DA 40 NG AFM

appr. 2-19 01-Jul-2014 ' appr. 2-20 01-Jul-2014 ' appr. 2-21 01-Jul-2014 ' appr. 2-22 01-Jul-2014 ' appr. 2-23 01-Jul-2014 ' appr. 2-24 01-Jul-2014 ' appr. 2-25 01-Jul-2014 ' appr. 2-26 01-Jul-2014 ' appr. 2-27 01-Jul-2014 ' Ch. Page Date 2 appr. 2-28 01-Jul-2014 ' appr. 2-29 01-Jul-2014 ' appr. 2-30 01-Jul-2014 ' appr. 2-31 01-Jul-2014 ' appr. 2-32 01-Jul-2014 ' appr. 2-33 01-Jul-2014 ' appr. 2-34 01-Jul-2014 ' appr. 2-35 01-Jul-2014 ' appr. 2-36 01-Jul-2014 ' DA 40 NG AFM Introduction Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 0 - 7 Ch. 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Page Date 3 3-29 01-Jul-2014 ' 3-30 01-Jul-2014 ' 3-31 01-Jul-2014 ' 3-32 01-Jul-2014 ' 3-33 01-Jul-2014 ' 3-34 01-Jul-2014 ' 3-35 01-Jul-2014 ' 3-36 01-Jul-2014 ' 3-37 01-Jul-2014 ' 3-38 01-Jul-2014 ' 3-39 01-Jul-2014 ' 3-40 01-Jul-2014 ' 3-41 01-Jul-2014 ' 3-42 01-Jul-2014 ' 3-43 01-Jul-2014 ' 3-44 01-Jul-2014 ' 3-45 01-Jul-2014 ' 3-46 01-Jul-2014 ' 3-47 01-Jul-2014 ' 3-48 01-Jul-2014 ' Introduction DA 40 NG AFM Page 0 - 8 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E Ch. 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Page Date 4B 4B-1 01-Jul-2014 ' 4B-2 01-Jul-2014 ' 4B-3 01-Jul-2014 ' 4B-4 01-Jul-2014 ' 4B-5 01-Jul-2014 ' 4B-6 01-Jul-2014 ' 4B-7 01-Jul-2014 ' 4B-8 01-Jul-2014 ' 4B-9 01-Jul-2014 ' 4B-10 01-Jul-2014 ' 4B-11 01-Jul-2014 ' 4B-12 01-Jul-2014 ' 4B-13 01-Jul-2014 ' 4B-14 01-Jul-2014 ' 4B-15 01-Jul-2014 ' 4B-16 01-Jul-2014 ' 4B-17 01-Jul-2014 ' 4B-18 01-Jul-2014 ' 4B-19 01-Jul-2014 ' 4B-20 01-Jul-2014 ' 4B-21 01-Jul-2014 ' 4B-22 01-Jul-2014 ' 4B-23 01-Jul-2014 ' 4B-24 01-Jul-2014 ' 4B-25 01-Jul-2014 ' 4B-26 01-Jul-2014 ' 4B-27 01-Jul-2014 ' Ch. Page Date 4B 4B-28 01-Jul-2014 ' 4B-29 01-Jul-2014 ' 4B-30 01-Jul-2014 ' Introduction DA 40 NG AFM Page 0 - 10 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E Ch. 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Page Date 6 6-1 01-Jul-2014 ' 6-2 01-Jul-2014 ' 6-3 01-Jul-2014 ' 6-4 01-Jul-2014 ' 6-5 01-Jul-2014 ' 6-6 01-Jul-2014 ' 6-7 01-Jul-2014 ' 6-8 01-Jul-2014 ' 6-9 01-Jul-2014 ' 6-10 01-Jul-2014 ' 6-11 01-Jul-2014 ' 6-12 01-Jul-2014 ' 6-13 01-Jul-2014 ' 6-14 01-Jul-2014 ' 6-15 01-Jul-2014 ' 6-16 01-Jul-2014 ' 6-17 01-Jul-2014 ' 6-18 01-Jul-2014 ' 6-19 01-Jul-2014 ' 6-20 01-Jul-2014 ' 6-21 01-Jul-2014 ' 6-22 01-Jul-2014 ' 6-23 01-Jul-2014 ' 6-24 01-Jul-2014 ' 6-25 01-Jul-2014 ' 6-26 01-Jul-2014 ' 6-27 01-Jul-2014 ' 6-28 01-Jul-2014 ' Introduction DA 40 NG AFM Page 0 - 12 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E Ch. 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Page Date 7 7-28 01-Jul-2014 ' 7-29 01-Jul-2014 ' 7-30 01-Jul-2014 ' 7-31 01-Jul-2014 ' 7-32 01-Jul-2014 ' 7-33 01-Jul-2014 ' 7-34 01-Jul-2014 ' 7-35 01-Jul-2014 ' 7-36 01-Jul-2014 ' 7-37 01-Jul-2014 ' 7-38 01-Jul-2014 ' 7-39 01-Jul-2014 ' 7-40 01-Jul-2014 ' 7-41 01-Jul-2014 ' 7-42 01-Jul-2014 ' 7-43 01-Jul-2014 ' 7-44 01-Jul-2014 ' 7-45 01-Jul-2014 ' 7-46 01-Jul-2014 ' 7-47 01-Jul-2014 ' 7-48 01-Jul-2014 ' DA 40 NG AFM Introduction Page 0 - 13 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E Ch. Page Date 8 8-1 01-Jul-2014 ' 8-2 01-Jul-2014 ' 8-3 01-Jul-2014 ' 8-4 01-Jul-2014 ' 8-5 01-Jul-2014 ' 8-6 01-Jul-2014 ' 8-7 01-Jul-2014 ' 8-8 01-Jul-2014 ' 8-9 01-Jul-2014 ' 8-10 01-Jul-2014 ' 8-11 01-Jul-2014 ' 8-12 01-Jul-2014 ' 8-13 01-Jul-2014 ' 8-14 01-Jul-2014 ' Ch. Page Date 9 9-1 01-Jul-2014 ' 9-2 01-Jul-2014 ' ' 9-3 01-Jul-2014 ' ' 9-4 01-Jul-2014 ' Introduction DA 40 NG AFM Page 0 - 14 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 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 DA 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-15 1.6.1 CONVERSION FACTORS . . . . . . . . . . . . . . . . . . . . . . . . . 1-15 1.6.2 CONVERSION CHART LITER / US GALLON . . . . . . . . . . 1-17 1.7 THREE-VIEW DRAWING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-18 1.8 SOURCE DOCUMENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-19 1.8.1 ENGINE AND ENGINE INSTRUMENTS . . . . . . . . . . . . . . . 1-19 1.8.2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-20 General DA 40 NG AFM Page 1 - 2 Rev. 3 01-Jul-2014 Doc. # 6.01.15-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. This Airplane Flight Manual is valid for all serial numbers. 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 Exhaust Pipe with Muffler MÄM 40-434 or OÄM 40- 310 9 yes 9 no Garmin G1000 Avionics System MÄM 40-447 9 yes 9 no Long Range Tanks OÄM 40-130 9 yes 9 no Baggage Tray (Extended Baggage Compartment) OÄM 40-164 9 yes 9 no Baggage Tube Basic Design 9 yes 9 no Winter Baffle Fresh Air Inlet OÄM 40-183 9 yes 9 no Nose Landing Gear Tie-down OÄM 40-200 9 yes 9 no Front Seats with Adjustable % Backrest % OÄM 40-252 9 yes 9 no Maximum Landing Mass 1280 kg % MÄM 40-574 % 9 yes % 9 no % DA 40 NG AFM General Modification Source Installed Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 1 - 3 Shorter NLG Damper % MÄM 40-631 % 9 yes % 9 no % Maximum Take-Off Mass 1310 kg % MÄM 40-662 % 9 yes % 9 no % Conventional Cockpit DA 40 NG Club OÄM 40-321 9 yes 9 no Emergency Axe % OÄM 40-326 % 9 yes % 9 no % Retrofit with Autopilot KAP 140 OÄM 40-329 9 yes 9 no Retrofit without Autopilot GFC 700 OÄM 40-330 9 yes 9 no Short Baggage Extension OÄM 40-331 9 yes 9 no DA 40 NG without Autopilot GFC 700 OÄM 40-333 9 yes 9 no Landing Gear with Large Tyres and % 1280 kg Maximum Landing Mass % OÄM 40-334 % 9 yes % 9 no % Diesel Operation % OÄM 40-370 % 9 yes % 9 no % This Airplane Flight Manual must be kept on board the airplane at all times. Its designated place is the side bag of the forward left seat. CAUTION The DA 40 NG is a single 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, flights during the night, on top, under instrument meteorological conditions (IMC), or above terrain which is unsuitable for a landing, constitute a risk. It is therefore highly recommended to select flight times and flight routes such that this risk is minimized. General DA 40 NG AFM Page 1 - 4 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 1.2 CERTIFICATION BASIS This airplane has been type certified in accordance with the procedures established by EASA. The certification basis is JAR-23, published on 11-Mar-1994 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 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 1 - 5 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall Dimensions Span : 11.63 m 38 ft 2 in Length : 8.06 m 26 ft 5 in Height : 1.97 m 6 ft 6 in Wing Airfoil : Wortmann FX 63-137/20 - W4 Wing area : 13.244 m² 142.6 sq.ft. Mean aerodynamic chord (MAC) : 1.171 m 3 ft 10 in Aspect ratio : 10.223 Dihedral : 5° Leading edge sweep : 1° Aileron Area (total, left + right) : 0.654 m² 7.0 sq.ft. Wing Flaps Area (total, left + right) : 1.56 m² 16.8 sq.ft. General DA 40 NG AFM Page 1 - 6 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E Horizontal Tail Area : 2.34 m 2 25.2 sq.ft. Elevator area : 0.665 m 2 7.2 sq.ft. Angle of incidence : -3.0° relative to longitudinal axis of airplane Vertical Tail Area : 1.60 m² 17.2 sq.ft. Rudder area : 0.47 m² 5.1 sq.ft. Landing Gear Track : 2.97 m 9 ft 9 in Wheelbase : 1.68 m 5 ft 6 in Wheelbase (if MÄM 40-574 is installed) % : 1.85 m 6 ft 8 in % Nose wheel : 5.00-5; 6 PR, TT, 120 mph Main wheel : 15x6.0-6; 6 PR, TT, 160 mph DA 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 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 NE: Never Exceed Speed in smooth air. This speed must not be exceeded in any operation. vNO: Maximum Structural Cruising Speed. This speed may be exceeded only in smooth air, and then only with caution. vR : Rotation Speed. Speed at which the nose wheel lifts off. % v50 : Speed at 50 ft (15 m)above the take-off surface. % General DA 40 NG AFM Page 1 - 8 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E vS Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration. vS0 : Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the landing configuration. vx: Best Angle-of-Climb Speed. vy: Best Rate-of-Climb Speed. (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 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. 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 1,013.25 hPa (29.92 inHg). DA 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 1 - 9 Pressure Altitude: Altitude above MSL, indicated by a barometric altimeter which is set to 1,013.25 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 maneuverability for take-off and landing has been demonstrated during type certification. MET: Weather, weather advice. NAV: Navigation, route planning. General DA 40 NG AFM Page 1 - 10 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E (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 consumables and the maximum quantity of oil. Maximum Take-off Mass: The maximum permissible mass for take-off. Maximum Landing Mass: The highest mass for landing conditions at the maximum descent velocity. This condition was used in the strength calculations to determine the landing gear loads during a particularly hard landing. Maximum Zero Fuel Mass: The highest permissible mass with empty fuel tanks. DA 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 1 - 11 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 CT: Coolant Temperature. EECU: Electronic Engine Control Unit. GT: Gearbox Temperature. LOAD: Engine output power in percent of take-off power. MED: Main Engine Display. OP: Oil Pressure (oil pressure in the lubrication system of the engine). OT: Oil Temperature (oil temperature in the lubrication system of the engine). RPM: Revolutions per minute (rotational speed of the propeller). SED: Secondary Engine Display. FT: Fuel Temperature. General DA 40 NG AFM Page 1 - 12 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E (f) Designation of the Circuit Breakers on the Instrument Panel ADC: Air Data Computer. ADF: Automatic Direction Finder. AHRS: Attitude and Heading Reference System. ANNUN: Annunciator Panel. AV/CDU FAN: Avionic-, CDU-Cooling Fans. AV. BUS: Avionic Bus. AUDIO: Audio Panel / Marker Beacon Receiver. AUTOPILOT: Autopilot System. COM: COM Radio. COM1: COM Radio No. 1. COM2: COM Radio No. 2. DG: Directional Gyro. DME: Distance Measuring Equipment. EECU A: ECU A. EECU B: ECU B. ENG INST: Engine Instruments. ESS TIE: Bus Interconnection. FAN/OAT: Fan / Outside Air Temperature. FLAPS: Flap System. FLOOD: Flood Light. FUEL PUMP A: ECU A Fuel Pump. FUEL PUMP B: ECU B Fuel Pump. GPS: Global Positioning System. GPS/NAV1: Global Positioning System and NAV Receiver No. 1. GPS/NAV2: Global Positioning System and NAV Receiver No. 2. HORIZON: Artificial Horizon (Attitude Gyro). DA 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 1 - 13 INST.1: Engine Instrument. INST. LT: Instrument Lights. LANDING: Landing Light. MAIN TIE: Bus Interconnection. MASTER CONTROL: Master Control (Avionics Relay). MFD: Multi Function Display. NAV: NAV Receiver. PFD: Primary Flight Display. PITOT: Pitot Heating System. POSITION: Position Lights. PWR: Power. START: Starter. STROBE: Strobe Lights (= Anti Collision Lights). T & B: Turn and Bank Indicator. TAS: Traffic Advisory System. TAXI/MAP: Taxi Light / Map Lights. WX500: Stormscope. XFR PUMP: Fuel Transfer Pump. XPDR Transponder. (g) Equipment ELT: Emergency Locator Transmitter. (h) Design Change Advisories MÄM: Mandatory Design Change Advisory. OÄM: Optional Design Change Advisory. General DA 40 NG AFM Page 1 - 14 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E (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. GFRP: Glass Fiber Reinforced Plastic. GIA: Garmin Integrated Avionics. JAR: Joint Aviation Requirements. DA 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 1 - 15 1.6 UNITS OF MEASUREMENT 1.6.1 CONVERSION FACTORS Dimension SI-Units US Units Conversion Length [mm] millimeter [m] meter [km] kilometer [in] inch [ft] feet [NM] nautical mile [mm] / 25.4 = [in] [m] / 0.3048 = [ft] [km] / 1.852 = [NM] Volume [l] liter [ml] milliliter % [US gal] US gallon [qts] US quarts [oz] ounce % [l] / 3.7854 = [US gal] [l] / 0.9464 = [qts] [ml] x 0.033814 = [oz] % Speed [km/h] kilometer per hour [m/s] meter per second [kt] knot [mph] mile per hour [fpm] feet per minute [km/h] / 1.852 = [kt] [km/h] / 1.609 = [mph] [m/s] x 196.85 = [fpm] Speed of rotation [RPM] revolutions per minute -- Mass [kg] kilogram [lb] pound [kg] x 2.2046 = [lb] Force, weight [N] newton [lbf] pound force [N] x 0.2248 = [lbf] Pressure [hPa] hecto- pascal [mbar] millibar [bar] bar [inHg] inches of mercury [psi] pound per square inch [hPa] = [mbar] [hPa] / 33.86 = [inHg] [bar] x 14.504 = [psi] Temperature [°C] degree Celsius [°F] degree Fahrenheit [°C]x1.8 + 32 = [°F] ([°F] - 32)/1.8 = [°C] General DA 40 NG AFM Dimension SI-Units US Units Conversion Page 1 - 16 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E Intensity of electric current [A] ampère -- Electric charge (battery capacity) [Ah] ampère-hour -- Electric potential [V] volt -- Time [sec] second -- DA 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 1 - 17 1.6.2 CONVERSION CHART LITER / US GALLON Liter US Gallon US Gallon Liter 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 General DA 40 NG AFM Page 1 - 18 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 8060 mm (26 ft 5 in) 11630 mm (38 ft 2 in) 1.7 THREE-VIEW DRAWING DA 40 NG AFM General Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 1 - 19 1.8 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. 1.8.1 ENGINE AND ENGINE INSTRUMENTS 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 AE300, E4.01.01 Maintenance Manual AE300, E4.08.04 Installation Manual AE300, E4.02.01 General DA 40 NG AFM Page 1 - 20 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 1.8.2 PROPELLER Address: mt-propeller Airport Straubing Wallmühle D-94348 ATTING GERMANY Phone: +49-9429-9409-0 E-mail: sales@mt-propeller.com Internet: www.mt-propeller.de Documents: E-124, Operation and Installation Manual Hydraulically controlled variable pitch propeller MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25 DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 1 CHAPTER 2 OPERATING LIMITATIONS Page 2.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 2.2 AIRSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 2.3 AIRSPEED INDICATOR MARKINGS . . . . . . . . . . . . . . . . . . . . . . . 2-4 2.4 POWER-PLANT LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 2.5 ENGINE INSTRUMENT MARKINGS . . . . . . . . . . . . . . . . . . . . . . 2-11 2.6 WARNING, CAUTION AND STATUS LIGHTS . . . . . . . . . . . . . . . 2-12 2.7 MASS (WEIGHT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 2.8 CENTER OF GRAVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 2.9 APPROVED MANEUVERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19 2.10 MANEUVERING LOAD FACTORS . . . . . . . . . . . . . . . . . . . . . . . . 2-20 2.11 OPERATING ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 2.12 FLIGHT CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 2.13 KINDS OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 2.14 FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-26 2.15 LIMITATION PLACARDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-29 2.16 OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35 2.16.1 TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35 2.16.2 BATTERY CHARGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35 2.16.3 EMERGENCY SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35 2.16.4 DOOR LOCKING DEVICE . . . . . . . . . . . . . . . . . . . . . . . . 2-36 2.16.5 ELECTRONIC EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . 2-36 2.16.6 SMOKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36 2.16.7 USE OF THE SUN VISORS . . . . . . . . . . . . . . . . . . . . . . . 2-36 Operating Limitations DA 40 NG AFM Page 2 - 2 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E 2.1 INTRODUCTION Chapter 2 of this Airplane Flight Manual includes operating limitations, instrument markings, and placards necessary for the safe operation of the airplane, its power-plant, standard systems and standard equipment. The limitations included in this Chapter are approved. WARNING Operation of the airplane outside of the approved operating limitations is not permissible. DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 3 2.2 AIRSPEED Airspeed KIAS Remarks vO Operating maneuvering speed up to 1080 kg (2381 lb) 101 KIAS Do not make full or abrupt control surface movement above this speed. above 1080 kg (2381 lb) to 1180 kg (2601 lb) 108 KIAS above 1180 kg (2601 lb) 113 KIAS v FE Max. flaps extended speed LDG 98 KIAS Do not exceed these speeds with the given flap setting. T/O 110 KIAS v NO = vC Max. structural cruising speed 130 KIAS Do not exceed this speed except in smooth air, and then only with caution. vNE Never exceed speed in smooth air 172 KIAS Do not exceed this speed in any operation. Operating Limitations DA 40 NG AFM Page 2 - 4 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E 2.3 AIRSPEED INDICATOR MARKINGS Marking IAS Significance White arc ' 60 KIAS - 98 KIAS ' Operating range with flaps fully extended. Green arc ' 66 KIAS - 130 KIAS ' Normal operating range. Yellow arc 130 KIAS - 172 KIAS 'Caution' range - “Only in smooth air”. Red line 172 KIAS Maximum speed for all operations - vNE. DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 5 2.4 POWER-PLANT LIMITATIONS a) Engine manufacturer : Austro Engine b) Engine designation : E4-A c) RPM limitations (shown as propeller RPM) Maximum take-off (RPM) : 2300 RPM max. 5 min Max. continuous power (RPM) : 2100 RPM Max. overspeed : 2500 RPM max. 20 sec d) Engine power Max. take-off power : 100% (123.5 kW) max. 5 min Max. continuous power : 92% (114 kW) e) Oil pressure Minimum at idle : 0.9 bar Minimum at max. continuous conditions : 2.5 bar Maximum : 6.5 bar Normal range : 2.5 bar - 6.0 bar f) Oil quantity Minimum : 5.0 l Maximum : 7.0 l Maximum oil consumption : 0.1 liter/hour g) Oil temperature Operating Limitations DA 40 NG AFM Page 2 - 6 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E Minimum : - 30 °C Maximum : 140 °C Normal range : 50 °C - 135 °C h) 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 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. i) Coolant temperature Minimum (at start-up) : - 30 °C Minimum (full load) : 60 °C Maximum : 105 °C j) Fuel temperature Minimum : - 25 °C Maximum : 60 °C DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 7 k) Fuel pressure (absolute pressure) Minimum : 4 bar NOTE The fuel pressure is not indicated; a fuel pressure warning will illuminate on the PFD (if G1000 is installed) or SED (if installed) if the pressure is below the limit. Maximum : 7 bar NOTE The fuel pressure is not indicated; the fuel pressure caution ECU A/B FAIL on the PFD (if G1000 is installed) or ECU A/B on the White Wire annunciator panel (if installed) will illuminate if the pressure is above the limit. l) Voltage Minimum : 24.1 V Maximum : 32.0 V m) Amperage Maximum : 70 A n) Propeller manufacturer : mt-Propeller o) Propeller designation : MTV-6-R/190-69 p) Propeller diameter : 190 cm (6 ft 3 in) q) Prop. pitch angle (@ 0.75 R) : Low Pitch 14.5E± 0.2E High Pitch 35E± 1.0E Operating Limitations DA 40 NG AFM Page 2 - 8 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E r) Governor : mt-Propeller P-853-16 electrical governor s) Oil specification : Approved Engine Oil Types ' SAE Grade ' SHELL HELIX ULTRA ' 5W-30 ' ADDINOL SUPER POWER MV 0537 ' 5W-30 ' BP Visco 5000 5W-30 ' 5W-30 ' REPSOL ELITE Common Rail 5W30 ' 5W-30 ' Gulf Formula GMX ' 5W-30 ' G-Energy F Synth 5W-30 ' 5W-30 ' QUARTZ 9000 ENERGY 5W-30 ' 5W-30 ' Gulf Formula GX ' 5W-30 ' AEROSHELL Oil Diesel Ultra ' 5W-30 ' CASTROL Edge 5W-30 A3 ' 5W-30 ' CASTROL Edge Professional A3 ' 5W-30 ' SHELL HELIX ULTRA ' 5W-40 ' LIQUI MOLY 5W-40 LEICHTLAUF HIGH TECH ' 5W-40 ' megol Motorenoel High Condition ' 5W-40 ' PETRONAS Syntium 3000 ' 5W-40 ' LUKOIL LUXE synthetic ' 5W-40 ' CASTROL Edge Professional A3 ' 5W-40 ' CASTROL Magnatec Professional A3 ' 5W-40 ' VALVOLINE SynPower HST ' 5W-40 ' VALVOLINE SynPower ' 5W-40 ' GULF Formula GX ' 5W-40 ' Castrol SLX Professional Longtec 0W-40 ' 0W-40 ' DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 9 CASTROL Edge 0W-40 A3/B4 ' 0W-40 ' CASTROL Edge Professional A3 ' 0W-40 ' SHELL HELIX Ultra ' 0W-40 ' ' CAUTION ' Only engine oils conforming to MB 229.5 specification are ' approved by Austro Engine GmbH to be used for operation. ' ' NOTE ' It is not recommended to mix different SAE grades. ' t) Gearbox oil (propeller gearbox) : SHELL SPIRAX GSX 75W-80 SHELL SPIRAX S6 GXME 75W-80 ' u) Coolant : Distilled water / Cooler protection (BASF Glysantin Protect Plus / G48): - Mixture ratio 50% / 50% for freezing point ' -38°C (-36°F). ' - Mixture ratio 40% / 60% (MÄM 40-638 is ' carried out) freezing point -53 °C (-63°F) ' CAUTION If the coolant or gearbox oil level is low the reason must be determined and the problem must be corrected by authorized personnel. Operating Limitations DA 40 NG AFM Page 2 - 10 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E v) Maximum restart altitude : 16,400 ft pressure altitude for immediate restarts 10,000 ft pressure altitude for restarts within 2 minutes DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 11 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the table 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 0.9 bar 0.9 to 2.5 bar 2.5 to 6.0 bar 6.0 to 6.5 bar above 6.5 bar Oil temp. below -30°C -30° to 50°C 50° to 135°C 135° to140°C 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 -20°C -20° 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 14 US gal -- -- Operating Limitations DA 40 NG AFM Page 2 - 12 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E 2.6 WARNING, CAUTION AND STATUS LIGHTS The following tables show the color and significance of the warning, caution and advisory alert lights. There are two variants: G1000 annunciation or SED, MED and ‘White Wire’ annunciator panel. Color and Significance of the Warning Lights (Red) Warning Alerts (Red) Meaning / Cause G1000 installed SED, MED, White Wire installed WARNING WARNING One of the warnings listed below is being indicated. ENG TEMP - Engine coolant temperature is in the upper red range (too high / > 105 °C). OIL TEMP - Engine oil temperature is in the upper red range (too high / > 140 °C). OIL PRES - Engine oil pressure is in the lower red range (too low / < 0.9 bar). L/R FUEL TEMP - Fuel temperature is in the upper red range (too high / > 60 °C). GBOX TEMP - Engine gearbox temperature is in the upper red range (too high / > 120 °C). FUEL PRESS FUELPRESS Engine fuel pressure is low. ALTN AMPS - Engine alternator output is in the upper red range (too high / > 70 A). ALTN FAIL ALTERNATOR Engine alternator has failed. STARTER START Engine starter is engaged. DA 40 NG AFM Operating Limitations Warning Alerts (Red) Meaning / Cause G1000 installed SED, MED, White Wire installed Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 13 DOOR OPEN DOORS Canopy and/or rear door are/is not closed and locked. ATTITUDE FAIL - 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. AIRSPEED FAIL - Display system is not receiving airspeed input from the air data computer; accompanied by a red X through the airspeed display. ALTITUDE FAIL - Display system is not receiving altitude input from the air data computer; accompanied by a red X through the altimeter display. VERT SPEED FAIL - Display system is not receiving vertical speed input from the air data computer; accompanied by a red X through the vertical speed display. HDG - Display system is not receiving valid heading input from the AHRS; accompanied by a red X through the digital heading display. 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. Operating Limitations DA 40 NG AFM Page 2 - 14 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E Color and Significance of the Caution Lights (Amber) Caution Alerts (Amber) Meaning / Cause G1000 installed SED, MED, White Wire installed CAUTION CAUTION One of the cautions below is being indicated. ECU A FAIL ECU A A fault has occurred in the engine ECU A or ECU A is being tested during FADEC-test procedure during the 'Before Take-Off Check'. ECU B FAIL ECU B A fault has occurred in the engine ECU B or ECU B is being tested during FADEC-test procedure during the 'Before Take-Off Check'. FUEL LOW LOW FUEL Left fuel quantity is low. VOLTS LOW LOW VOLTS Engine bus voltage is too low (< 25 V). COOL LVL WATERLEV Engine coolant level is low. PITOT FAIL PITOT Pitot heat has failed. PITOT HT OFF - Pitot heat is OFF. LOI - GPS integrity is insufficient for the current phase of flight. AHRS ALIGN: Keep Wings Level - The AHRS (Attitude and Heading Reference System) is aligning. - ENGINE Engine limit exceeded. DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 15 Color and Significance of the Status Lights (White) Advisory Alerts (White) Meaning / Cause G1000 installed SED, MED, White Wire installed GLOW ON GLOW Engine glow plug active. FUEL XFER FUEL TRANS Fuel transfer from auxiliary to main tank is in progress. PFD FAN 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. Operating Limitations DA 40 NG AFM Page 2 - 16 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E 2.7 MASS (WEIGHT) Value Mass (Weight) Maximum take-off mass 1280 kg 2822 lb Maximum take-off mass (if MÄM 40-662 is installed) ' 1310 kg ' 2888 lb ' Maximum landing mass if MÄM 40-574 is installed ' 1216 kg 1280 kg ' 2681 lb 2822 lb ' Minimum flight mass 940 kg 2072 lb Maximum zero fuel mass if MÄM 40-574 is installed ' 1200 kg 1265 kg ' 2646 lb 2789 lb ' Standard: Max. load in baggage compartment (between rear seats and baggage frame) 30 kg 66 lb Max. load in baggage tube compartment (if installed) 5 kg 11 lb Max. load in short baggage extension (if OÄM 40-331 is installed) 15 kg 33 lb Extended baggage compartment (if OÄM 40-164 is installed): Max. load in cockpit baggage compartment (behind rear seats) 45 kg 100 lb Max. load in extended baggage compartment (behind cabin baggage compartment) 18 kg 40 lb Max. load in cockpit baggage compartment and extended baggage compartment 45 kg 100 lb WARNING Exceeding the mass limits will lead to an overstressing of the airplane as well as to a degradation of flight characteristics and flight performance. DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 17 NOTE In some countries the beginning of a flight is defined by starting the engine. In those countries a maximum ramp mass 4 kg (9 lb) above the maximum take-off mass is approved. At the time of lift-off the maximum permitted take-off mass must not be exceeded. NOTE The maximum zero fuel mass is the highest mass with empty fuel tanks. Operating Limitations DA 40 NG AFM Page 2 - 18 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-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 upper surface of a 600:31 wedge which is placed on top of the rear fuselage in front of the vertical stabilizer. When the upper surface of the wedge is aligned horizontally, the Datum Plane is vertical. The Datum Plane is located 2.194 meter (86.38 in) forward of the most forward point of the root rib on the stub wing. Center of Gravity Limitations The center of gravity (CG position) for flight conditions must be between the following limits: Most forward CG: 2.40 m (94.5 in) aft of DP from 940 kg to 1080 kg (2072 lb to 2381 lb) 2.46 m (96.9 in) aft of DP at 1280 kg (2822 lb) If MÄM 40-662 is installed: ' 2.469 m (97.2 in) aft of DP at 1310 kg (2888 lb) ' linear variation between these values Most rearward CG: 2.53 m (99.6 in) aft of DP from 940 kg (2072 lb) to 1310 kg (2888 lb) ' WARNING Exceeding the center of gravity limitations reduces the controllability and stability of the airplane. DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 19 2.9 APPROVED MANEUVERS The airplane is to be operated 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. CAUTION Intentional negative g-maneuvers are not permitted. Operating Limitations DA 40 NG AFM Page 2 - 20 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E 2.10 MANEUVERING LOAD FACTORS WARNING The table below shows structural limitations. Exceeding the maximum load factors will lead to an overstressing of the airplane. CAUTION Intentional negative g-maneuvers are not permitted. at vO at vNE with flaps in T/O or LDG position Positive 3.8 3.8 2.0 Negative -1.52 0 0 DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 21 2.11 OPERATING ALTITUDE The maximum operating altitude is 16,400 ft (5,000 m) pressure altitude. 2.12 FLIGHT CREW Minimum crew : 1 (one person) Maximum number of occupants : 4 (four persons) Operating Limitations DA 40 NG AFM Page 2 - 22 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E 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 unpaved surfaces Flights into known or forecast icing conditions are prohibited. Flights into known 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. NOTE Many of the items of minimum equipment listed in the following table are integrated in the G1000 (if installed). DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 23 For daytime VFR flights In addition for night VFR flights In addition for IFR flights Flight & naviga- tion instru- ments • Airspeed indicator • Altimeter • Magnetic compass • 1 headset, used by pilot in command • Vertical speed indicator (VSI) • Attitude gyro • Turn & bank indicator • Directional gyro • VHF radio (COM) • VOR receiver • Transponder (XPDR) • GPS receiver (part of G1000, if installed) • Second headset (if PM 1000 intercom is installed) • Second airspeed indicator (on PFD and backup, if G1000 is installed) • Second altimeter • Second attitude gyro (on PFD and backup, if G1000 is installed) • Second VHF radio (COM) • VOR-LOC-GP receiver • Second GPS receiver (part of G1000, if installed) Operating Limitations DA 40 NG AFM For daytime VFR flights In addition for night VFR flights In addition for IFR flights Page 2 - 24 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E Engine instru- ments • Fuel qty. • Oil press. • Oil temp. • Coolant temp. • Coolant level indicator • Gearbox temp. • Load • Prop. RPM • Fuel temp. left & right tank • Fuel flow • Fuel pressure warning • ECU A/B Caution ' • ENGINE Caution ' (if White Wire annunciator panel is installed) • Ammeter • Voltmeter DA 40 NG AFM Operating Limitations For daytime VFR flights In addition for night VFR flights In addition for IFR flights Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 25 Lighting • Position lights • Strobe lights (anti collision lights) • Landing light • Instrument lighting • Flood light • Flashlight Other opera- tional mini- mum equip- ment • Stall warning system • Alternate means for fuel quantity indication (see Section 7.9) • Safety belts for each occupied seat • Airplane Flight Manual • Pitot heating system • Alternate 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. Operating Limitations DA 40 NG AFM Page 2 - 26 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E 2.14 FUEL Approved fuel grades: JET A, JET A-1 (ASTM D 1655) ' TS-1(Russia, GOST 10227-86) ' TS-1 (Ukraine, GSTU 320.00149943.011-99) ' RT (Russia, GOST 10227-86) ' RT (Ukraine, GSTU 320.00149943.007-97) ' No. 3 Jet Fuel (China, GB 6537-2006) ' JP-8 (F34) (USA, MIL-DTL-83133G-2010) ' and blends of the above listed fuel grades. NOTE A minimum cetane number of 37 determined acc. to EN ISO 5165/ASTM D613 is recommended. NOTE Use only uncontaminated fuel from reliable sources. Any mixture of the different types of fuel additives is not permitted. ' OPERATION WITH ANTI-MICROBIAL LIFE FUEL ADDITIVES ' The application of the following additives is permitted: ' - KATHON FP 1.5 : max. 100 ppm ' - BIOBOR JF : max. 270 ppm for initial treatment ' max. 135 ppm for permanent use after initial treatment ' DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 27 CAUTION ' In case of an unknown or an over dosage of the fuel ' additives the fuel system must be purged until the dosage ' is within the permitted limits. ' NOTE ' The specified additives are qualified for the operation with ' the certified fuel grades. ' To clean the fuel system of the airplane a higher dosage ' of the specified additive is allowed under consideration of ' the instructions of the additive supplier. During cleaning ' the engine must not be operated. ' NOTE ' The instructions of the fuel additive supplier must be ' followed. ' OPERATION WITH ANTI-ICING FUEL ADDITIVES ' The application of the following additive is permitted: ' - PRIST Hi-Flash : max. 1500 ppm ' ' CAUTION ' The use of PRIST Hi-Flash fuel additive is only permitted ' with JET A, JET A-1 (ASTM D 1655) and JP-8 (F34). ' NOTE ' The instructions of the fuel additive supplier must be ' followed. ' Operating Limitations DA 40 NG AFM Page 2 - 28 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E Standard Tank Configuration: Total fuel quantity : 2 x 15.0 US gal (2 x 56.8 liter) Usable fuel : 2 x 14.0 US gal (2 x 53.0 liter) Long Range Tank (if installed) Configuration: Total fuel quantity : 2 x 20.5 US gal (2 x 77.6 liter) Usable fuel : 2 x 19.5 US gal (2 x 73.8 liter) Max. indicated fuel quantity : 14 US gal (53 liter) per tank Max. permissible difference between right and left tank : 9 US gal (approx. 34 liter) CAUTION If an indicator shows 14 US gal, then 19.5 US gal must be assumed for the calculation of the difference between right and left tank. DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 29 max. usable fuel: 2 x 19.5 US gal * Max. indicated fuel quantity: 2 x 14 US gal * Refer to AFM to use entire tank capacity * Max. difference LH/RH tank: 9 US gal 2.15 LIMITATION PLACARDS All limitation placards relevant for the base DA 40 NG airplane are shown below. A list of all placards is included in the Airplane Maintenance Manual (Doc. No. 6.02.15), Chapter 11. On the Instrument Panel: 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, IFR. ALL AEROBATIC MANEUVERS INCLUDING SPINNING ARE PROHIBITED. FOR FURTHER OPERATIONAL LIMITATIONS REFER TO THE AIRPLANE FLIGHT MANUAL. OPERATING MANEUVERING SPEED: VO = 113 KIAS (ABOVE 1180 KG / 2601 LB) VO = 108 KIAS (ABOVE 1080 KG / 2381 LB TO 1180 KG / 2601 LB) VO = 101 KIAS (UP TO 1080 KG / 2381 LB ) On the Instrument Panel, Next to the Fuel Quantity Indication: Long Range Tank (if installed): Operating Limitations DA 40 NG AFM Page 2 - 30 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E WARNING APPROVED FUEL JET-A1 or see Airplane Flight Manual Next to Each of the Two Fuel Filler Necks: Next to the Essential Bus Switch: Ess. Bus NOT for normal operation. See AFM. DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 31 OIL SHELL HELIX ULTRA 5W30 or see Airplane Flight Manual max. 98 KIAS max. 110 KIAS NORMAL EMERGENCY FUEL VALVE CAUTION: INTERMITTENT USE ONLY (SEE AFM) OFF In the Cowling, on the Door for the Oil Filler Neck: Next to the Flap Selector Switch: On the Fuel Valve: Operating Limitations DA 40 NG AFM Page 2 - 32 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E Max. 5 kg/ 11 lb Next to the Baggage Compartment: Baggage Tube Compartment: Baggage Tray (if OÄM 40-164 installed, extended baggage compartment): Max. 30 kg/ 66 lb DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 33 COCKPIT BAGGAGE COMPARTMENT MAX. 45 kg [100 lb] ARM: 3.89 m [153.1”] BAGGAGE EXTENSION MAX. 18 kg [40 lb] ARM: 4.54 m [178.7”] MAX. BAGGAGE TOTAL (COCKPIT BAGGAGE COMPARTMENT & EXTENSION): 45 kg [100 lb] CAUTION: OBSERVE WEIGHT AND BALANCE LIMITATIONS SEE AIRPLANE FLIGHT MANUAL CHAPTER 6 If Short Baggage Extension (OÄM 40-331) is carried out: Operating Limitations DA 40 NG AFM Page 2 - 34 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E EMERGENCY EXIT: The keylock must be unlocked during flight Remove at Outside Temperatures above 20 °C / 68 °F Alternate Static OPEN CLOSED If Alternate Static is open Emergency Window and Cockpit Vent must be closed On the Left Sidewall, Next to the Instrument Panel: Beside the Door Locking Device: On Fuel Cooler Inlet Baffle (if installed): On the Instrument Panel: ______ NO SMOKING ______ DA 40 NG AFM Operating Limitations Doc. # 6.01.15-E Rev. 3 01-Jul-2014 EASA approved Page 2 - 35 2.16 OTHER LIMITATIONS 2.16.1 TEMPERATURE The airplane may only be operated when its temperature prior to operation is not less than -40 °C (-40 °F). ' With the airplane cold soaked and its temperature below -20 °C (-4 °F) the use of an external pre-heater for the engine and pilot compartment prior to operation is mandatory. The airplane may only be operated with the fuel cooler inlet baffle installed when the outside air temperature at take-off does not exceed 20 EC (68 EF). If the outside air temperature at take-off is below -30°C (-22°F) the coolant radiator ' inlet baffle (OÄM 40-364) must be installed. The airplane may only be operated with ' the coolant radiator inlet baffle, if the outside air temperature at take-off does not ' exceed 0°C (32°F). ' With the airplane cold soaked and its temperature below -30°C (-22°F) the batterries ' must be pre-heated (OÄM 40-363) prior to operation. ' 2.16.2 BATTERY CHARGE Take-off for a Night VFR or IFR flight with an empty main battery is not permitted. The use of an external power supply for engine starting with an empty airplane main battery is not permitted if the subsequent flight is intended to be a Night VFR or an IFR flight. In this case the airplane main battery must be charged first. 2.16.3 EMERGENCY SWITCH IFR flights are not permitted when the seal on the emergency switch is broken. Operating Limitations DA 40 NG AFM Page 2 - 36 Rev. 3 01-Jul-2014 EASA approved Doc. # 6.01.15-E 2.16.4 DOOR LOCKING DEVICE The canopy and the passenger door must not be key locked during operation of the airplane. 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 telephones - Remote radio controls - Video screens employing CRTs - Minidisc recorders when in the record mode This list is not exhaustive. The use of laptop computers, including those with CD-ROM drives, CD and minidisc players in the replay mode, cassette players and video cameras is permitted. All this equipment however should be switched off for take-off and landing. 2.16.6 SMOKING Smoking in the airplane is not permitted. 2.16.7 USE OF THE SUN VISORS The sun visors (if installed, OÄM 40-327) may only be used during cruise. During all other phases of flight the sun visors must be locked in the fully upward position. DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 1 CHAPTER 3 EMERGENCY PROCEDURES Page 3.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3 3.1.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES . . . . . . . . . . . . . 3-4 3.2 INSTRUMENT INDICATIONS IN PROHIBITED (RED) RANGE . . . 3-5 3.2.1 ENGINE TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5 3.2.2 OIL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 3.2.3 OIL PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9 3.2.4 GEARBOX TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . 3-10 3.2.5 L/R FUEL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . 3-11 3.2.6 FUEL PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12 3.2.7 ALTERNATOR AMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13 3.2.8 ALTERNATOR FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-14 3.3 ENGINE PROBLEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15 3.3.1 ENGINE PROBLEMS ON GROUND . . . . . . . . . . . . . . . . . 3-15 3.3.2 ENGINE PROBLEMS DURING TAKE-OFF . . . . . . . . . . . . 3-16 3.3.3 ENGINE TROUBLESHOOTING IN FLIGHT . . . . . . . . . . . . 3-18 3.3.4 ENGINE FAILURE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . 3-21 3.3.5 RESTARTING THE ENGINE IN FLIGHT . . . . . . . . . . . . . . 3-22 3.3.6 DEFECTIVE RPM REGULATING SYSTEM . . . . . . . . . . . . 3-24 3.3.7 FUEL TRANSFER PUMP FAILURE . . . . . . . . . . . . . . . . . . 3-28 3.4 FAILURES IN THE ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . 3-30 3.4.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . 3-30 3.4.2 HIGH CURRENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-31 3.4.3 STARTER MALFUNCTION . . . . . . . . . . . . . . . . . . . . . . . . . 3-32 Emergency Procedures DA 40 NG AFM Page 3 - 2 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.5 SMOKE AND FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-33 3.5.1 SMOKE AND FIRE ON GROUND . . . . . . . . . . . . . . . . . . . 3-33 3.5.2 SMOKE AND FIRE DURING TAKE-OFF . . . . . . . . . . . . . . 3-35 3.5.3 SMOKE AND FIRE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . 3-38 3.6 GLIDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-40 3.7 EMERGENCY LANDINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-41 3.7.1 EMERGENCY LANDING WITH ENGINE OFF . . . . . . . . . . 3-41 3.7.2 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-43 3.7.3 LANDING WITH DEFECTIVE BRAKES . . . . . . . . . . . . . . . 3-44 3.8 RECOVERY FROM AN UNINTENTIONAL SPIN . . . . . . . . . . . . . 3-45 3.9 OTHER EMERGENCIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-46 3.9.1 ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-46 3.9.2 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-47 3.9.3 UNLOCKED DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-48 NOTE Procedures for uncritical system faults are given in Chapter 4B - ABNORMAL OPERATING PROCEDURES. DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 3 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 here 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 aircraft"). 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. Thus it should be guaranteed that the pilot is at no time shocked by an engine failure and that he can act calmly and with determination. Emergency Procedures DA 40 NG AFM Page 3 - 4 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event KIAS Airspeed for best glide angle (Flaps UP) 88 KIAS Airspeed for emergency landing with engine off Flaps UP 83 KIAS Flaps T/O 78 KIAS Flaps LDG 77 KIAS DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 5 3.2 INSTRUMENT INDICATIONS IN PROHIBITED (RED) RANGE 3.2.1 ENGINE TEMPERATURE 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 for COOL LVL (if G1000 is installed) or WATERLEV (if SED is installed) caution message (low coolant level). COOL LVL (if G1000 is installed) or WATERLEV (if SED is installed) Caution Message Not Displayed: During climb: - Reduce power 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 as far as possible and increase airspeed. CONTINUED Emergency Procedures DA 40 NG AFM Page 3 - 6 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E During cruise: - Reduce power, or - Increase airspeed, if necessary by initiating a descent. - Check coolant temperature in green range. CAUTION If high coolant temperature is indicated and the COOL LVL (if G1000 is installed) or WATERLEV (if SED is installed) 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 3.3.4 - ENGINE FAILURE IN FLIGHT. COOL LVL (if G1000 is installed) or WATERLEV (if SED is installed) Caution Message Displayed: - Reduce power. - Expect loss of coolant. WARNING A further increase in coolant temperature must be expected. Prepare for an engine failure in accordance with 3.3.4 - ENGINE FAILURE IN FLIGHT. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 7 3.2.2 OIL TEMPERATURE 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. - Expect loss of engine oil. WARNING A further increase in oil temperature must be expected. Prepare for an engine failure in accordance with 3.3.4 - ENGINE FAILURE IN FLIGHT. If the Oil Pressure Is Within the Green Range: - Reduce power. - Increase airspeed. CONTINUED Emergency Procedures DA 40 NG AFM Page 3 - 8 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 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 3.3.4 - ENGINE FAILURE IN FLIGHT. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 9 3.2.3 OIL PRESSURE Engine oil pressure is in the lower red range (too low / below 0.9 bar). Oil pressures below the limit value of 0.9 bar can lead to a total loss of power due to engine failure. - Reduce power. - Expect loss of oil. WARNING Land at the nearest suitable airfield. Prepare for an engine failure in accordance with 3.3.4 - ENGINE FAILURE IN FLIGHT. END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 10 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.2.4 GEARBOX TEMPERATURE 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. - 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 3.3.4 - ENGINE FAILURE IN FLIGHT. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 11 3.2.5 L/R FUEL TEMPERATURE 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. - 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. The fuel temperature can be decreased by transferring fuel from the auxiliary to the main tank. END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 12 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.2.6 FUEL PRESSURE Engine fuel pressure is low. 1. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . check 2. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . check ON 3. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . ON If FUEL PRESS (if G1000 is installed) or FUELPRESS (if SED is installed) Warning Remains: 4. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY 5. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . OFF If FUEL PRESS (if G1000 is installed) or FUELPRESS (if SED is installed) Warning Still Remains: WARNING Imminent engine failure must be expected. Prepare for an engine failure in accordance with 3.3.4 - ENGINE FAILURE IN FLIGHT. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 13 3.2.7 ALTERNATOR AMPS Engine alternator output is in the upper red range (too high / above 70 A). This warning is indicated when the consumption of electrical power is too high. % Possible reasons are: % - A fault in wiring or equipment. % 1. Electrical equipment . . . . . . . . . . . . . . . . . . . switch OFF as necessary and % possible to reduce electric load % % If the problem does not clear itself: % % 2. Land on the nearest suitable airfield. % END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 14 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.2.8 ALTERNATOR FAIL Engine alternator has failed. The batteries are the last remaining source of electrical power for about 30 minutes. 1. Circuit breakers . . . . . . . . . . . . . . . . . . . . . . check 2. ESSENTIAL BUS . . . . . . . . . . . . . . . . . . . . . ON 3. Electrical equipment . . . . . . . . . . . . . . . . . . . switch OFF all equipment which is not needed 4. Land on the nearest suitable airfield. WARNING The ECU which is absolutely necessary for engine operation needs electrical power. It is recommended to switch off all electrical consumers and to land as soon as possible. Be prepared for an engine failure and an emergency landing. For a severe electrical failure a ECU backup battery system is installed. CAUTION For cases in which the battery capacity is not sufficient to reach a suitable airfield, an emergency battery is installed, serving as an additional back-up system for the backup attitude gyro (artificial horizon) and flood light. This battery is switched on with the EMERGENCY switch, located on the top left side of the instrument panel. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 15 3.3 ENGINE PROBLEMS 3.3.1 ENGINE PROBLEMS ON GROUND 1. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as required NOTE If considered necessary, the engine must be shut down. Otherwise the cause of the problem must be established in order to re-establish engine performance. CAUTION If the oil pressure is in the red range, the engine must be shut down immediately. WARNING If the problem cannot be cleared, the airplane must not be flown. END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 16 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.3.2 ENGINE PROBLEMS DURING TAKE-OFF (a) Take-Off Can Still Be Aborted (Sufficient Runway Length Available) Land Straight Ahead: 1. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . IDLE On the Ground: 2. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as required WARNING If sufficient time is remaining, the risk of fire in the event of a collision can be reduced as follows: - Fuel valve . . . . . . . . . . . . . . . . . . OFF - ENGINE MASTER . . . . . . . . . . . OFF - ELECTRIC MASTER . . . . . . . . . . OFF END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 17 (b) Take-Off Can No Longer Be Aborted 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . immediate pitch down to avoid airspeed reduction WARNING If, in the event of an engine problem occurring during take-off, the take-off can no longer be aborted and a safe height has not been reached, then a straight-ahead emergency landing should be considered. Do not attempt to turn back to the airfield. Turning back can be fatal. If Time Allows: 2. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . check MAX 3. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . check ON 5. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . check AUTO WARNING If the problem does not clear itself immediately, and the engine is no longer producing sufficient power, then an emergency landing must be carried out in accordance with 3.7.1 - EMERGENCY LANDING WITH ENGINE OFF. END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 18 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.3.3 ENGINE TROUBLESHOOTING IN FLIGHT WARNING Control over the flight attitude has priority over attempts to solve the current problem ("first fly the airplane"). 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88 KIAS 2. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . MAX 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. If ECU A and ECU B Cautions Appear Simultaneously - If the indicated LOAD remains unchanged, and - if the perceived thrust is reduced, and - if the engine noise level changes or the engine is running rough: 3. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . . IDLE for 1 second 4. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . . slowly increase to 1975 RPM If the engine shows a power loss during the POWER lever increase: 5. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . . IDLE for 1 second 6. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . . slowly increase, stop prior to the previously observed engine power loss RPM CONTINUED DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 19 WARNING Do not increase the POWER lever past the propeller speed of 1975 RPM or the setting determined in step 6. An increase of engine power beyond this setting leads into another power loss. NOTE With this power setting the engine can provide up to 65 % load at the maximum propeller speed of 1975 RPM. 7. Land at the next suitable airfield. Otherwise: Depending on the situation the following attempts can be made to restore normal engine operation: 3. Circuit breakers . . . . . . . . . . . . . . . . . . . . . . check / reset if necessary If normal engine operation is restored continue flight and land as soon as possible. Otherwise: 4. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . swap between ECU A and B If either ECU A or B setting restores normal engine operation then maintain ECU setting and land as soon as possible. CONTINUED Emergency Procedures DA 40 NG AFM Page 3 - 20 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E Otherwise: 5. 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: 6. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY If normal engine operation is restored continue flight and land as soon as possible. Remain within maximum allowable lateral imbalance. Otherwise: 7. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . NORMAL 8. Alternate air . . . . . . . . . . . . . . . . . . . . . . . . . OPEN 9. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . apply power as 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 3.3.4 - ENGINE FAILURE IN FLIGHT and land as soon as possible. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 21 3.3.4 ENGINE FAILURE IN FLIGHT WARNING Control over the flight attitude has priority over attempts to solve the current problem ("first fly the airplane"). NOTE As long as there is no major mechanical engine defect, the propeller will continue to windmill. 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88 KIAS 2. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP If the Remaining Altitude is Sufficient for an Restart Attempt: Try to restart the engine, refer to 3.3.5 - RESTARTING THE ENGINE IN FLIGHT. If the Remaining Altitude is NOT Sufficient for an Restart Attempt: Carry out an emergency landing in accordance with 3.7.1 - EMERGENCY LANDING WITH ENGINE OFF. END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 22 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.3.5 RESTARTING THE ENGINE IN FLIGHT NOTE With a failed engine the propeller continues to windmill. A stopped propeller indicates a major mechanical engine defect. Starter assisted restart shall not be considered. Maximum restart altitude: 16,400 ft pressure altitude . . . . . . . . . . . . . . . for immediate restarts 10,000 ft pressure altitude . . . . . . . . . . . . . . . for restarts within two minutes NOTE If the engine is allowed to cool down for more than two minutes, a successful restart may not be possible. 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . 88 KIAS 2. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . IDLE 3. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . check AUTO 4. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . check NORMAL 5. Alternate air . . . . . . . . . . . . . . . . . . . . . . . . . as required 6. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . check 7. Fuel transfer pump . . . . . . . . . . . . . . . . . . . . as required 8. ELECTRIC MASTER . . . . . . . . . . . . . . . . . . check ON 9. ENGINE MASTER . . . . . . . . . . . . . . . . . . . . check ON CONTINUED DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 23 If Engine Does Not Start: 10. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY If Engine Does Not Start Adopt Glide Configuration: 11. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP 12. Airspeed88 KIAS NOTE The glide ratio is 9.7; i.e., for every 1000 ft (305 m) of altitude loss the maximum horizontal distance traveled in still air is 1.59 NM (2.94 km). During this the propeller will continue to windmill. Carry out an emergency landing in accordance with 3.7.1 - EMERGENCY LANDING WITH ENGINE OFF. CAUTION Engine restart following an engine fire should only be attempted if it is unlikely that a safe emergency landing can be made. It must be expected that engine restart is impossible after an engine fire. 13. AVIONIC MASTER . . . . . . . . . . . . . . . . . . . . ON, if required END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 24 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.3.6 DEFECTIVE RPM REGULATING SYSTEM WARNING In case of defective RPM regulating system, reduced engine performance should be anticipated. CAUTION Following a failure of the governor the RPM should be adjusted with the POWER lever. CAUTION The POWER lever should be moved slowly, in order to avoid over-speeding and excessively rapid RPM changes. The light wooden propeller blades produce more rapid RPM changes than metal blades. (a) Oscillating RPM 1. Power setting . . . . . . . . . . . . . . . . . . . . . . . . change If the Problem Does Not Clear: 2. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . swap between ECU A and B If the Problem Does Not Clear: 3. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . AUTO 4. Land on the nearest suitable airfield. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 25 (b) Propeller Overspeed CAUTION Climb performance will be reduced. NOTE The propeller now works like a fixed pitch propeller. RPM is controlled by the engine power setting. Flight to the nearest airfield can be continued with a lower power setting and at a lower airspeed. Climb and go-around may not be possible under all conditions. 1. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . reduce to not exceed 2300 RPM 2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88 KIAS 3. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . check UP After RPM has Stabilized Below 2300 RPM: 4. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . as required, do not exceed 2300 RPM 5. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . as required, do not exceed 2300 RPM If the Problem Does Not Clear: 6. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . swap between ECU A and B NOTE If selecting ECU A or ECU B does not solve the problem, switch back to AUTO. Keep controlling the climb/sink rate with the POWER lever and do not exceed 2300 RPM. CONTINUED Emergency Procedures DA 40 NG AFM Page 3 - 26 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E If the Problem Does Not Clear: 7. Land on the nearest suitable airfield. If an Increased Climb Rate is Required: 8. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . T/O position 9. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72 KIAS 10. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . as required, do not exceed 2300 RPM END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 27 (c) Propeller Underspeed 1. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . as required If the Problem Does Not Clear 2. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . swap between ECU A and B If the Problem Does Not Clear: 3. VOTER switch . . . . . . . . . . . . . . . . . . . . . . . AUTO 4. POWER lever . . . . . . . . . . . . . . . . . . . . . . . as required WARNING Due to this problem the propeller RPM will drop. There may be no climb performance and no go-around power available. 5. Land on the nearest suitable airfield. END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 28 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.3.7 FUEL TRANSFER PUMP FAILURE 1. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . check If Main Tank Fuel Quantity Low: 2. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY 3. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . OFF WARNING The fuel valve must be switched back to NORMAL before the auxiliary tank indication reads zero! Otherwise, the engine will stop during flight when the auxiliary tank is empty. WARNING When the fuel pump takes in air (e.g. when the fuel valve is not switched back and the auxiliary tank is empty), an inspection of the pump is necessary prior to next flight. CAUTION When set to EMERGENCY, fuel is transferred from the auxiliary tank to the main tank at a rate of approximately 45 US gal/h (170 liter/h). 4. AUX tank . . . . . . . . . . . . . . . . . . . . . . . . . . . monitor quantity 5. MAIN tank . . . . . . . . . . . . . . . . . . . . . . . . . . . monitor quantity CONTINUED DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 29 NOTE AUX tank quantity must not be less than 1 US gal and MAIN tank quantity must not be more than 14 US gal. 6. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . NORMAL 7. Land as soon as practicable. END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 30 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.4 FAILURES IN THE ELECTRICAL SYSTEM 3.4.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM 1. Circuit breakers . . . . . . . . . . . . . . . . . . . . . . check IN 2. ESSENTIAL BUS . . . . . . . . . . . . . . . . . . . . . ON If There Is Still No Electrical Power Available: 2. EMERGENCY switch (if installed) . . . . . . . . ON 3. Flood light, if necessary . . . . . . . . . . . . . . . . ON 4. POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . set based on lever positions and engine noise 5. Prepare landing with flaps in the given position. Refer to 4B.5 - FAILURES IN FLAP OPERATING SYSTEM. 6. Land on the nearest suitable airfield. WARNING Engine stoppage may occur, depending on the failure mode. A backup battery is installed for the ECU to provide electrical power solely to ECU B and its system for at least 30 minutes. NOTE The backup artificial horizon and the flood light will have electrical power for at least 1.5 hours. If G1000 is installed make use of the stand-by airspeed indicator and altimeter. Engine power can be set via visual reference of the POWER lever position. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 31 3.4.2 HIGH CURRENT If HIGH CURRENT (> 70 A) is indicated on the G1000 (if installed) or SED (if installed): 1. ESSENTIAL BUS . . . . . . . . . . . . . . . . . . . . . ON 2. ENGINE SYSTEM DISPLAY (if G1000 is installed) . . . . . . . . . . . . . . . . . . select by pressing ENGINE and SYSTEM softkey on MFD 3. Circuit breakers . . . . . . . . . . . . . . . . . . . . . . check IN 4. Ammeter/Voltmeter . . . . . . . . . . . . . . . . . . . monitor 5. Land on the nearest suitable airfield. END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 32 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.4.3 STARTER MALFUNCTION If the starter does not disengage from the engine after starting (Starter engaged warning (STARTER) on the G1000 (if installed) or START on the White Wire annunciator (if installed) illuminates after the engine has started): On Ground: 1. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. ENGINE MASTER . . . . . . . . . . . . . . . . . . . . OFF 3. ELECTRIC MASTER . . . . . . . . . . . . . . . . . . OFF Terminate flight preparation! In Flight: Land as soon as possible. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 33 3.5 SMOKE AND FIRE 3.5.1 SMOKE AND FIRE ON GROUND (a) Engine Fire When Starting on the Ground 1. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. Fuel transfer pump . . . . . . . . . . . . . . . . . . . . OFF 3. ENGINE MASTER . . . . . . . . . . . . . . . . . . . . OFF 4. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 5. ELECTRIC MASTER . . . . . . . . . . . . . . . . . . OFF After Standstill: 6. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . open 7. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . evacuate immediately END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 34 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E (b) Electrical Fire with Smoke on the Ground 1. ELECTRIC MASTER . . . . . . . . . . . . . . . . . . OFF If the Engine Is Running: 2. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . IDLE 3. ENGINE MASTER . . . . . . . . . . . . . . . . . . . . OFF 4. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . OFF When the Engine Has Stopped: 6. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . open 7. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . evacuate immediately END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 35 3.5.2 SMOKE AND FIRE DURING TAKE-OFF (a) If Take-Off Can Still Be Aborted 1. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 3. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . apply - bring the airplane to a stop 4. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 5. Fuel transfer pump . . . . . . . . . . . . . . . . . . . . OFF 6. ENGINE MASTER . . . . . . . . . . . . . . . . . . . . OFF 7. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 8. ELECTRIC MASTER . . . . . . . . . . . . . . . . . . OFF After Standstill: 9. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . open 10. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . evacuate immediately END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 36 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E (b) If Take-Off Cannot Be Aborted 1. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. If possible, fly along a short-cut traffic circuit and land on the airfield. WARNING If, in the event of an engine problem occurring during take-off, the take-off can no longer be aborted and a safe height has not been reached, then a straight-ahead emergency landing should be carried out. Do not attempt to turn back to the airfield. Turning back can be fatal. Refer to 3.3.2 - ENGINE PROBLEMS DURING TAKE-OFF. After Climbing to a Height From Which the Selected Landing Area Can Be Reached Safely: 3. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 4. Fuel transfer pump . . . . . . . . . . . . . . . . . . . OFF 5. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 6. ENGINE MASTER . . . . . . . . . . . . . . . . . . . . OFF 7. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 8. ELECTRIC MASTER . . . . . . . . . . . . . . . . . . OFF 9. Emergency windows . . . . . . . . . . . . . . . . . . . open if necessary 10. Carry out an emergency landing with engine off. Allow for increased landing distance due to the flap position. Refer to 3.7.1 - EMERGENCY LANDING WITH ENGINE OFF. CONTINUED DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 37 CAUTION In case of extreme smoke development, the front canopy may be unlatched during flight. This allows it to partially open, in order to improve ventilation. The canopy will remain open in this position. Flight characteristics will not be affected significantly. When Airplane Has Stopped: 11. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . open 12. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . evacuate immediately END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 38 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.5.3 SMOKE AND FIRE IN FLIGHT WARNING In the event of smoke or fire, prepare to land the airplane without delay while completing fire suppression and/or smoke evacuation procedures. If it cannot be visually verified that the fire has been completely extinguished, whether the smoke has cleared or not, land immediately. (a) Engine Fire in Flight 1. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. Select appropriate emergency landing area. When it Seems Certain That the Landing Area Will Be Reached: 3. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 4. POWER lever . . . . . . . . . . . . . . . . . . . . . . . . MAX 5. Emergency windows . . . . . . . . . . . . . . . . . . . open if required 6. Land immediately. Refer to 3.7.1 - EMERGENCY LANDING WITH ENGINE OFF. CAUTION In case of extreme smoke development, the front canopy may be unlatched during flight. This allows it to partially open, in order to improve ventilation. The canopy will remain open in this position. Flight characteristics will not be affected significantly. When Airplane Has Stopped: 7. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . open 8. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . evacuate immediately END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 39 (b) Electrical Fire with Smoke in Flight 1. EMERGENCY switch (if installed) . . . . . . . . ON 2. AVIONIC MASTER . . . . . . . . . . . . . . . . . . . . OFF 3. ELECTRIC MASTER . . . . . . . . . . . . . . . . . . OFF 4. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 5. Emergency windows . . . . . . . . . . . . . . . . . . . open if required 6. Land immediately. Refer to 3.7.1 - EMERGENCY LANDING WITH ENGINE OFF. WARNING Switching OFF the ELECTRIC MASTER will lead to total failure of all electronic and electric equipment. Also affected from this is the attitude gyro (artificial horizon). However, by switching the EMERGENCY switch ON, if installed, the emergency battery, if installed will supply power to the 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 partially open, in order to improve ventilation. The canopy will remain open in this position. Flight characteristics will not be affected significantly. When Airplane Has Stopped: 7. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . open 8. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . evacuate immediately END OF CHECKLIST Emergency Procedures DA 40 NG AFM Page 3 - 40 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 3.6 GLIDING 1. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP 2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88 KIAS NOTE The glide ratio is 9.7; i.e., for every 1000 ft (305 m) of altitude loss the maximum horizontal distance traveled in still air is 1.59 NM (2.94 km). During this the propeller will continue to windmill. NOTE For operation without wheel fairings the glide ratio is reduced to 9.4; i.e., for every 1000 ft (305 m) of altitude loss the maximum horizontal distance traveled in still air is 1.54 NM (2.85 km). During this the propeller will continue to windmill. END OF CHECKLIST DA 40 NG AFM Emergency Procedures Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 3 - 41 3.7 EMERGENCY LANDINGS NOTE For all airspeed tables in the following sections apply linear variations between weights. 3.7.1 EMERGENCY LANDING WITH ENGINE OFF CAUTION % For emergency landing the adjustable backrests (if installed) % must be fixed in the upright position. % 1. Adjustable backrests (if installed) . . . . . . . . . adjust to the upright % position described by a placard % on the roll-over bar and verify % proper fixation % 2. ENGINE MASTER . . . . . . . . . . . . . . . . . . . . check OFF % 3. Fuel transfer pump . . . . . . . . . . . . . . . . . . . . OFF % 4. Fuel pumps . . . . . . . . . . . . . . . . . . . . . . . . . . OFF % 5. Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF % 6. AVIONIC MASTER . . . . . . . . . . . . . . . . . . . . OFF % 7. Safety harnesses . . . . . . . . . . . . . . . . . . . . . check fastened and tightened % When Sure of Making Landing Area: 8. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . T/O or LDG, as required % NOTE Extending the flaps to LDG will increase drag and incur a high sink rate. When the landing area can be reached safely, landing with flaps LDG is advisable. CONTINUED Emergency Procedures DA 40 NG AFM Page 3 - 42 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E 9. Approach speed . . . . . . . . . . . . . . . . . . . . . . see table below: % % Flaps 940 kg (2072 lb) 1000 kg (2205 lb) 1080 kg (2381 lb) 1160 kg (2557 lb) 1216 kg (2681 lb) up to 1280 kg (2822 lb) T/O 68 KIAS 70 KIAS 73 KIAS 76 KIAS 77 KIAS 78 KIAS LDG 66 KIAS 69 KIAS 72 KIAS 74 KIAS 76 KIAS 77 KIAS 10. ELECTRIC MASTER . . . . . . . . . . . . . . . . . . OFF % 11. Touch down