temperature range is not imposed by the engine manufacturer. However, there is a delay between power changes and gearbox temperature. Therefore, a cautionary range has been added to the G1000 gearbox temperature instrument solely to make the pilot attentive to the gearbox temperature approaching the maximum allowable limit. There is no specific time limit associated with operating in the cautionary gearbox temperature range. Operating Limitations DA 42 NG AFM Page 2 - 8 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E j) Coolant temperature Minimum (at start-up) : - 30 °C Minimum (full load) : 60 °C Maximum : 105 °C k) Fuel temperature Minimum : -25 °C Maximum : 60 °C l) Fuel pressure Minimum : 4 bar Maximum : 7 bar NOTE The fuel pressure is not indicated on the G1000; on the system monitor a fuel pressure warning will illuminate if the pressure is below limit. m)Voltage Minimum : 24.1 V Maximum : 32.0 V n) Amperage Maximum : 70 A DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 9 o) Propeller manufacturer : mt-Propeller p) Propeller designation : MTV-6-R-C-F / CF 187-129 q) Propeller diameter : 187 cm r) Prop. pitch angle (@ 0.75 R) : 12° ± 0.2° (low pitch) 15° ± 1° (start lock position) 81° ± 1° (feathered position) s) Governor : mt-Propeller P-877-16 electrical governor with feather position t) Oil specification : SHELL HELIX ULTRA 5W30 SHELL HELIX ULTRA 5W40 u) Gearbox oil (propeller gearbox) : SHELL SPIRAX GSX 75W-80 v) Coolant : Distilled water / cooler protection (BASF Glysantin Protect Plus / G48) 1/1. The freezing point of the coolant is - 38°C. CAUTION If the coolant or gearbox oil level is low the reason must be determined and the problem must be corrected by authorized personnel. w) Maximum restart altitude : 18,000 ft pressure altitude for immediate restarts 10,000 ft pressure altitude for restarts within two minutes Operating Limitations DA 42 NG AFM Page 2 - 10 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E x) Restart airspeed (starter) : max. 100 KIAS or airspeed for a stationary propeller, whichever is lower Restart airspeed (windmilling) : 125 KIAS to 145 KIAS y) No intentional shutdown below 5,000 and above 10,000 ft pressure altitude. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 11 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the tables below. Indi- cation Red arc/bar = lower prohibited range Yellow arc/bar = caution range Green arc/bar = normal operating range Yellow arc/bar = caution range Red arc/bar = upper prohibited range RPM -- -- up to 2100 RPM 2100 to 2300 RPM above 2300 RPM Oil pressure below 1.5 bar 1.5 to 2.5 bar 2.5 to 6.0 bar 6.0 to 6.5 bar above 6.5 bar Oil temp. below -30°C -30° to 50°C 50° to 125°C 125° to 140°C above 140°C Coolant temp. below -30°C -30° to 60°C 60° to 95°C 95° to 105°C above 105°C Gearbox temp. below -30°C -30° to 35°C 35° to 115°C 115° to 120°C above 120°C Load -- -- up to 92% 92 - 100% -- Fuel temp. below -25°C -25° to 5°C 5° to 55°C 55° to 60°C above 60°C Ammeter -- -- up to 60A 60 to 70A above 70A Volt- meter below 24.1V 24.1 to 25V 25 to 30V 30 to 32V above 32V Fuel qty. below 1 US gal -- 1 to 25 US gal -- -- Operating Limitations DA 42 NG AFM Page 2 - 12 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.6 WARNING, CAUTION AND ADVISORY ALERTS 2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000 NOTE The alerts described in the following are displayed on the Garmin G1000. Section 7.10 includes a detailed description of the alerts. The following tables show the color and significance of the warning, caution and advisory alerts lights on the G1000. Color and Significance of 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 / <1.5 bar). L/R FUEL TEMP Left / Right fuel temperature is in the upper red range (too high / >60 °C) L/R GBOX TEMP Left / Right engine gearbox temperature is in the upper red range (too high / >120 °C). L/R FUEL PRESS Left / Right engine fuel pressure is low. DA 42 NG AFM Operating Limitations Warning alerts (red) Meaning / Cause Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 13 L/R ALTN AMPS Left / Right engine alternator output is in the upper red range (too high / >70 amps). L/R ENG FIRE Left / Right engine fire detected. L/R STARTER Left / Right engine starter is engaged. DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed and locked. POSN ERROR G1000 will no longer provide GPS based navigational 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 display system is not receiving valid heading input from the AHRS. WARN RAIM position warning. The nav deviation bar is removed. Operating Limitations DA 42 NG AFM Page 2 - 14 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E Color and Significance of the Caution Alerts on the G1000 Caution alerts (amber) Meaning / Cause L/R ECU A FAIL A fault has occurred in the left/right engine ECU A (one reset of minor faults is possible) or ECU A is being tested during FADEC-test procedure during the 'Before Take-Off Check'. L/R ECU B FAIL A fault has occurred in the left/right engine ECU B (one reset of minor faults is possible) or ECU B is being tested during FADEC-test 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 engine bus voltage is too low (< 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 heat is OFF. STICK LIMIT Control stick limiting system (variable elevator stop) has failed. INTEG RAIM not available RAIM (Receiver Autonomous Integrity Monitor) is not available. AHRS ALIGN: Keep Wings Level The AHRS (Attitude and Heading Reference System) is aligning. DA 42 NG AFM Operating Limitations Caution alerts (amber) Meaning / Cause Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 15 L/R AUX FUEL E Left / Right auxiliary fuel tank empty (if installed). CHECK GEAR Landing gear is not down and locked. DEICE LVL LO De-icing fluid level is low (if installed). DEIC PRES HI De-icing pressure is high (if installed). DEIC PRES LO De-icing pressure is low (if installed). Color and Significance of the Advisory Alerts on the G1000 Advisory alerts (white) Meaning / Cause L/R GLOW ON Left / Right engine glow plug active. L/R AUXPUMP ON Fuel transfer from auxiliary to main tank is in progress (if installed). PFD FAN FAIL Cooling fan for the PFD is inoperative. MFD FAN FAIL Cooling fan for the MFD is inoperative. GIA FAN FAIL Cooling fan for the GIAs is inoperative. 2.6.2 OTHER WARNING ALERTS Warning Alerts on the Instrument Panel Warning alert (red) Meaning / Cause GEAR UNSAFE WARNING LIGHT Illuminates if the landing gear is neither in the final up nor in the down & locked position. Operating Limitations DA 42 NG AFM Page 2 - 16 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E Audible Warning Alerts Audible warning alert Meaning / Cause GEAR RETRACTED CHIME TONE (repeating) Resounds if the landing gear is retracted while the flaps move into position LDG or when the power lever is placed in a position below 25%. 2.7 MASS (WEIGHT) Value Mass (Weight) Minimum flight mass 1510 kg 3329 lb Maximum take-off mass 1900 kg 4189 lb Maximum zero fuel mass 1765 kg 3891 lb Maximum landing mass (see NOTE below) 1805 kg 3979 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. load, cabin baggage compartment and baggage extension together 45 kg 100 lb WARNING Exceeding the mass limits will lead to overstressing of the airplane as well as to degradation of flight characteristics and flight performance. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 17 NOTE In some countries the beginning of a flight is defined by starting the powerplant. In those countries a ramp mass of maximal MTOM + 8 kg (MTOM + 18 lb) is approved. At the time of lift-off the maximum permitted take-off mass must not be exceeded. NOTE A landing with a mass between 1805 kg (3979 lb) and 1900 kg (4189 lb) is admissible. It constitutes an abnormal operating procedure. A "Hard Landing Check" is only required after a hard landing, regardless of the actual landing mass. Operating Limitations DA 42 NG AFM Page 2 - 18 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.8 CENTER OF GRAVITY 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 plane is vertical. The datum plane is located 2.196 meters (86.46 in) forward of the most forward point of the root rib on the stub wing (refer to 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: 2.357 m (92.80 in) aft of datum plane at 1510 kg (3329 lb) 2.418 m (95.20 in) aft of datum plane at max. take-off mass (see Section 2.7) linear variation in between Most rearward flight CG: 2.460 m (96.85 in) aft of datum plane at 1510 kg (3329 lb) 2.480 m (97.64 in) aft of datum plane at 1700 kg (3748 lb) 2.480 m (97.64 in) aft of datum plane at max. take-off mass (see Section 2.7) linear variation in between Refer to Section 6.4.4 for a graphical illustration of the CG limitations. WARNING Exceeding the center of gravity limitations reduces the controllability and stability of the airplane. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 19 2.9 APPROVED MANEUVERS The airplane is certified in the Normal Category in accordance with JAR-23. Approved Maneuvers 1) all normal flight maneuvers; 2) stalling (with the exception of dynamic stalling); and 3) Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which an angle of bank of not 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 permitted. CAUTION Intentional negative g- maneuvers are not permitted. Operating Limitations DA 42 NG AFM Page 2 - 20 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.10 MANEUVERING LOAD FACTORS NOTE The tables below show structural limitations. The load factor limits for the engine must also be observed. Refer to the corresponding Operation Manual for the engine. at vO at vNE with flaps in APP or LDG position Positive 3.8 3.8 2.0 Negative -1.52 -1.52 WARNING Exceeding the maximum structural load factors will lead to overstressing of the airplane. CAUTION Intentional negative g- maneuvers are not permitted. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 21 2.11 OPERATING ALTITUDE The maximum operating altitude is 18,000 ft (5,486 m) pressure altitude. 2.12 FLIGHT CREW Minimum crew : 1 (one person) Maximum number of occupants : 4 (four persons) 2.13 KINDS OF OPERATION Provided that national operational requirements are met, the following kinds of operation are approved: • daytime flights according to Visual Flight Rules (VFR) • with 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 Flights into known or forecast thunderstorms are prohibited. Minimum Operational Equipment (Serviceable) The following table lists the minimum serviceable equipment required by JAR-23. Additional minimum equipment for the intended operation may be required by national operating rules and also depends on the route to be flown. Operating Limitations DA 42 NG AFM Page 2 - 22 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E NOTE Many of the items of minimum equipment listed in the following table are integrated in the G1000. for daytime VFR flights in addition for night VFR flights in addition for IFR flights Flight & navigation instruments * airspeed indicator (on G1000 PFD or backup) * altimeter (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 * VOR receiver * transponder (XPDR), mode A and mode C * GPS receiver (part of G1000) * second airspeed indicator (both, on G1000 PFD and backup) * second altimeter (both, on G1000 PFD and backup) * second attitude gyro (both, on G1000 PFD and backup) * second VHF radio (COM) * VOR-LOC-GP receiver * second GPS receiver (part of G1000) DA 42 NG AFM Operating Limitations for daytime VFR flights in addition for night VFR flights in addition for IFR flights Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 23 Engine instruments * 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 * fuel flow (2x) * fuel px warning * ammeter * voltmeter Lighting * position lights * strobe lights (anti collision lights) * landing light * instrument lighting * flood light * flashlight Operating Limitations DA 42 NG AFM for daytime VFR flights in addition for night VFR flights in addition for IFR flights Page 2 - 24 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E Other operational minimum equipment * 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. Engine Systems and Equipment All engine systems and equipment must be functional prior to airplane take-off. Any engine system or equipment failure must be corrected before next flight. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 25 2.14 FUEL Approved fuel grades : JET A (ASTM D 1655), JET A-1 (ASTM D 1655). NOTE A minimum cetane number of 37 determined acc. to EN ISO 5165/ASTM D613 is recommended. NOTE Use only uncontaminated fuel from reliable sources. Main Tanks Auxiliary Tanks (if installed) Total US gal liters US gal liters US gal liters 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 Operating Limitations DA 42 NG AFM Page 2 - 26 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.15 LIMITATION PLACARDS All limitation placards are shown below. A list of all placards is included in the Airplane Maintenance Manual (Doc. No. 7.02.15), Chapter 11. The following limitation placards are in the forward view of the pilot: Limitations for GFC 700 Autopilot System: Autopilot / Yaw Damper DISC during take-off and landing. Do not use AP during single engine operation. Maximum speed for autopilot operation is 180 KIAS. Minimum speed for autopilot operation is 90 KIAS. Minimum Altitude for Autopilot Operation: Cruise, Climb, Descent and Maneuvering: 800 feet AGL Approach : 200 feet AGL Departure : 200 feet AGL This airplane may only be operated in accordance with the Airplane Flight Manual in the "Normal" category in non-icing conditions. Provided that national operational requirements are met and the appropriate equipment is installed and operational, this airplane is approved for the following kinds of operation: day VFR, night VFR and IFR. All aerobatic maneuvers including spinning are prohibited. For further operational limitations refer to the Airplane Flight Manual. Operating maneuvering speed: vO = 122 KIAS (above 1800 kg / 3968 lb) v O = 119 KIAS (above 1700 kg / 3748 lb to 1800 kg / 3968 lb) v O = 112 KIAS (up to 1700 kg / 3748 lb ) DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 27 GPS NOT APPROVED FOR WAAS OPERATIONS LANDING GEAR vLE / vLOE = 188 KIAS vLOR = 152 KIAS EMERGENCY Gear Extension Max. 152 KIAS max. usable fuel: 2 x 25 US gal max. difference LH/RH tank: 5 US gal max. usable fuel main tank: 2 x 25 US gal auxiliary tank: 2 x 13 US gal max. difference LH/RH main tank: 5 US gal On the Emergency Landing Gear Extension Lever: On the Instrument Panel: Standard Tank: Auxiliary Tank (if installed): Operating Limitations DA 42 NG AFM Page 2 - 28 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E Crossfeed with fuel pump ON in emergencies only WARNING APPROVED FUEL JET-A1 or see Airplane Flight Manual Next to the Fuel Selector: (a) Next to Each of the Two Fuel Filler Necks; (b) In Addition Next to Each of the Two Auxiliary Fuel Filler Necks (if installed): DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 29 OIL SHELL HELIX ULTRA 5W30 or see Airplane Flight Manual In Each Cowling, on the Door for the Oil Filler Neck: Next to the Flap Selector Switch: UP Flaps APP 133 KIAS LDG 113 KIAS Operating Limitations DA 42 NG AFM Page 2 - 30 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E In the Cabin, on the Left Fuselage Sidewall: Next to the Cabin Baggage Compartment: DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 31 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 ______ Operating Limitations DA 42 NG AFM Page 2 - 32 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.16 OTHER LIMITATIONS 2.16.1 FUEL TEMPERATURE From -25 °C to 60 °C (from -13 °F to 140 °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 permitted if the subsequent flight is intended to be a Night VFR or IFR flight. In this case the airplane battery must first be charged. 2.16.3 EMERGENCY SWITCH IFR flights are not permitted when the seal on the emergency switch is broken. 2.16.4 DOOR LOCKING DEVICE The canopy and the passenger door must not be blocked by the key lock during operation of the airplane. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 33 2.16.5 ELECTRONIC EQUIPMENT The use and switching 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 drives, CD and minidisc players in the replay mode, cassette players and video cameras is permitted. All this equipment however should be switched off for take-off and landing. Operating Limitations DA 42 NG AFM Page 2 - 34 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.16.6 GARMIN G1000 AVIONICS SYSTEM 1. The Garmin G1000 Cockpit Reference Guide, P/N 190-00963-00, appropriate revision must be immediately available to the flight crew. 2. The G1000 must utilize the software Garmin 010-00670-01 approved software in accordance with the mandatory service bulletin DAI MSB 42NG-003, latest version. Software Part Number Approved Version Function System for approved version see DAI MSB 42NG-003 latest version 010-00670-01 Manifest 006-B0093-( ) GPS1, GPS2 006-B0172-( ) GTX1-GIA1, GTX1-GIA2 006-B0190-( ) GIA1, GIA2 006-B0193-( ) GEA1-GIA1; GEA1-GIA2 006-B0203-( ) GMA1-GIA1, GMA1-GAI2 006-B0223-( ) GRS1-GIA1, GRS1-GIA2 006-B0224-( ) GMU1 006-B0319-( ) PFD1, MFD1 006-B0328-( ) 006-B0329-( ) 006-C0048-( ) GMU1 FPGA 006-C0049-( ) GRS1 FPGA 006-C0055-( ) GDC1 FPGA 006-D0159-( ) GRS1 MV DB 006-D0202-( ) 006-B0261-( ) GDC1-GIA1 006-B0081-( ) COM1, COM2 006-B0083-( ) GS1, GS2 006-B0082-( ) NAV1, NAV2 DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 35 NOTE The database version is displayed on the MFD power-up page immediately after system power-up and must be acknowledged. The remaining system software versions can be verified on the AUX group sub-page 5, "AUX-SYSTEM STATUS". 3. IFR enroute, oceanic and terminal navigation predicated upon 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. 4. 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 database must incorporate the current update cycle. NOTE Not all published approaches are in the FMS database. The pilot must ensure that the planned approach is in the database. (a) Instrument approaches utilizing the GPS receiver must be conducted in the approach mode and Receiver Autonomous Integrity Monitoring (RAIM) must be available at the Final Approach Fix. (b) Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay with the G1000 GPS receiver is not authorized. (c) Use of the G1000 VOR/ILS receiver to fly approaches not approved for GPS require VOR/ILS navigation data to be present on the display. Operating Limitations DA 42 NG AFM Page 2 - 36 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E (d) When an alternate airport is required by the applicable operating rules, it must be served by an approach based on other than GPS or Loran-C navigation, the airplane must have the operational equipment capable of using that navigation aid, and the required navigation aid must be operational. (e) VNAV information may be utilized for advisory information only. Use of VNAV information for Instrument Approach Procedures does not guarantee step-down fix altitude protection, or arrival at approach minimums in normal position to land. (f) RNAV (GPS) approaches must be conducted utilizing the GPS sensor. (g) RNP RNAV operations are not authorized, except as noted in Chapter 1 of this AFM. 5. If not previously defined, the following default settings must be made in the "SYSTEM SETUP" menu of the G1000 prior to operation (refer to Pilot's Guide for procedure if necessary): (a) DIS, SPD : nm, kt (sets navigation units to "nautical miles" and "knots") (b) ALT, VS : ft, fpm (sets altitude units to "feet" and "feet per minute") (c) POSITION : deg-min (sets navigation grid units to decimal minutes) NOTE Navigation Information is referenced to WGS-84 reference system, and should only be used where the Aeronautical Information Publication (including electronic data and aeronautical charts) conforms to WGS-84 or equivalent. DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 37 6. When AHRS is required to meet the items listed in the Minimum operational equipment (serviceable) table in Section 2.13 of this AFM, operation is prohibited in the following areas: (a) north of 70° N and south of 70° S latitudes, (b) north of 65° N between 75° W and 120° W longitude, and (c) south of 55° S between 120° E and 165° E longitude. When day VFR operations are conducted in the above areas, the MFD must be in a non-heading up orientation. 7. The fuel quantity, fuel required, and fuel remaining functions on the Fuel Page (displayed when pushing the FUEL button as shown in Section 7.13) of the FMS are supplemental information only and must be verified by the flight crew. 8. The GPS is not approved for WAAS operations: (a) The G1000 integrated avionics system is NOT approved for GPS WAAS operations including GPS WAAS approach procedures such as "LPV", "LNAV/VNAV", and "LNAV +V". (b) SBAS (WAAS & MSAS) functionality must be disabled on the G 1000 GPS Status page (refer to the G1000 Pilot´s Guide for procedure). 9. The availability of SafeTaxi® , ChartView, or FliteCharts® in electronic form on the G1000 is for information purposes only, it is still mandatory to carry another source of charts on-board the airplane. Operating Limitations DA 42 NG AFM Page 2 - 38 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 2.16.7 AUTOPILOT LIMITATIONS 1. It is the responsibility of the pilot in command to monitor the autopilot when it is engaged. The pilot should be prepared to immediately disconnect the autopilot and to take prompt corrective action in the event of unexpected or unusual autopilot behavior. 2. The autopilot and yaw damper must be disconnected (using the DISC button) during take-off, landing and single engine operation. 3. Following an autopilot or electric trim malfunction, reengaging the autopilot or manual electric trim, or resetting the AUTOPILOT circuit breaker is prohibited until the cause of the malfunction has been determined and corrected. 4. The Garmin G1000 Cockpit Reference Guide for the Diamond DA 42 NG, P/N 010-00963-00 approved revision must be immediately available to the flight crew. 5. ILS approaches using the GFC700 / flight director are limited to Category I approaches only. 6. Autopilot maximum airspeed: 180 KIAS Autopilot minimum airspeed: 90 KIAS 7. Altitude select captures below 1200 feet AGL are prohibited. 8. The autopilot must be disengaged: - below 200 ft AGL during approach, - below 200 ft AGL during departure, - below 800 ft AGL for all other phases of flight, - during single engine operation. 9. Overriding the autopilot to change pitch or roll attitude is prohibited. (Disengage or press CWS while maneuvering.) DA 42 NG AFM Operating Limitations Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 EASA approved Page 2 - 39 10. The GFC 700 components must utilize the following or later approved software versions: Sub-System Software Version GDU v9.03 GDC 74 v3.02 GEA 7X v2.07 GPS v3.03 GIA 6X v5.65 GIA Audio v2.03 GMAX347 v4.01 GMU44 v2.01 GRS 77 v2.11 GTX 33X v5.01 GDL 69 v3.20.00 GSA 8X v2.20 GFC 700 v2.00 The system software versions can be verified on the AUX group sub-page 5, "AUX - SYSTEM STATUS". Operating Limitations DA 42 NG AFM Page 2 - 40 Rev. 1 18-Feb-2009 EASA approved Doc. No. 7.01.15-E 11. The GFC 700 AFCS pre-flight test must be successfully completed prior to use of the autopilot, flight director, yaw damper or manual electric trim. 12. A pilot with the seat belt fastened must occupy the left pilot's seat during all operations. 13. The yaw damper is an integral part of the autopilot system and must not be used separately. 2.16.8 SMOKING Smoking in the airplane is not permitted. 2.16.9 GROUND OPERATION Take-off and landing has been demonstrated on hard paved surfaces (asphalt, concrete, etc.) and grass runways. 2.16.10 USE OF THE SUN VISORS The sun visors (if installed, OÄM 42-101) may only be used during cruise. During all other phases of flight the sun visors must be locked in the fully upward position. DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 1 CHAPTER 3 EMERGENCY PROCEDURES Page 3.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4 3.1.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES . . . . . . . . . . . . . . 3-5 3.1.3 SELECTING EMERGENCY FREQUENCY . . . . . . . . . . . . . . 3-5 3.2 AIRPLANE-RELATED G1000 WARNINGS . . . . . . . . . . . . . . . . . . . 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 FUEL PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12 3.2.8 L/R ALTN AMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12 3.2.9 L/R ENG FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13 3.2.10 L/R STARTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-14 3.2.11 DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-14 3.3 AIRPLANE-RELATED G1000 CAUTIONS . . . . . . . . . . . . . . . . . . . 3-15 3.3.1 L/R ALTN FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15 3.4 G1000 SYSTEM WARNINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.1 RED X . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.2 POSN ERROR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.3 ATTITUDE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.4 AIRSPEED FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.5 ALTITUDE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-17 Emergency Procedures DA 42 NG AFM Page 3 - 2 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.4.6 VERT SPEED FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-17 3.4.7 HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-17 3.4.8 WARN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-17 3.5 G1000 FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-18 3.5.1 NAVIGATION INFORMATION FAILURE . . . . . . . . . . . . . . 3-18 3.5.2 PFD OR MFD DISPLAY FAILURE . . . . . . . . . . . . . . . . . . . 3-18 3.5.3 AHRS FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-19 3.5.4 AIR DATA COMPUTER (ADC) FAILURE . . . . . . . . . . . . . . 3-20 3.5.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-20 3.5.6 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-21 3.6 ABNORMAL ENGINE BEHAVIOUR . . . . . . . . . . . . . . . . . . . . . . . 3-22 3.7 ONE ENGINE INOPERATIVE PROCEDURES . . . . . . . . . . . . . . . 3-23 3.7.1 DETECTING THE INOPERATIVE ENGINE . . . . . . . . . . . . 3-24 3.7.2 ENGINE TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . 3-25 3.7.3 ENGINE SECURING (FEATHERING) PROCEDURE . . . . 3-27 3.7.4 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-28 3.7.5 ENGINE FAILURE DURING TAKE-OFF . . . . . . . . . . . . . . . 3-32 3.7.6 ENGINE FAILURES IN FLIGHT . . . . . . . . . . . . . . . . . . . . . 3-35 3.7.7 LANDING WITH ONE ENGINE INOPERATIVE . . . . . . . . . 3-37 3.7.8 GO-AROUND / BALKED LANDING WITH ONE ENGINE INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-40 3.7.9 FLIGHT WITH ONE ENGINE INOPERATIVE . . . . . . . . . . . 3-42 3.8 LANDING GEAR SYSTEM FAILURES . . . . . . . . . . . . . . . . . . . . . 3-44 3.8.1 LANDING GEAR UNSAFE WARNING . . . . . . . . . . . . . . . . 3-44 3.8.2 MANUAL EXTENSION OF THE LANDING GEAR . . . . . . . 3-46 3.8.3 LANDING WITH GEAR UP . . . . . . . . . . . . . . . . . . . . . . . . . 3-48 3.8.4 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-49 DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 3 3.8.5 LANDING WITH DEFECTIVE BRAKES . . . . . . . . . . . . . . . . 3-50 3.9 FAILURES IN THE ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . . 3-51 3.9.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . . 3-51 3.9.2 HIGH CURRENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-52 3.9.3 STARTER MALFUNCTION . . . . . . . . . . . . . . . . . . . . . . . . . 3-52 3.10 SMOKE AND FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-53 3.10.1 ENGINE FIRE ON GROUND . . . . . . . . . . . . . . . . . . . . . . . 3-53 3.10.2 ENGINE FIRE DURING TAKE-OFF . . . . . . . . . . . . . . . . . . 3-54 3.10.3 ENGINE FIRE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . 3-55 3.10.4 ELECTRICAL FIRE ON GROUND . . . . . . . . . . . . . . . . . . . 3-56 3.10.5 ELECTRICAL FIRE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . 3-57 3.11 OTHER EMERGENCIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-58 3.11.1 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-58 3.11.2 UNLOCKED DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-59 3.11.3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-60 3.11.4 UNINTENTIONAL FLIGHT INTO ICING . . . . . . . . . . . . . . . 3-63 3.11.5 FUEL SUPPLY FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . 3-64 3.11.6 RECOVERY FROM AN UNINTENTIONAL SPIN . . . . . . . . 3-65 3.11.7 EMERGENCY DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . 3-67 3.11.8 EMERGENCY EXIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-67 3.11.9 AUTOPILOT OR ELECTRIC TRIM MALFUNCTION / FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-68 NOTE Procedures for uncritical system faults are given in Chapter 4B - ABNORMAL OPERATING PROCEDURES. Emergency Procedures DA 42 NG AFM Page 3 - 4 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.1 INTRODUCTION 3.1.1 GENERAL This chapter contains checklists as well as the description of recommended procedures to be followed in the event of an emergency. Engine failure or other airplane-related emergencies are most unlikely to occur if the prescribed procedures for pre-flight checks and airplane maintenance are followed. If, nonetheless, an emergency does arise, the guidelines given in this chapter should be followed and applied in order to clear the problem. As it is impossible to foresee all kinds of emergencies and cover 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 airplane"). Prior to the flight the pilot must consider the suitability of the terrain for an emergency landing for each phase of the flight. For a safe flight the pilot must constantly keep a safe minimum flight altitude. Solutions for various adverse scenarios should be thought over in advance. This should prevent a situation where the pilot is faced with an emergency he cannot handle calmly and with determination. DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 5 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event One engine inoperative minimum control speed (air) v MCA 76 KIAS One engine inoperative speed for best rate of climb vYSE 85 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. Emergency Procedures DA 42 NG AFM Page 3 - 6 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.2 AIRPLANE-RELATED G1000 WARNINGS 3.2.1 WARNINGS / GENERAL "Warning" means that the non-observation of the corresponding procedure leads to an immediate or important degradation in flight safety. The warning text is displayed in red color. A warning chime tone of 1.5 seconds duration will sound and repeat without delay until the alarm is acknowledged 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 more as required. - Increase airspeed by 10 KIAS or more as required. - If the coolant temperature does not reach the green range within 60 seconds, reduce power on affected engine as far as possible and increase airspeed. CONTINUED DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 7 During cruise: - Reduce power on affected engine. - Increase airspeed. - Check coolant temperature in green range. CAUTION If high coolant temperature is indicated and the L/R COOL LVL caution message is not displayed, it can be assumed that there is no technical defect in the cooling system and that the above mentioned procedure can decrease the temperature(s). This might not be the case if the coolant temperature does not return to the green range. In this case perform a precautionary landing on the nearest suitable airfield. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST L/R COOL LVL caution message displayed: - Reduce power on affected engine. - Expect loss of coolant. WARNING A further increase in coolant temperature must be expected. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 8 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.2.3 L/R OIL TEMP L/R OIL TEMP Left / Right engine oil temperature is in the upper red range (too high / above 140 °C). Oil temperatures above the limit value of 140 °C can lead to a total loss of power due to engine failure. - Check oil pressure. If the oil pressure is outside of the green range (lower limit): - Reduce power on affected engine. - Expect loss of engine oil. WARNING A further increase in oil temperature must be expected. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. If the oil pressure is within the green range: - Reduce power on affected engine. - Increase airspeed. CONTINUED DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 9 CAUTION If high oil temperature is announced and the oil pressure indication is within the green range, it can be assumed that there is no technical defect in the engine oil system and that the above mentioned procedure can decrease the temperature(s). This might not be the case if the oil temperature does not return to the green range. In this case perform a precautionary landing on the nearest suitable airfield. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST 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 1.5 bar). Oil pressures below the limit value of 1.5 bar can lead to a total loss of power due to engine failure. - Reduce power on affected engine. - Expect loss of oil. WARNING Land at the nearest suitable airfield. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 10 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.2.5 L/R GBOX TEMP L/R GBOX TEMP Left / Right engine gearbox temperature is in the upper red range (too high / above 120 °C). Gearbox temperatures above the limit value of 120 °C can lead to a total loss of power due to engine failure. - Reduce power on affected 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 the nearest suitable airfield. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 11 3.2.6 L/R FUEL TEMP L/R FUEL TEMP Left / Right fuel temperature is in the upper red range (too high / above 60 °C). Fuel temperatures above the limit value of 60 °C can lead to a noticeable reduction of the high pressure pump efficiency. - Reduce power on affected engine. - Increase airspeed. CAUTION 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 main tank is low. If the auxiliary tank is installed the fuel temperature can be decreased by transferring fuel from the auxiliary to the main tank. END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 12 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.2.7 L/R FUEL PRESS L/R FUEL PRESS Left / Right engine fuel pressure is low. 1. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . check 2. FUEL SELECTOR of affected engine . . . . . . check ON 3. Fuel pump of affected engine . . . . . . . . . . . . ON if L/R FUEL PRESS warning remains: 4. Fuel pump of affected engine . . . . . . . . . . . . OFF 5. FUEL SELECTOR of affected engine . . . . . . CROSSFEED if L/R FUEL PRESS warning still remains: WARNING Imminent engine failure must be expected. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURE IN FLIGHT. END OF CHECKLIST 3.2.8 L/R ALTN AMPS L/R ALTN AMPS Left / Right engine alternator output is in the upper red range (too high / above 70 amps). Proceed according to: 3.9.2 - HIGH CURRENT DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 13 3.2.9 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: 3.10.1 - ENGINE FIRE ON GROUND 3.10.2 - ENGINE FIRE DURING TAKE-OFF 3.10.3 - ENGINE FIRE IN FLIGHT Emergency Procedures DA 42 NG AFM Page 3 - 14 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.2.10 L/R STARTER L/R STARTER Left / Right engine starter is engaged. Proceed according to: 3.9.3 - STARTER MALFUNCTION 3.2.11 DOOR OPEN DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed and locked. Proceed according to: 3.11.2 - UNLOCKED DOORS DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 15 3.3 AIRPLANE-RELATED G1000 CAUTIONS 3.3.1 L/R ALTN FAIL L/R ALTN FAIL Left / Right engine alternator has failed. (a) One Alternator Failed Proceed according to: 4B.4.6 - L/R ALTN FAIL (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 Release 5. Stall / Pitot heat . . . . . . . . . . . . . . . . . . . . . . OFF 6. All lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 16 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.4 G1000 SYSTEM WARNINGS 3.4.1 RED X A red X through any display field, such as COM frequencies, NAV frequencies, or engine data, indicates that display field is not receiving valid data. 3.4.2 POSN ERROR POSN ERROR The system will flag and no longer provide GPS based navigational guidance. Revert to the G1000 VOR/ILS receivers or an alternate means of navigation other than the G1000 GPS receivers. 3.4.3 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. 3.4.4 AIRSPEED FAIL AIRSPEED FAIL The display system is not receiving airspeed input from the air data computer; accompanied by a red X through the airspeed display. Revert to the standby airspeed indicator. DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 17 3.4.5 ALTITUDE FAIL ALTITUDE FAIL The display system is not receiving altitude input from the air data computer; accompanied by a red X through the altimeter display. Revert to the standby altimeter. 3.4.6 VERT SPEED FAIL 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. 3.4.7 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 compass. 3.4.8 WARN WARN RAIM position warning - nav deviation bar removed. 1. CDI softkey . . . . . . . . . . . . . . . . . . . . . . . . . . switch to VOR/LOC Emergency Procedures DA 42 NG AFM Page 3 - 18 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.5 G1000 FAILURES 3.5.1 NAVIGATION INFORMATION FAILURE If Garmin G1000 GPS navigation information is not available or invalid, utilize remaining operational navigation equipment as required. 3.5.2 PFD OR MFD DISPLAY FAILURE 1. DISPLAY BACKUP button on audio panel . . PUSH Automatic Entry of Display Revisionary 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 problem causing the automatic entry of reversionary mode is resolved. A maximum of one attempt to return to normal mode is approved using the following procedure. DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 19 (b) DISPLAY BACKUP button on audio panel ...... PUSH (button will be IN) - If the system returns to normal mode, leave the DISPLAY BACKUP button IN and continue. - lf the system remains in reversionary mode, or abnormal display behavior such as display flashing occurs, then return the DISPLAY BACKUP button to the OUT position. 3.5.3 AHRS FAILURE NOTE A failure of the Attitude and Heading Reference System (AHRS) is indicated by a removal of the sky/ground presentation and a red X and a yellow "AHRS FAILURE" shown on the PFD. The digital heading presentation will be replaced with a yellow "HDG" and the compass rose digits will be removed. The course pointer will indicate straight up and course may be set using the digital window. 1. Use standby attitude indicator, emergency compass and navigation map 2. Course . . . . . . . . . . . . . . . . . . . . . . . . . . . . . set using digital window Emergency Procedures DA 42 NG AFM Page 3 - 20 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.5.4 AIR DATA COMPUTER (ADC) 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. 3.5.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS NOTE Loss of an engine parameter is indicated by a red X through the data field. Erroneous information may be identified by indications which do not agree with other system information. Erroneous indications may be determined by comparing a display with other displays and other system information. 1. Set power based on power lever position, engine noise and speed. 2. Monitor other indications to determine the health of the engine. 3. Use known power settings and Section 5.3.2 of the AFM for approximate fuel flow values. 4. Use other system information, such as annunciator messages, GPS fuel quantity and flow to safely complete the flight. DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 21 3.5.6 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS NOTE Loss of an annunciator may be indicated when engine or fuel displays show an abnormal or emergency situation and the annunciator is not present. An erroneous annunciator may be identified when an annunciator appears which does not agree with other 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 determined that the condition does not exist, treat the situation as if the condition exists. Refer to Chapter 3 - EMERGENCY PROCEDURES or Chapter 4B - ABNORMAL OPERATING PROCEDURES. Emergency Procedures DA 42 NG AFM Page 3 - 22 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.6 ABNORMAL ENGINE BEHAVIOUR 1. Full power . . . . . . . . . . . . . . . . . . . . . . . . . . . apply If the abnormal engine behavior sustains, refer to 3.7 - ONE ENGINE INOPERATIVE PROCEDURES. END OF CHECKLIST DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 23 3.7 ONE ENGINE INOPERATIVE PROCEDURES WARNING In certain combinations of airplane weight, configuration, ambient conditions, speed and pilot skill, negative climb performance may result. Refer to Chapter 5 - PERFORM- ANCE for one engine inoperative performance data. In any event the sudden application of power during one- engine inoperative operation makes the control of the airplane more difficult. CAUTION Below 10,000 ft pressure altitude, do not attempt an in-flight engine restart if the engine has been shutdown for more than two minutes. Above 10,000 ft pressure altitude only immediate restart is possible. Emergency Procedures DA 42 NG AFM Page 3 - 24 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.7.1 DETECTING 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 (with coordinated controls). To handle 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 that, once directional control is re-established, the pilot can feel the control force on the foot pushing the rudder-pedal on the side of the operative engine, while the foot on the side of the failed engine feels no force. Further, the engine instruments can help to analyze the situation. DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 25 3.7.2 ENGINE TROUBLESHOOTING WARNING Control over the flight attitude has priority over attempts to solve the current problem ("first fly the airplane"). NOTE With respect to handling and performance, the left-hand engine (pilots view) is considered the "critical" engine. NOTE If the loss of power was due to unintentional setting of the POWER lever, you may adjust the friction lock and continue your flight. Depending on the situation the following attempts can be made to restore normal engine operation: 1. Circuit breakers . . . . . . . . . . . . . . . . . . . . . . check / reset if necessary If normal engine operation is restored continue flight and land as soon as possible. Otherwise: 2. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . swap between ECU A and B If either ECU A or B setting restores normal engine operation then maintain that ECU setting and land as soon as possible. CONTINUED Emergency Procedures DA 42 NG AFM Page 3 - 26 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E Otherwise: 3. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . . switch back to AUTO to retain ECU redundancy If normal engine operation is restored continue flight and land as soon as possible. Otherwise: 4. FUEL SELECTOR of affected engine . . . . . . CROSSFEED CAUTION Switching on the fuel pump of the affected engine in combination with CROSSFEED may cause damage to the high-pressure pump. If normal engine operation is restored continue flight. Remain within maximum allowable lateral imbalance. Otherwise: 5. FUEL SELECTOR of affected engine . . . . . . ON / CROSSFEED as required 6. ALTERNATE AIR . . . . . . . . . . . . . . . . . . . . . OPEN 7. POWER lever of affected engine . . . . . . . . . apply power as required If normal engine operation is restored continue flight and land as soon as practicable. If normal engine operation could not be restored by following the procedures in this section prepare for 3.7.3 - ENGINE SECURING (FEATHERING) PROCEDURE and land as soon as possible. END OF CHECKLIST DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 27 3.7.3 ENGINE SECURING (FEATHERING) PROCEDURE Shut down and feathering of the affected engine: 1. Affected engine . . . . . . . . . . . . . . . . . . . . . . . identify & verify 2. ENGINE MASTER affected engine . . . . . . . . OFF CAUTION Do not shut down an engine with the FUEL SELECTOR valve. Otherwise the high pressure fuel pump can be damaged. Securing the feathered engine: 3. Alternator affected engine . . . . . . . . . . . . . . . OFF 4. Fuel pump . . . . . . . . . . . . . . . . . . . . . . . . . . . check OFF 5. FUEL SELECTOR affected engine . . . . . . . . OFF NOTE The remaining fuel in the tank of the secured engine can be used for the remaining engine to extend range and maintain lateral balance by setting its FUEL SELECTOR in 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 Emergency Procedures DA 42 NG AFM Page 3 - 28 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E 3.7.4 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT If the reason for the shutdown has been ascertained and there is no indication of malfunction or engine fire a restart may be attempted. Restarting the Engine with the Starter Maximum restart altitude: 18,000 ft pressure altitude for immediate restart. 10,000 ft pressure altitude for restarts within two minutes. CAUTION Do not attempt an in-flight engine restart if the engine has been shutdown for more than two minutes. NOTE If the engine is allowed to cool down for more than two minutes a successful restart may not be possible. Maximum restart airspeed: max. 100 KIAS or airspeed for a stationary propeller, whichever is lower. CAUTION Do not engage the starter when the propeller is windmilling. CONTINUED DA 42 NG AFM Emergency Procedures Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 3 - 29 NOTE At airspeeds below 100 KIAS it is possible that the propeller may windmill intermittently. Therefore, care should be taken to ensure that the propeller is stationary when engaging the starter. 1. POWER lever of affected engine . . . . . . . . . IDLE 2. FUEL SELECTOR of affected engine . . . . . . check ON 3. Alternate air . . . . . . . . . . . . . . . . . . . . . . . . . as required 4. ALTERNATOR of affected engine . . . . . . . . ON 5. ENGINE MASTER of affected engine . . . . . . ON, propeller un-feathers 6. STARTER of affected engine . . . . . . . . . . . . engage when propeller is stationary CAUTION After the engine has started, the POWER lever should be set to a moderate power setting until engine temperatures have reached the green range. END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 30 Rev. 1 18-Feb-2009 Doc. No. 7.01.15-E Restarting the Engine by Wind