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Diamond Aircraft DA 42 NG Airplane Flight Manual

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Page 2 DA 42 NG AFM Introduction Intentionally left blank. Page 0 - 0a Rev. 7 02-Oct-2017 Doc. # 7.01.15-E...
Page 3 Before this airplane is operated for the first time, the pilot must familiarize himself with the complete contents of this Airplane Flight Manual. In the event that you have obtained your DIAMOND DA 42 NG second-hand, please let us know your address, so that we can supply you with the publications necessary for the safe operation of your airplane.
Page 4 Introduction DA 42 NG AFM 0.1 APPROVAL The content of approved chapters is approved by EASA. All other content is approved by DAI under the authority of EASA DOA No. EASA.21J.052 in accordance with Part 21. 0.2 RECORD OF REVISIONS All revisions of this manual, with the exception of - •...
Page 5 DA 42 NG AFM Introduction Date of Rev. Chap- EASA Approval Date Reason Page(s) Signature Approval No. Date Inserted Revision EASA EASA.A.C. 18-Feb-2009 Certification 090012 FAA Certification, MÄM 42-336, 42-338, 42-353, 42-357, 42-363, 42-374, 30-Nov-2009 42-403, CSV.A.01553 OÄM 42-053, 42-142,...
Page 6 Introduction DA 42 NG AFM Date of Rev. Chap- EASA Approval Date Reason Page(s) Signature Approval No. Date Inserted Revision MÄM 42- -377, -426, -437, -456, -466, -488, -499, -530a&-674, -542, -547, -551, -575, -584, -585, -589, -602, -641, -685, -696, -701, OÄM 42-...
Page 7 DA 42 NG AFM Introduction Date of Rev. Chap- EASA Approval Date Reason Page(s) Signature Approval No. Date Inserted Revision 0-4 thru 0-16, MÄM 42- 1-2, 1-3, 1-7, 1-22, -685, -757 Revision 5 of 2-2, 2-43, the AFM Doc. 3-75, No.
Page 8 Introduction DA 42 NG AFM Date of Rev. Chap- EASA Approval Date Reason Page(s) Signature Approval No. Date Inserted Revision Page 0 - 6 Rev. 7 02-Oct-2017 Doc. # 7.01.15-E...
Page 9 DA 42 NG AFM Introduction 0.3 LIST OF EFFECTIVE PAGES Page Date Page Date 19-Jun-2012 02-Oct-2017 0-0a 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 1-10 02-Oct-2017 02-Oct-2017 1-11 02-Oct-2017 02-Oct-2017 1-12...
Page 10 Introduction DA 42 NG AFM Page Date Page Date appr. 2-1 02-Oct-2017 appr. 2-29 02-Oct-2017 appr. 2-2 02-Oct-2017 appr. 2-30 02-Oct-2017 appr. 2-3 02-Oct-2017 appr. 2-31 02-Oct-2017 appr. 2-4 02-Oct-2017 appr. 2-32 02-Oct-2017 appr. 2-5 02-Oct-2017 appr. 2-33 02-Oct-2017 appr. 2-6 02-Oct-2017 appr.
Page 11 DA 42 NG AFM Introduction Page Date Page Date 02-Oct-2017 3-29 02-Oct-2017 02-Oct-2017 3-30 02-Oct-2017 02-Oct-2017 3-31 02-Oct-2017 02-Oct-2017 3-32 02-Oct-2017 02-Oct-2017 3-33 02-Oct-2017 02-Oct-2017 3-34 02-Oct-2017 02-Oct-2017 3-35 02-Oct-2017 02-Oct-2017 3-36 02-Oct-2017 02-Oct-2017 3-37 02-Oct-2017 3-10 02-Oct-2017 3-38 02-Oct-2017...
Page 12 Introduction DA 42 NG AFM Page Date Page Date 3-57 02-Oct-2017 4A-1 02-Oct-2017 3-58 02-Oct-2017 4A-2 02-Oct-2017 3-59 02-Oct-2017 4A-3 02-Oct-2017 3-60 02-Oct-2017 4A-4 02-Oct-2017 3-61 02-Oct-2017 4A-5 02-Oct-2017 3-62 02-Oct-2017 4A-6 02-Oct-2017 3-63 02-Oct-2017 4A-7 02-Oct-2017 3-64 02-Oct-2017 4A-8...
Page 13 DA 42 NG AFM Introduction Page Date Page Date 4A-29 02-Oct-2017 4A-57 02-Oct-2017 4A-30 02-Oct-2017 4A-58 02-Oct-2017 4A-31 02-Oct-2017 4A-59 02-Oct-2017 4A-32 02-Oct-2017 4A-60 02-Oct-2017 4A-33 02-Oct-2017 4A-61 02-Oct-2017 4A-34 02-Oct-2017 4A-62 02-Oct-2017 4A-35 02-Oct-2017 4A-63 02-Oct-2017 4A-36 02-Oct-2017 4A-64...
Page 14 Introduction DA 42 NG AFM Page Date Page Date 4B-1 02-Oct-2017 4B-29 02-Oct-2017 4B-2 02-Oct-2017 4B-30 02-Oct-2017 4B-3 02-Oct-2017 4B-31 02-Oct-2017 4B-4 02-Oct-2017 4B-32 02-Oct-2017 4B-5 02-Oct-2017 4B-33 02-Oct-2017 4B-6 02-Oct-2017 4B-34 02-Oct-2017 4B-7 02-Oct-2017 4B-35 02-Oct-2017 4B-8 02-Oct-2017 4B-36...
Page 15 DA 42 NG AFM Introduction Page Date Page Date 02-Oct-2017 5-29 02-Oct-2017 02-Oct-2017 5-30 02-Oct-2017 02-Oct-2017 5-31 02-Oct-2017 02-Oct-2017 5-32 02-Oct-2017 02-Oct-2017 5-33 02-Oct-2017 02-Oct-2017 5-34 02-Oct-2017 02-Oct-2017 5-35 02-Oct-2017 02-Oct-2017 5-36 02-Oct-2017 02-Oct-2017 5-37 02-Oct-2017 5-10 02-Oct-2017 5-38 02-Oct-2017...
Page 16 Introduction DA 42 NG AFM Page Date Page Date 02-Oct-2017 6-29 02-Oct-2017 02-Oct-2017 6-30 02-Oct-2017 02-Oct-2017 6-31 02-Oct-2017 02-Oct-2017 6-32 02-Oct-2017 02-Oct-2017 6-33 02-Oct-2017 02-Oct-2017 6-34 02-Oct-2017 02-Oct-2017 02-Oct-2017 Page Date 02-Oct-2017 02-Oct-2017 6-10 02-Oct-2017 02-Oct-2017 6-11 02-Oct-2017 02-Oct-2017 6-12...
Page 17 DA 42 NG AFM Introduction Page Date Page Date 7-21 02-Oct-2017 7-49 02-Oct-2017 7-22 02-Oct-2017 7-50 02-Oct-2017 7-23 02-Oct-2017 7-51 02-Oct-2017 7-24 02-Oct-2017 7-52 02-Oct-2017 7-25 02-Oct-2017 7-53 02-Oct-2017 7-26 02-Oct-2017 7-54 02-Oct-2017 7-27 02-Oct-2017 7-55 02-Oct-2017 7-28 02-Oct-2017 7-56...
Page 18 Introduction DA 42 NG AFM Page Date Page Date 7-77 02-Oct-2017 02-Oct-2017 7-78 02-Oct-2017 02-Oct-2017 7-79 02-Oct-2017 02-Oct-2017 7-80 02-Oct-2017 02-Oct-2017 7-81 02-Oct-2017 02-Oct-2017 7-82 02-Oct-2017 02-Oct-2017 7-83 02-Oct-2017 7-84 02-Oct-2017 Page Date 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017 02-Oct-2017...
Page 19 DA 42 NG AFM Introduction 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) ........1 OPERATING LIMITATIONS (an approved chapter) .
Page 20 Introduction DA 42 NG AFM Intentionally left blank. Page 0 - 18 Rev. 7 02-Oct-2017 Doc. # 7.01.15-E...
Page 21 DA 42 NG AFM General CHAPTER 1 GENERAL Page INTRODUCTION ........1-2 CERTIFICATION BASIS .
Page 22 General DA 42 NG AFM 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.
Page 23 DA 42 NG AFM General Modification Source Installed Garmin Hard- and Software MÄM 42-978 9 yes 9 no Upgrade I (Garmin G1000 NXi) Garmin GWX 68 Weather Radar OÄM 42-119 9 yes 9 no Ice Protection System OÄM 42-053 9 yes...
Page 24 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.
Page 25 DA 42 NG AFM General 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...
Page 26 General DA 42 NG AFM 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...
Page 27 DA 42 NG AFM General Wing Flaps Area (total, left + right) : 2.18 m² 23.5 sq.ft. Horizontal Tail Area : 2.35 m 25.3 sq.ft. Elevator area : 0.66 m² 7.1 sq.ft. Angle of incidence : -1.1° relative to longitudinal axis of airplane...
Page 28 General DA 42 NG AFM 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.
Page 29 DA 42 NG AFM General Maximum Structural Cruising Speed. This speed may be exceeded only in smooth air, and then only with caution. Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration.
Page 30 General DA 42 NG AFM 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.
Page 31 DA 42 NG AFM General MET: Weather, weather advice. NAV: Navigation, route planning. RoC: Rate of Climb. (d) Mass and Balance 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.
Page 32 General DA 42 NG AFM 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.
Page 33 DA 42 NG AFM General (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...
Page 34 General DA 42 NG AFM 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 Automatic Direction Finder Distance Measuring Equipment Wx RDR...
Page 35 DA 42 NG AFM General 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...
Page 36 General DA 42 NG AFM (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:...
Page 37 DA 42 NG AFM General 1.6 UNITS OF MEASUREMENT 1.6.1 CONVERSION FACTORS Dimension SI-Units US Units Conversion Length [mm] millimeters [in] inches [mm] / 25.4 = [in] meters [ft] feet [m] / 0.3048 = [ft] [km] kilometers [NM] nautical [km] / 1.852 = [NM]...
Page 38 General DA 42 NG AFM Dimension SI-Units US Units Conversion Intensity of ampères electric current Electric [Ah] ampère-hours charge (battery capacity) Electric volts potential Time [sec] seconds Page 1 - 18 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 39 DA 42 NG AFM General 1.6.2 CONVERSION CHART LITERS / US GALLONS Liters US Gallons US Gallons Liters 15.1 22.7 30.3 37.9 45.4 10.6 53.0 11.9 60.6 13.2 68.1 15.9 75.7 18.5 83.3 21.1 90.9 23.8 98.4 26.4 106.0 29.1 113.6...
Page 40 General DA 42 NG AFM 1.7 THREE-VIEW DRAWING Page 1 - 20 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 41 DA 42 NG AFM General 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,...
Page 42 As installed on the DA 42 NG, the Garmin GWX 68 and the GWX 70 have a range of 160 nautical miles. Refer to Garmin G1000 Pilot’s Guide for the DA 42 NG, P/N 190-00962-( ) for Garmin G1000 or P/N 190-02237-( ) for G1000 NXi in the latest effective issue for further information.
Page 43 DA 42 NG AFM General 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.
Page 44 General DA 42 NG AFM 1.9.3 AVIONICS SYSTEM Address: Garmin International, Inc. 1200 East 151 Street Olathe, Kansas 66062 Phone: +1-(913)-3978200 Fax: +1-(913)-3978282 Website: www.garmin.com Documents: G1000 Cockpit Reference Guide P/N 190-00963-( ), latest revision G1000 Pilot’s Guide P/N 190-00962-( ), latest revision...
Page 45 DA 42 NG AFM Operating Limitations CHAPTER 2 OPERATING LIMITATIONS Page INTRODUCTION ........2-3 AIRSPEED .
Page 46 Operating Limitations DA 42 NG AFM 2.16.6 GARMIN G1000 AVIONICS SYSTEM ....2-39 2.16.7 AUTOPILOT LIMITATIONS ..... . . 2-43 2.16.8 SMOKING .
Page 47 DA 42 NG AFM Operating Limitations 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.
Page 48 Operating Limitations DA 42 NG AFM 2.2 AIRSPEED Airspeed KIAS Remarks Operating above 1800 kg 122 KIAS Do not make full or abrupt control surface maneuvering (3968 lb) movement above this speed speed. above 1700 kg 119 KIAS (3748 lb) to...
Page 49 DA 42 NG AFM Operating Limitations 2.3 AIRSPEED INDICATOR MARKINGS Marking KIAS Significance White arc 62 - 113 KIAS Operating range with flaps fully extended. If MÄM 42-678 is carried out: 64 - 113 KIAS Green arc 69 - 151 KIAS Normal operating range.
Page 50 Operating Limitations DA 42 NG AFM 2.4 POWER-PLANT LIMITATIONS a) Number of engines 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)
Page 51 DA 42 NG AFM Operating Limitations 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 If G1000 system software prior to P/N 010-00670-04 is installed: Normal range 50 °C - 125 °C...
Page 52 Operating Limitations DA 42 NG AFM 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...
Page 53 DA 42 NG AFM Operating Limitations NOTE The fuel pressure is not indicated on the G1000; a fuel pressure warning will illuminate on the PFD if the pressure is below limit. m)Voltage Minimum 24.1 V Maximum 32.0 V n) Amperage...
Page 54 Operating Limitations DA 42 NG AFM t) Oil specification SAE Grade 5W-30: SHELL HELIX ULTRA ADDINOL SUPER POWER MV 0537 BP VISCO 5000 REPSOL ELITE COMMON RAIL GULF FORMULA GMX G-ENERGY F SYNTH QUARTZ 9000 ENERGY GULF FORMULA GX AEROSHELL Oil Diesel Ultra...
Page 55 DA 42 NG AFM Operating Limitations SAE Grade 0W-40: CASTROL SLX PROFESSIONAL LONGTEC CASTROL Edge 0W-40 A3/B4 CASTROL Edge Professional A3 SHELL Helix Ultra CAUTION Only engine oils conforming to MB 229.5 specification are approved by Austro Engine GmbH to be used for operation.
Page 56 Operating Limitations DA 42 NG AFM w) Maximum restart altitude 18,000 ft pressure altitude for immediate restarts 10,000 ft pressure altitude for restarts within two minutes If MÄM 42-938 (engine software VC33_2_05_19 or later approved software) is installed 15,000 ft pressure altitude...
Page 57 DA 42 NG AFM Operating Limitations 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the tables below. Indi- Yellow Green Yellow cation arc/bar arc/bar arc/bar arc/bar arc/bar lower caution normal caution upper prohibited...
Page 58 Operating Limitations DA 42 NG AFM Indi- Yellow Green Yellow cation arc/bar arc/bar arc/bar arc/bar arc/bar lower caution normal caution upper prohibited range operating range prohibited range range range Fuel below -30°C -30° to -20°C -20° to 55°C 55° to 60°C above 60°C...
Page 59 DA 42 NG AFM Operating Limitations 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 7.13 includes a detailed description of the alerts.
Page 60 Operating Limitations DA 42 NG AFM Warning Alerts Meaning / Cause (red) 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.
Page 61 DA 42 NG AFM Operating Limitations Color and Significance of the Caution Alerts on the G1000 Caution Alerts Meaning / Cause (amber) A fault has occurred in the left/right engine ECU A or L/R ECU A FAIL ECU A is being tested during FADEC-test procedure during the 'Before Take-Off Check'.
Page 62 Operating Limitations DA 42 NG AFM Color and Significance of the Advisory Alerts on the G1000 Advisory Alerts Meaning / Cause (white) L/R GLOW ON Left / Right engine glow plug active. L/R AUXPUMP Fuel transfer from auxiliary to main tank is in progress (if installed).
Page 63 DA 42 NG AFM Operating Limitations 2.7 MASS (WEIGHT) Mass (Weight) Value Minimum flight mass 1450 kg 3197 lb Maximum take-off mass 1900 kg 4189 lb Maximum take-off mass (if MÄM 42-678 is carried out) 1999 kg 4407 lb Maximum zero fuel mass...
Page 64 Operating Limitations DA 42 NG AFM 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.
Page 65 DA 42 NG AFM Operating Limitations 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.
Page 66 Operating Limitations DA 42 NG AFM WARNING Exceeding the center of gravity limitations reduces the controllability and stability of the airplane. 2.9 APPROVED MANEUVERS The airplane is certified in the Normal Category in accordance with JAR-23. Approved Maneuvers 1) All normal flight maneuvers;...
Page 67 DA 42 NG AFM Operating Limitations 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 v at v...
Page 68 Operating Limitations DA 42 NG AFM 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: •...
Page 69 DA 42 NG AFM Operating Limitations NOTE Many of the items of minimum equipment listed in the following table are integrated in the G1000. for Daytime in Addition for in Addition for VFR Flights Night VFR Flights IFR Flights Flight &...
Page 70 Operating Limitations DA 42 NG AFM for Daytime in Addition for in Addition for VFR Flights Night VFR Flights IFR Flights Engine * Fuel qty. (2x) * Ammeter instruments * Oil press. (2x) * Voltmeter * Oil temp. (2x) * Coolant temp. (2x)
Page 71 DA 42 NG AFM Operating Limitations for Daytime in Addition for in Addition for VFR Flights Night VFR Flights IFR Flights Other * Stall warning * Pitot heating * Emergency battery operational system system (for backup attitude minimum gyro and flood light)
Page 72 Operating Limitations DA 42 NG AFM 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.
Page 73 DA 42 NG AFM Operating Limitations 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.
Page 74 Operating Limitations DA 42 NG AFM 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).
Page 75 DA 42 NG AFM Operating Limitations 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.
Page 76 Operating Limitations DA 42 NG AFM LANDING GEAR = 188 KIAS = 152 KIAS If OÄM 42-179 is not incorporated: GPS NOT APPROVED FOR WAAS OPERATIONS On the Emergency Landing Gear Extension Lever: EMERGENCY Gear Extension Max. 152 KIAS On the Instrument Panel:...
Page 77 DA 42 NG AFM Operating Limitations Next to the Fuel Selector: Crossfeed with fuel pump ON in emergencies only (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):...
Page 78 Operating Limitations DA 42 NG AFM In Each Cowling, on the Door for the Oil Filler Neck: AUSTRO ENGINE SHELL HELIX Aero ULTRA 5W-40 5W30 or see Airplane or see Airplane Flight Manual Flight Manual Next to the Flap Selector Switch:...
Page 79 DA 42 NG AFM Operating Limitations Next to the Cabin Baggage Compartment: If OÄM 42-207 is carried out: EASA Doc. No. 7.01.15-E Rev. 7 02-Oct-2017 Page 2 - 35 approved...
Page 80 Operating Limitations DA 42 NG AFM In the Cabin, on the Left Fuselage Sidewall: In the Nose Baggage Compartment: Max. Baggage: 30 kg [66 lb] Beside the Door Locking Device Installed in the Passengers' Door: EMERGENCY EXIT: The keylock must be...
Page 81 DA 42 NG AFM Operating Limitations 2.16 OTHER LIMITATIONS 2.16.1 FUEL TEMPERATURE If G1000 system software prior to P/N 010-00670-06 is installed: From -25 °C to 60 °C (from -13 °F to 140 °F). If G1000 system software P/N 010-00670-06 or later is installed: From -30 °C to 60 °C (from -22 °F to 140 °F).
Page 82 Operating Limitations DA 42 NG AFM 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.
Page 83 DA 42 NG AFM Operating Limitations 2.16.6 GARMIN G1000 AVIONICS SYSTEM 1. The Garmin G1000 Cockpit Reference Guide, P/N 190-00963-( ) or Garmin G1000 NXi Cockpit Reference Guide, P/N 190-02238-( ), appropriate revision must be immediately available to the flight crew.
Page 84 Operating Limitations DA 42 NG AFM Software Part Number Approved Function Version 006-B0081-( ) COM1, COM2 006-B0083-( ) GS1, GS2 006-B0082-( ) NAV1, NAV2 NOTE The database version is displayed on the MFD power-up page immediately after system power-up and must be acknowledged.
Page 85 DA 42 NG AFM Operating Limitations 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. When an alternate airport is required by the applicable operating rules, it must...
Page 86 Operating Limitations DA 42 NG AFM 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: North of 72° N latitude at all longitudes.
Page 87 4. The Garmin G1000 Cockpit Reference Guide for the Diamond DA 42 NG, P/N 010-00963-( ) or Garmin G1000 NXi Cockpit Reference Guide for the Diamond DA 42 NG, P/N 010-02238-( ) approved revision must be immediately available to the flight crew.
Page 88 Operating Limitations DA 42 NG AFM 10. The GFC 700 components must utilize the following or later approved software versions: Sub-System Software Version v9.03 GDC 74 v3.02 GEA 7X v2.07 v3.03 GIA 6X v5.65 GIA Audio v2.03 GMAX347 v4.01 GMU44 v2.01...
Page 89 DA 42 NG AFM Operating Limitations 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 or OÄM 42-142) may only be used during cruise.
Page 90 Operating Limitations DA 42 NG AFM Intentionally left blank. EASA Page 2 - 46 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E approved...
Page 91 Emergency DA 42 NG AFM Procedures CHAPTER 3 EMERGENCY PROCEDURES Page INTRODUCTION ........3-4 3.1.1 GENERAL .
Page 92 Emergency DA 42 NG AFM Procedures G1000 FAILURES ........3-19 3.5.1 NAVIGATION INFORMATION FAILURE .
Page 93 Emergency DA 42 NG AFM Procedures 3.10.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . 3-56 3.10.2 HIGH CURRENT ....... . 3-57 3.10.3 STARTER MALFUNCTION .
Page 94 Emergency DA 42 NG AFM Procedures 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.
Page 95 Emergency DA 42 NG AFM Procedures 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event One engine inoperative minimum FLAPS UP 76 KIAS control speed (air) v FLAPS APP 73 KIAS One engine inoperative speed for 85 KIAS best rate of climb v 3.1.3 SELECTING EMERGENCY FREQUENCY...
Page 96 Emergency DA 42 NG AFM Procedures 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.
Page 97 Emergency DA 42 NG AFM Procedures 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).
Page 98 Emergency DA 42 NG AFM Procedures 3.2.3 L/R OIL TEMP Left / Right engine oil temperature is in the upper red L/R OIL TEMP 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.
Page 99 Emergency DA 42 NG AFM Procedures 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).
Page 100 Emergency DA 42 NG AFM Procedures 3.2.4 L/R OIL PRES If G1000 system software prior to P/N 010-00670-06 is installed: Left / Right engine oil pressure is in the lower red L/R OIL PRES range (too low / <1.5 bar).
Page 101 Emergency DA 42 NG AFM Procedures 3.2.5 L/R GBOX TEMP Left / Right engine gearbox temperature is in the L/R GBOX TEMP 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.
Page 102 Emergency DA 42 NG AFM Procedures 3.2.6 L/R FUEL TEMP Left / Right fuel temperature is in the upper red range L/R FUEL TEMP (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.
Page 103 Emergency DA 42 NG AFM Procedures 3.2.7 L/R FUEL PRESS Left / Right engine fuel pressure is low. L/R FUEL PRESS 1. Fuel quantity ......check 2.
Page 104 Emergency DA 42 NG AFM Procedures 3.2.8 L/R ALTN AMPS Left / Right engine alternator output is in the upper red L/R ALTN AMPS range (too high / above 70 Amps). Proceed according to: 3.10.2 - HIGH CURRENT 3.2.9 L/R ENG FIRE L/R ENG FIRE Left / Right engine fire detected.
Page 105 Emergency DA 42 NG AFM Procedures 3.2.10 L/R STARTER Left / Right engine starter is engaged. L/R STARTER Proceed according to: 3.10.3 - STARTER MALFUNCTION 3.2.11 DOOR OPEN Front and/or rear canopy and/or baggage door are/is DOOR OPEN not closed and locked.
Page 106 Emergency DA 42 NG AFM Procedures 3.3 AIRPLANE-RELATED G1000 CAUTIONS 3.3.1 L/R ALTN FAIL Left / Right engine alternator has failed. L/R ALTN FAIL (a) One Alternator Failed Proceed according to: 4B.4.6 - L/R ALTN FAIL (b) Both Alternators Failed...
Page 107 Emergency DA 42 NG AFM Procedures 3.4 G1000 SYSTEM WARNINGS 3.4.1 RED X / YELLOW X A red or yellow X through any display field, such as COM frequencies, NAV frequencies, or engine data, indicates that display field is not receiving valid data.
Page 108 Emergency DA 42 NG AFM Procedures 3.4.5 VERT SPEED FAIL The display system is not receiving vertical speed VERT SPEED FAIL input from the air data computer; accompanied by a red or yellow X through the vertical speed display. Determine vertical speed based on the change of altitude information.
Page 109 Emergency DA 42 NG AFM Procedures 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...
Page 110 Emergency DA 42 NG AFM Procedures (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.
Page 111 Emergency DA 42 NG AFM Procedures 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.
Page 112 Emergency DA 42 NG AFM Procedures 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.
Page 113 Emergency DA 42 NG AFM Procedures 3.6 ABNORMAL ENGINE BEHAVIOUR 1. Full power ......apply If the abnormal engine behavior sustains, refer to 3.7 - ONE ENGINE INOPERATIVE...
Page 114 Emergency DA 42 NG AFM Procedures 3.7 ONE ENGINE INOPERATIVE PROCEDURES WARNING In certain combinations of airplane weight, configuration, ambient conditions, speed and pilot skill, negative climb performance result. Refer Chapter 5 - PERFORMANCE for one engine inoperative performance data.
Page 115 Emergency DA 42 NG AFM Procedures 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.
Page 116 Emergency DA 42 NG AFM Procedures 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.
Page 117 Emergency DA 42 NG AFM Procedures WARNING Do not increase the POWER lever past the propeller speed of 1975 RPM or the setting determined in step 4. An increase of engine power beyond this setting leads into another power loss.
Page 118 Emergency DA 42 NG AFM Procedures 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.
Page 119 Emergency DA 42 NG AFM Procedures 3.7.3 ENGINE SECURING (FEATHERING) PROCEDURE Shut down and feathering of the affected engine: 1. Affected engine ..... . . identify & verify 2.
Page 120 Emergency DA 42 NG AFM Procedures 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...
Page 121 Emergency DA 42 NG AFM Procedures 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.
Page 122 Emergency DA 42 NG AFM Procedures Restarting the Engine by Windmilling If the reason for the shutdown has been ascertained and there is no indication of malfunction or engine fire a restart may be attempted. Maximum restart altitude: 18,000 ft pressure altitude for immediate restart.
Page 123 Emergency DA 42 NG AFM Procedures NOTE Below 125 KIAS it is possible that the propeller may not windmill continuously. Continuous windmilling is required for a successful restart. Above 145 KIAS a restart can overspeed the propeller. 1. POWER lever of affected engine ..IDLE 2.
Page 124 Emergency DA 42 NG AFM Procedures 3.7.5 ENGINE FAILURE DURING TAKE-OFF a) Engine Failure During Ground Roll - Abort take-off. 1. POWER lever ......IDLE / BOTH 2.
Page 125 Emergency DA 42 NG AFM Procedures b) Engine Failure After Lift Off If the landing gear is still extended and the remaining runway / surface is adequate: - Abort the take-off and land straight ahead. If the remaining runway / surface is inadequate: - Decide whether to abort or to continue the take-off.
Page 126 Emergency DA 42 NG AFM Procedures 6. Inoperative engine ..... secure according to 3.7.3 - ENGINE SECURING (FEATHERING) PROCEDURE Land as soon as possible according to 3.7.7 - LANDING WITH ONE ENGINE INOPERATIVE.
Page 127 Emergency DA 42 NG AFM Procedures 3.7.6 ENGINE FAILURES IN FLIGHT (a) Engine Failure During Initial Climb WARNING As the climb is a flight condition which is associated with high power settings, airspeeds lower than v = 76 KIAS (flaps UP) or 73 KIAS (flaps APP) should be avoided as a sudden engine failure can lead to loss of control.
Page 128 Emergency DA 42 NG AFM Procedures (b) Engine Failure During Flight 1. Rudder ......maintain directional control 2.
Page 129 Emergency DA 42 NG AFM Procedures 3.7.7 LANDING WITH ONE ENGINE INOPERATIVE Preparation: 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...
Page 130 Emergency DA 42 NG AFM Procedures Inoperative engine: 7. Engine ......check secured (feathered) according to 3.7.3 - ENGINE...
Page 131 Emergency DA 42 NG AFM Procedures 14. POWER lever ......as required 15. Trim ....... as required / directional trim to...
Page 132 Emergency DA 42 NG AFM Procedures If the approach to land is not successful you may consider: 3.7.8 GO-AROUND / BALKED LANDING WITH ONE ENGINE INOPERATIVE CAUTION The go-around / balked landing is not recommended to be initiated below a minimum of 800 ft above ground.
Page 133 Emergency DA 42 NG AFM Procedures If a positive rate of climb cannot be established: - Land so as to keep clear of obstacles. If time allows the following steps can reduce the risk of fire in an event of collision with obstacles after touchdown: 6.
Page 134 Emergency DA 42 NG AFM Procedures If landing with landing gear extended: 10. LANDING GEAR ..... . DOWN, check 3 green 11.
Page 135 Emergency DA 42 NG AFM Procedures 3.7.9 FLIGHT WITH ONE ENGINE INOPERATIVE CAUTION Even if a positive flight performance can be established with one engine inoperative, land as soon as possible at the next suitable airfield / airport. CAUTION Prolonged operation with excessive side slip/bank angle may cause fuel starvation, which is normally advised by LOW FUEL indication on the G1000.
Page 136 Emergency DA 42 NG AFM Procedures CAUTION Switching the fuel pump to ON in combination with CROSSFEED may cause damage to the high-pressure pump. NOTE If the FUEL SELECTOR is set on CROSSFEED, the engine will be supplied with fuel from the main tank on the opposite side.
Page 137 Emergency DA 42 NG AFM Procedures 3.8 ENGINES OUT LANDING 1. ENGINE MASTER ....both OFF 2. Alternator switches ....both OFF 3.
Page 138 Emergency DA 42 NG AFM Procedures If landing with landing gear extended: 9. LANDING GEAR ..... . DOWN, check 3 green 10.
Page 139 Emergency DA 42 NG AFM Procedures 3.9 LANDING GEAR SYSTEM FAILURES 3.9.1 LANDING GEAR UNSAFE WARNING NOTE The landing gear unsafe warning light illuminates if the landing gear is neither in the final up or down & locked position. Illumination of this light is therefore normal during transit.
Page 140 Emergency DA 42 NG AFM Procedures NOTE If the landing gear cannot be retracted to the final up position you may continue the flight with the landing gear extended in the down & locked position. Consider for higher aerodynamic drag, resulting in degraded flight performance, increased fuel consumption and decreased range.
Page 141 Emergency DA 42 NG AFM Procedures 3.9.2 MANUAL EXTENSION OF THE LANDING GEAR NOTE In case of a failure of the electrical pump, which is driving the landing gear actuators, the landing gear can be extended manually at speeds up to 152 KIAS. The manual extension of the landing gear may take up to 20 seconds.
Page 142 Emergency DA 42 NG AFM Procedures 7. Gear indicator lights ....check 3 green lights NOTE If the landing gear is correctly extended and locked, as indicated by the 3 green lights, the red light is illuminated additionally if the GEAR circuit breaker is pulled.
Page 143 Emergency DA 42 NG AFM Procedures 3.9.3 LANDING WITH GEAR UP NOTE This procedure applies if the landing gear is completely retracted. 1. Approach ......with power at normal approach airspeeds and flap settings 2.
Page 144 Emergency DA 42 NG AFM Procedures 3.9.4 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR CAUTION A defective (e.g. burst) tire is not usually easy to detect. The damage normally occurs during take-off or landing, and is hardly noticeable during fast taxiing. It is only during the roll- out after landing or at lower taxiing speeds that a tendency to swerve occurs.
Page 145 Emergency DA 42 NG AFM Procedures 3.9.5 LANDING WITH DEFECTIVE BRAKES Consider the greater rolling distance. 1. Safety harness ..... . . check fastened and tightened...
Page 146 Emergency DA 42 NG AFM Procedures 3.10 FAILURES IN THE ELECTRICAL SYSTEM 3.10.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM 1. Circuit breakers ..... . . check if all OK (pressed in) If there is still no electrical power available: 2.
Page 147 Emergency DA 42 NG AFM Procedures 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 3.10.2 HIGH CURRENT If high current is indicated on the G1000: 1.
Page 148 Emergency DA 42 NG AFM Procedures 3.11 SMOKE AND FIRE NOTE The cabin hand fire extinguisher is located inside the airplane passenger compartment on the RH side of the cabin floor behind the co-pilot seat. To release the fire extinguisher bottle out of the bracket, it is necessary to catch the bottle at the agent-outlet nozzle near the Y-spring.
Page 149 Emergency DA 42 NG AFM Procedures 3.11.2 ENGINE FIRE DURING TAKE-OFF 1. Cabin heat & Defrost ....OFF CAUTION In case of extreme smoke development, the front canopy may be unlatched during flight.
Page 150 Emergency DA 42 NG AFM Procedures 3.11.3 ENGINE FIRE IN FLIGHT 1. Cabin heat & Defrost ....OFF CAUTION In case of extreme smoke development, the front canopy may be unlatched during flight.
Page 151 Emergency DA 42 NG AFM Procedures 3.11.4 ELECTRICAL FIRE ON GROUND 1. ELECT. MASTER ..... OFF If the engine is running: 2.
Page 152 Emergency DA 42 NG AFM Procedures 3.11.5 ELECTRICAL FIRE IN FLIGHT 1. EMERGENCY SWITCH ....ON 2. AVIONIC MASTER ....OFF 3.
Page 153 Emergency DA 42 NG AFM Procedures 3.12 OTHER EMERGENCIES 3.12.1 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN Carbon monoxide (CO) is a gas which is developed during the combustion process. It is poisonous and without smell. Increased concentration of carbon monoxide gas can be fatal.
Page 154 Emergency DA 42 NG AFM Procedures 3.12.2 UNLOCKED DOORS 1. Airspeed ......reduce immediately 2.
Page 155 Emergency DA 42 NG AFM Procedures Front Baggage Door Open 5. Airspeed ......reduce, so that door is in a stable position 6.
Page 156 Emergency DA 42 NG AFM Procedures 3.12.3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM 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.
Page 157 Emergency DA 42 NG AFM Procedures (b) Propeller Overspeed NOTE This procedure applies for continued propeller overspeed due to a malfunction in the propeller constant speed unit or a engine control unit malfunction. 1. POWER setting ..... . reduce as required If the problem does not clear: 2.
Page 158 Emergency DA 42 NG AFM Procedures (c) Fixed RPM 1. POWER setting ..... . . change If the problem does not clear: 2.
Page 159 Emergency DA 42 NG AFM Procedures 3.12.4 UNINTENTIONAL FLIGHT INTO ICING 1. Leave the icing area (by changing altitude or turning back, in order to reach zones with a higher ambient temperature). 2. PITOT HEAT ......ON 3.
Page 160 Emergency DA 42 NG AFM Procedures 3.12.5 FUEL SUPPLY FAILURE 1. FUEL SELECTOR ....CROSSFEED / affected engine WARNING In case of a fuel supply failure a fuel pump inspection is required prior to the next flight.
Page 161 Emergency DA 42 NG AFM Procedures 3.12.6 RECOVERY FROM AN UNINTENTIONAL SPIN CAUTION Spin recovery has NOT been shown during certification as it is NOT required for this airplane category. The given recovery method is based on general experience! CAUTION Intentional spins are prohibited in this airplane.
Page 162 Emergency DA 42 NG AFM Procedures When rotation has stopped: 6. Rudder ......neutral 7.
Page 163 Emergency DA 42 NG AFM Procedures 3.12.7 EMERGENCY DESCENT 1. FLAPS ......UP 2.
Page 164 Emergency DA 42 NG AFM Procedures 3.12.9 AUTOPILOT OR ELECTRIC TRIM MALFUNCTION / FAILURE NOTE An autopilot or electric trim malfunction may be recognized by an unexpected deviation from the desired flight path, abnormal flight control or trim wheel movement, or flight director commands which cause unexpected or contradictory information on the other cockpit displays.
Page 165 Emergency DA 42 NG AFM Procedures NOTE Accomplish items 1 and 2 simultaneously! 1. Airplane control stick ....grasp firmly and regain airplane control 2.
Page 166 Emergency DA 42 NG AFM Procedures Intentionally left blank. Page 3 - 76 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 167 Normal Operating DA 42 NG AFM Procedures CHAPTER 4A NORMAL OPERATING PROCEDURES Page 4A.1 INTRODUCTION ........4A-3 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES .
Page 168 Normal Operating DA 42 NG AFM Procedures 4A.6.13 AFTER LANDING ......4A-61 4A.6.14 SHUT-DOWN .
Page 169 Guide, P/N 190-00963-( ) and the Garmin G1000 Pilot’s Guide for the Diamond DA 42 NG, P/N 190-00962-( ). If MÄM 42-978 is installed, normal operating procedures for GFC 700 are described in the Garmin G1000 NXi Cockpit Reference Guide, P/N 190-02238-( ) and the Garmin G1000 NXi Pilot’s Guide...
Page 170 Normal Operating DA 42 NG AFM Procedures 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES FLAPS up to 1900 kg above 1900 kg (4189 lb) (4189 lb) Airspeed for rotation (take-off run, min. 80 KIAS min. 80 KIAS min. 76 KIAS min. 76 KIAS Airspeed for take-off climb min.
Page 171 Normal Operating DA 42 NG AFM Procedures 4A.3 ADVISORY ALERTS ON THE G1000 The G1000 provides the following advisory-alerts on the PFD in the alert area: 4A.3.1 ADVISORY/GENERAL White color coded text. CHARACTERISTICS 4A.3.2 L/R GLOW ON L/R GLOW ON Left / Right engine glow plug active.
Page 172 Procedures 4A.4 FLIGHT CHARACTERISTICS The DA 42 NG is to be flown with "the feet on the pedals“, meaning that coordinated flight in all phases and configurations shall be supported by dedicated use of the rudder and ailerons together. With the landing gear extended and at aft CG-locations, with flaps up and full power...
Page 173 Normal Operating DA 42 NG AFM Procedures 4A.6 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4A.6.1 PRE-FLIGHT INSPECTION I. Cabin Check Preparation: a) Parking brake ......set ON b) MET, NAV, mass and balance .
Page 174 Normal Operating DA 42 NG AFM Procedures Below Instrument Panel in Front of Right Seat: a) ALTERNATE AIR ..... check CLOSED On the Instrument Panel: a) ALTERNATOR .
Page 175 Normal Operating DA 42 NG AFM Procedures Check Procedure: a) ELECT. MASTER ..... ON CAUTION When switching the ELECT. MASTER ON, the electrically driven hydraulic gear pump may activate itself for 5 to 20 seconds in order to restore the system pressure.
Page 176 Normal Operating DA 42 NG AFM Procedures f) Gear warning / fire detector TEST BUTTON ... . . PUSH, check fire detection warning and aural alert and CHECK GEAR caution...
Page 177 Normal Operating DA 42 NG AFM Procedures ELECT. MASTER ..... OFF m) Flight controls ......check free and correct movement up to full deflection n) Trims .
Page 178 Normal Operating DA 42 NG AFM Procedures II. Walk-Around Check, Visual Inspection CAUTION A visual inspection means: examination for damage, cracks, delamination, excessive play, load transmission, correct attachment and general condition. In addition control surfaces should be checked for freedom of movement.
Page 179 Normal Operating DA 42 NG AFM Procedures 2. Left Engine Nacelle: a) 3 air inlets / 2 air outlets ....clear b) Engine oil level ..... . . check dipstick (inspection hole in the upper cowling) c) Gearbox oil level .
Page 180 Normal Operating DA 42 NG AFM Procedures Nacelle underside ..... check for excessive contamination particularly by oil, fuel, and other fluids k) Auxiliary tank vent outlet on lower surface (if installed) .
Page 181 Normal Operating DA 42 NG AFM Procedures Tie-down ......check, clear m) Aileron and linkage ....visual inspection n) Aileron hinges and safety pin .
Page 182 Normal Operating DA 42 NG AFM Procedures 6. Fuselage, Right Side: a) Fuselage skin ......visual inspection b) Rear window .
Page 183 Normal Operating DA 42 NG AFM Procedures e) Openings on lower surface ....check for foreign objects and for traces of fuel (if tank is full, fuel...
Page 184 Normal Operating DA 42 NG AFM Procedures 9. Right Engine Nacelle: a) 3 air inlets / 2 air outlets ....clear b) Engine oil level ..... . . check dipstick (inspection hole in the upper cowling) c) Gearbox oil level .
Page 185 Normal Operating DA 42 NG AFM Procedures Nacelle underside ..... check for excessive contamination particularly by oil, fuel, and other fluids k) Auxiliary tank vent outlet on lower surface (if installed) .
Page 186 Normal Operating DA 42 NG AFM Procedures k) OAT sensor ......check EPU connector ..... . . check m) Tow bar .
Page 187 Normal Operating DA 42 NG AFM Procedures 4A.6.2 BEFORE STARTING ENGINE 1. Preflight inspection ....complete 2. Passengers ......instructed...
Page 188 Normal Operating DA 42 NG AFM Procedures NOTE The pilot must ensure that a passenger sitting on a front seat is instructed in the operation of the adjustable backrest (if installed). 5. Adjustable backrests (if installed) ..adjust to the upright...
Page 189 Normal Operating DA 42 NG AFM Procedures 16. G1000 ......wait until power-up completed.
Page 190 Normal Operating DA 42 NG AFM Procedures 4A.6.3 STARTING ENGINE NOTE At ambient temperatures below -22°C the engine may not start at the first attempt. In this case wait 60 seconds between the start attempts. 1. Strobe lights (ACL) ....ON 2.
Page 191 Normal Operating DA 42 NG AFM Procedures CAUTION Do not overheat the starter motor. Do not operate the starter motor for more than 10 seconds. At ambient temperatures below -22°C it is possible that the engine will not start at the first attempt. In this case wait 60 seconds between the start attempts.
Page 192 Normal Operating DA 42 NG AFM Procedures 4A.6.4 BEFORE TAXIING 1. Power lever ......as required, max. 50% if engine temperature below green range.
Page 193 Normal Operating DA 42 NG AFM Procedures NOTE The AFCS system automatically conducts a preflight self-test upon initial power application. The preflight test is indicated by a white boxed PFT on the PFD. Upon successful completion of the preflight test, the PFT is removed, the red AFCS annunciation is removed, and the autopilot disconnect tone sounds.
Page 194 Normal Operating DA 42 NG AFM Procedures 4A.6.5 TAXIING 1. Parking brake ......release 2. Brakes ......test on moving off 3.
Page 195 Normal Operating DA 42 NG AFM Procedures 4A.6.6 BEFORE TAKE-OFF 1. Position airplane into wind if possible. 2. Parking brake ......set...
Page 196 Normal Operating DA 42 NG AFM Procedures 9. Annunciations / Engine / System Page ..check OK / normal range (except oil pressure may be in the yellow range with a warm engine and power lever set to IDLE) 10.
Page 197 Normal Operating DA 42 NG AFM Procedures ECU / fuel pumps test sequence: CAUTION If the L/R ECU A/B FAIL indicators do not illuminate during the test sequence there is a malfunction in the engine control system. Terminate flight preparation.
Page 198 Normal Operating DA 42 NG AFM Procedures 1. Power lever ......IDLE 2. Propeller RPM ......check below 1000 RPM 3.
Page 199 Normal Operating DA 42 NG AFM Procedures 8. ECU TEST button ..... release NOTE By switching between ECU A and B the two independent electrical fuel pumps are switched over as well.
Page 200 Normal Operating DA 42 NG AFM Procedures Available Power Check: 1. POWER lever ......MAX for 10 seconds 2.
Page 201 Normal Operating DA 42 NG AFM Procedures 4A.6.7 TAKE-OFF Standard Procedure (Take-Off with Flaps UP) 1. Transponder ......as required 2.
Page 202 Normal Operating DA 42 NG AFM Procedures When safe climb is established: 7. LANDING GEAR ..... . apply brakes; UP,...
Page 203 Normal Operating DA 42 NG AFM Procedures NOTE In strong crosswinds steering can be augmented by use of the toe brakes. It should be noted, however, that this method increases the take-off roll, and should not generally be used. 6. Nose wheel lift-off ..... 76 KIAS 7.
Page 204 Normal Operating DA 42 NG AFM Procedures 4A.6.8 CLIMB Initial Climb Check 1. Landing light ......OFF / as required 2.
Page 205 Normal Operating DA 42 NG AFM Procedures GFC 700 Operation During Climb NOTE The NOSE UP and NOSE DN buttons on the mode controller on the MFD are referenced to airplane movement. The NOSE UP button will increase the reference pitch attitude, increase the reference vertical speed and decrease the reference airspeed.
Page 206 Normal Operating DA 42 NG AFM Procedures b) Flight Level Change (FLC) 1. Altitude preselect ..... . set to desired altitude 2.
Page 207 Normal Operating DA 42 NG AFM Procedures c) To Capture a Selected Altitude 1. Altimeter setting ..... . adjust to appropriate value 2.
Page 208 Normal Operating DA 42 NG AFM Procedures d) Navigation Capture and Track: 1. Navigation source ..... select VOR or GPS using CDI button on PFD 2.
Page 209 Normal Operating DA 42 NG AFM Procedures 4A.6.9 CRUISE 1. POWER lever ......up to 92% or maximum...
Page 210 Normal Operating DA 42 NG AFM Procedures 2. Transfer the second half of the auxiliary fuel: Repeat the procedure described above. NOTE Transfer the fuel from the auxiliary tanks to the main tanks as soon as possible. The fuel in the auxiliary tanks must be transferred to the main tanks to become available for the current flight mission.
Page 211 Normal Operating DA 42 NG AFM Procedures NOTE If the altitude preselect is not changed before selecting VS, the autopilot may re-capture the current altitude immediately after entering VS mode. Always ensure that the altitude preselect is adjusted prior to selecting VS.
Page 212 Normal Operating DA 42 NG AFM Procedures NOTE If the altitude preselect is not changed before selecting FLC, the autopilot may re-capture the current altitude immediately after entering FLC mode. Always ensure that the altitude preselect is adjusted prior to selecting FLC.
Page 213 Normal Operating DA 42 NG AFM Procedures NOTE In ALT mode, the autopilot will maintain the reference altitude shown in the autopilot window of the PFD regardless of the altitude in the altitude preselect window or the altimeter's barometric pressure setting. If the altimeter setting is changed, the autopilot will climb or descend to maintain the reference altitude.
Page 214 Normal Operating DA 42 NG AFM Procedures e) Navigation Capture and Track: 1. Navigation source ..... select VOR or GPS using CDI button on PFD 2.
Page 215 Normal Operating DA 42 NG AFM Procedures 4A.6.10 DESCENT 1. POWER lever ......as required 2. Airspeed ......as required 3.
Page 216 Normal Operating DA 42 NG AFM Procedures NOTE If the altitude preselect is not changed before selecting VS, the autopilot may re-capture the current altitude immediately after entering VS mode. Always ensure that the altitude preselect is adjusted prior to selecting VS.
Page 217 Normal Operating DA 42 NG AFM Procedures NOTE If the altitude preselect is not changed before selecting FLC, the autopilot may re-capture the current altitude immediately after entering FLC mode. Always ensure that the altitude preselect is adjusted prior to selecting FLC.
Page 218 Normal Operating DA 42 NG AFM Procedures NOTE In ALT mode, the autopilot will maintain the reference altitude shown in the autopilot window of the PFD regardless of the altitude in the altitude preselect window or the altimeter's barometric pressure setting. If the altimeter setting is changed, the autopilot will climb or descend to maintain the reference altitude.
Page 219 Normal Operating DA 42 NG AFM Procedures 4A.6.11 APPROACH & LANDING Approach: CAUTION For landing the adjustable backrests (if installed) must be fixed in the upright position. 1. Adjustable backrests (if installed) ..adjust to the upright...
Page 220 Normal Operating DA 42 NG AFM Procedures Before Landing: 12. Airspeed Up to 1900 kg (4189 lb) ....min. 86 KIAS with FLAPS UP min.
Page 221 Normal Operating DA 42 NG AFM Procedures GFC 700 Operation During Approach and Landing a) VOR 1. Navigation source ..... select VOR using CDI button on PFD 2.
Page 222 Normal Operating DA 42 NG AFM Procedures b) ILS 1. Navigation source ..... select LOC using CDI button on PFD 2.
Page 223 Normal Operating DA 42 NG AFM Procedures c) GPS 1. Navigation source ..... select GPS using CDI button on PFD 2.
Page 224 Normal Operating DA 42 NG AFM Procedures NOTE The course pointer must be at least 115° from the current magnetic heading before BC will be annunciated in the lateral mode field. Until that point, LOC will be annunciated. Selecting NAV mode for back course approaches inhibits the glideslope from coupling.
Page 225 Normal Operating DA 42 NG AFM Procedures 4A.6.12 GO AROUND 1. POWER lever ......MAX 2. FLAPS ......position APP 3.
Page 226 Normal Operating DA 42 NG AFM Procedures 3. Balked landing ......execute 4. Missed approach procedure ... . . execute (as applicable) 5.
Page 227 Normal Operating DA 42 NG AFM Procedures 4A.6.13 AFTER LANDING 1. POWER lever ..... . . IDLE 2. Brakes ......as required 3.
Page 228 Normal Operating DA 42 NG AFM Procedures 4A.6.14 SHUT-DOWN 1. Parking brake ......set 2. POWER lever ......1 minute at max. 10 % load 3.
Page 229 Normal Operating DA 42 NG AFM Procedures 4A.6.15 EXIT AIRPLANE Exit the airplane to the aft on designated areas on the inner wing section LH or RH. 4A.6.16 POST FLIGHT INSPECTION 1. Record any problem found in flight and during the post-flight check in the log book.
Page 230 Normal Operating DA 42 NG AFM Procedures 4A.6.18 OPERATION IN RAIN, SNOW OR VISIBLE MOISTURE 1. ALTERNATE AIR ..... OPEN...
Page 231 Normal Operating DA 42 NG AFM Procedures 4A.6.19 REFUELING CAUTION Before refueling, the airplane must be connected to electrical ground. Grounding points: exhaust, left and right. Refer to Section 2.14 - FUEL for approved fuel grades. Use of Fuel Additives...
Page 232 Normal Operating DA 42 NG AFM Procedures Typical Dosing Quantities: (a) KATHON FP 1.5 Fuel Quantity Fuel Additive * Liter US gal 13.2 40.2 88.68 0.13 26.4 80.4 177.37 0.26 39.6 120.6 266.05 11.6 0.39 52.8 160.8 354.73 15.5 0.52 79.3...
Page 233 Normal Operating DA 42 NG AFM Procedures (c) PRIST Hi-Flash Fuel Quantity Fuel Additive *,** PRIST Hi-Flash (1500 ppm) Liter US gal 13.2 40.2 88.68 58.9 1.99 26.4 80.4 177.37 117.9 3.99 39.6 120.6 266.05 176.8 5.98 52.8 160.8 354.73 235.8...
Page 234 Normal Operating DA 42 NG AFM Procedures 4A.6.20 FLIGHT AT HIGH ALTITUDE At high altitudes the provision of oxygen for the occupants is necessary. Legal requirements for the provision of oxygen should be adhered to. Refer to Section 2.11 - OPERATING ALTITUDE for more information.
Page 235 Normal Operating DA 42 NG AFM Procedures 1. Altitude ......stabilize in level flight at an...
Page 236 Normal Operating DA 42 NG AFM Procedures CAUTION After the engine has started, the POWER lever should be set to a moderate power setting until engine temperature have reached the green range. 6. Circuit breakers ..... . . check / reset if necessary...
Page 237 Abnormal Operating DA 42 NG AFM Procedures CHAPTER 4B ABNORMAL OPERATING PROCEDURES Page 4B.1 PRECAUTIONARY LANDING ......4B-3 4B.2 CANOPY IN COOLING GAP POSITION .
Page 238 Abnormal Operating DA 42 NG AFM Procedures 4B.4.11 STICK LIMIT ....... . . 4B-25 4B.4.12 CHECK GEAR .
Page 239 Abnormal Operating DA 42 NG AFM Procedures 4B.1 PRECAUTIONARY LANDING NOTE A landing of this type is only necessary when there is a reasonable suspicion that due to operational factors such as fuel shortage, weather conditions, etc. the possibility of endangering the airplane and its occupants by continuing the flight cannot be excluded.
Page 240 Abnormal Operating DA 42 NG AFM Procedures CAUTION If sufficient time is remaining, the risk of fire in the event of a collision with obstacles can be reduced as follows after a safe touch-down: ENGINE MASTER ..both OFF FUEL SELECTOR .
Page 241 Abnormal Operating DA 42 NG AFM Procedures 4B.2 CANOPY IN COOLING GAP POSITION CAUTION If take-off was inadvertently done with the canopy in the cooling gap position, do not attempt to close the canopy in flight. Land the airplane and close the canopy on ground.
Page 242 Abnormal Operating DA 42 NG AFM Procedures 4B.3.2 COOLANT TEMPERATURE (a) High Coolant Temperature Proceed according to: 3.2.2 - L/R ENG TEMP (b) Low Coolant Temperature Check G1000 for L/R COOL LVL caution message (low coolant level) NOTE During an extended descent from high altitudes with a low power setting coolant temperature may decrease.
Page 243 Abnormal Operating DA 42 NG AFM Procedures 4B.3.3 OIL TEMPERATURE (a) High Oil Temperature Proceed according to: 3.2.3 - L/R OIL TEMP (b) Low Oil Temperature NOTE During an extended descent from high altitudes with a low power setting oil temperature may decrease. In this case an increase in power can help.
Page 244 Abnormal Operating DA 42 NG AFM Procedures 4B.3.4 OIL PRESSURE (a) High Oil Pressure Check oil temperature. Check coolant temperature. If the Temperatures are within the Green Range: Expect false oil pressure indication. Keep monitoring temperatures. If the Temperatures are outside of the Green Range: Reduce power on affected engine.
Page 245 Abnormal Operating DA 42 NG AFM Procedures 4B.3.5 GEARBOX TEMPERATURE High Gearbox Temperature Proceed according to: 3.2.5 - L/R GBOX TEMP 4B.3.6 FUEL TEMPERATURE (a) High Fuel Temperature Proceed according to: 3.2.6 - L/R FUEL TEMP (b) Low Fuel Temperature Increase power on affected engine.
Page 246 Abnormal Operating DA 42 NG AFM Procedures 4B.3.7 VOLTAGE (a) Low Voltage Indication on the Ground with Engines Running 1. ALTERNATORS ..... . check ON 2.
Page 247 Abnormal Operating DA 42 NG AFM Procedures 4B.4 CAUTION-ALERTS ON THE G1000 The G1000 provides the following CAUTION-alerts on the PFD in the ALERT area. 4B.4.1 CAUTIONS / GENERAL CHARACTERISTICS * Amber color coded text. * Single warning chime tone of 1.5 seconds duration.
Page 248 Abnormal Operating DA 42 NG AFM Procedures 4B.4.2 L/R ECU A FAIL L/R ECU A FAIL * Left / Right engine ECU A has failed * is being tested during ECU test procedure before take-off check. Depending on the type of failure, the ECU failure cautions are either ‘non latched', i.e.
Page 249 Abnormal Operating DA 42 NG AFM Procedures (b) ECU A Caution During Flight NOTE In case of a failure in the electronic ECU (Engine Control Unit) A the system automatically switches to ECU B. 1. ALTERNATE AIR ..... OPEN 2.
Page 250 Abnormal Operating DA 42 NG AFM Procedures 6. VOTER switch ......ECU A 7. Wait ....... . 5 seconds 8.
Page 251 Abnormal Operating DA 42 NG AFM Procedures 4B.4.3 L/R ECU B FAIL * Left / Right engine ECU B has failed L/R ECU B FAIL * is being tested during ECU test procedure before take-off check. Depending on the type of failure, the ECU failure cautions are either ‘non latched', i.e.
Page 252 Abnormal Operating DA 42 NG AFM Procedures (b) ECU B Caution During Flight NOTE In case of a failure in the electronic ECU (Engine Control Unit) B the system automatically switches to ECU A. 1. ALTERNATE AIR ..... OPEN 2.
Page 253 Abnormal Operating DA 42 NG AFM Procedures 7. Wait ....... 5 seconds 8.
Page 254 Abnormal Operating DA 42 NG AFM Procedures 4B.4.4 L/R FUEL LOW Left / Right engine main tank fuel quantity is low. L/R FUEL LOW 1. Fuel quantity ......check...
Page 255 Abnormal Operating DA 42 NG AFM Procedures 4B.4.5 LOW VOLTAGE CAUTION (LOW VOLTS) Left / Right engine bus voltage is too low (less than L/R VOLTS LOW 25 Volts). Possible reasons are: - A fault in the power supply. - ALTERNATORS off.
Page 256 Abnormal Operating DA 42 NG AFM Procedures 4B.4.6 L/R ALTN FAIL Left / Right engine alternator has failed. L/R ALTN FAIL NOTE A L/R ALTN FAIL annunciation may be temporarily triggered during ground operation with low engine power settings. This indicates no system malfunction.
Page 257 Abnormal Operating DA 42 NG AFM Procedures 4B.4.7 L/R COOL LVL Left / Right engine coolant level is low. L/R COOL LVL A low coolant caution alert may indicate a loss of coolant. This will subsequently lead to decreased engine cooling capability / loss of engine power due to engine failure.
Page 258 Abnormal Operating DA 42 NG AFM Procedures 4B.4.8 PITOT FAIL / HT OFF Pitot heating system has failed. PITOT FAIL PITOT HT OFF Pitot heating system is OFF. 1. PITOT HEAT ......check ON / as required...
Page 259 Abnormal Operating DA 42 NG AFM Procedures 4B.4.9 STALL HT FAIL / OFF Stall warning heat has failed. STAL HT FAIL STAL HT OFF Stall warning heat is OFF. 1. PITOT HEAT ......check ON / as required...
Page 260 Abnormal Operating DA 42 NG AFM Procedures 4B.4.10 L/R AUXILIARY FUEL TANK EMPTY (if installed) Left / Right auxiliary fuel tank empty (displayed only L/R AUX FUEL E when AUX PUMP switch is ON). The auxiliary tank empty caution message indicates an empty auxiliary fuel tank while the aux.
Page 261 Abnormal Operating DA 42 NG AFM Procedures 4B.4.11 STICK LIMIT Control stick limiting system (variable elevator stop) has STICK LIMIT failed. The variable elevator backstop is activated depending on the position of the power levers. The system has two failure modes which can be identified as follows:...
Page 262 Abnormal Operating DA 42 NG AFM Procedures 4B.4.12 CHECK GEAR Landing gear is not down and locked. CHECK GEAR 1. Landing gear ......down / as required...
Page 263 Abnormal Operating DA 42 NG AFM Procedures 4B.4.13 LOI GPS integrity is insufficient for the current phase of flight. (a) Enroute, Oceanic, Terminal, or Initial Approach Phase of Flight If the LOI annunciation is displayed in the enroute, oceanic, terminal, or initial approach...
Page 264 Abnormal Operating DA 42 NG AFM Procedures 4B.5 FAILURES IN FLAP OPERATING SYSTEM Failure in Position Indication or Function 1. FLAPS position ..... . . check visually 2.
Page 265 Abnormal Operating DA 42 NG AFM Procedures (c) Only LDG available: Perform normal landing. END OF CHECKLIST 4B.6 FAILURES IN ELECTRICAL RUDDER PEDAL ADJUSTMENT Runaway of Electrical Rudder Pedal Adjustment (Optional Equipment, OÄM 42-070) NOTE The circuit breaker for the rudder pedal adjustment is located below the related switch, on the rear wall of the leg room.
Page 266 Abnormal Operating DA 42 NG AFM Procedures 4B.7 FAILURES IN HYDRAULIC SYSTEM 4B.7.1 CONTINUOUS HYDRAULIC PUMP OPERATION 1. Landing gear indication lights ... . check 2. Prepare for manual landing gear extension. Refer to Section 3.9.2 - MANUAL EXTENSION OF THE LANDING GEAR.
Page 267 Abnormal Operating DA 42 NG AFM Procedures 4B.7.2 HYDRAULIC PUMP FAILURE 1. Landing gear indication lights ... . check 2. Prepare for manual landing gear extension. Refer to Section 3.9.2 - MANUAL EXTENSION OF THE LANDING GEAR.
Page 268 Abnormal Operating DA 42 NG AFM Procedures 4B.8 STARTING ENGINE WITH EXTERNAL POWER 4B.8.1 BEFORE STARTING ENGINE 1. Pre-flight inspection ....complete 2.
Page 269 Abnormal Operating DA 42 NG AFM Procedures 5. Adjustable backrests (if installed) ..adjust to the upright position described by a placard on the roll-over bar and verify proper fixation 6. Rudder pedals ..... . . adjusted; if manual pedal...
Page 270 Abnormal Operating DA 42 NG AFM Procedures NOTE When switching the External Power Unit ON, all electrical equipment connected to the LH and RH main buses is powered. 19. G1000 ......wait until power-up completed.
Page 271 Abnormal Operating DA 42 NG AFM Procedures 4B.8.2 STARTING ENGINE 1. Strobe lights (ACL) ....ON 2. ELECT. MASTER ..... ON 3.
Page 272 Abnormal Operating DA 42 NG AFM Procedures CAUTION Do not overheat the starter motor. Do not operate the starter motor for more than 10 seconds. At ambient temperatures below -20°C it is possible that the engine will not run at the first attempt. In this case wait 60 seconds between the start attempts.
Page 273 Abnormal Operating DA 42 NG AFM Procedures 4B.9 LIGHTNING STRIKE 1. Airspeed ......as low as practicable, do not exceed v (refer to Section 2.2)
Page 274 Abnormal Operating DA 42 NG AFM Procedures 4B.10 FAILURES IN THE AUTOPILOT SYSTEM 4B.10.1 AUTOPILOT DISCONNECT (yellow AP flashing on PFD) 1. AP DISC switch ..... . . DEPRESS AND RELEASE (to cancel disconnect tone) 2.
Page 275 Abnormal Operating DA 42 NG AFM Procedures 4B.10.2 AUTOPILOT OVERSPEED RECOVERY (yellow MAXSPD on PFD) 1. POWER lever ......reduce power When overspeed condition is corrected: 2.
Page 276 Abnormal Operating DA 42 NG AFM Procedures 4B.10.3 LOSS OF NAVIGATION INFORMATION (Yellow VOR, VAPP, GPS or LOC flashing on PFD) NOTE If a navigation signal is lost while the autopilot is tracking it, the autopilot will roll the airplane wings level and default to roll mode (ROL).
Page 277 Abnormal Operating DA 42 NG AFM Procedures 4B.10.4 AUTOPILOT OUT OF TRIM (Yellow 7AIL, 6AIL, 8ELE, 9ELE, 7RUD or 6RUD on PFD) For 8ELE, or 9ELE Indication: WARNING Do not attempt to overpower the autopilot in the event of a pitch mistrim.
Page 278 Abnormal Operating DA 42 NG AFM Procedures 2. Airplane attitude ..... . . maintain / regain airplane control, use standby attitude indicator if necessary 3.
Page 279 Abnormal Operating DA 42 NG AFM Procedures For 6AIL, 7AIL or 6RUD, 7RUD Indication: 1. Rudder trim ......VERIFY slip / skid indicator is...
Page 280 Abnormal Operating DA 42 NG AFM Procedures 4B.10.5 FLASHING YELLOW MODE ANNUNCIATION NOTE Abnormal mode transitions (those not initiated by the pilot or by normal sequencing of the autopilot) will be annunciated by flashing the disengaged mode in yellow on the PFD. Upon loss of a selected mode, the system will revert to the default mode for the affected axis, either ROL or PIT.
Page 281 Abnormal Operating DA 42 NG AFM Procedures 4B.10.6 EFFECTS OF G1000 LOSSES UPON AUTOPILOT OPERATION G1000 System Loss Effect upon Autopilot Operation AHRS The autopilot disconnects and autopilot, yaw damper and flight director are inoperative. Manual electric trim is available.
Page 282 Abnormal Operating DA 42 NG AFM Procedures 4B.11 L/R AUX FUEL TRANSFER FAIL (IF AUX. TANKS ARE INSTALLED) If the fuel quantity in a main tank does not increase during fuel transfer: 1. Switch OFF both AUX PUMPS. 2. Check fuel pump LH/RH OFF.
Page 283 DA 42 NG AFM Performance CHAPTER 5 PERFORMANCE Page INTRODUCTION ........5-2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS .
Page 284 Performance DA 42 NG AFM 5.1 INTRODUCTION The performance tables and diagrams on the following pages are presented so that, on the one hand, you can see what performance you can expect from your airplane, while on the other hand they allow comprehensive and sufficiently accurate flight planning. The...
Page 285 DA 42 NG AFM Performance 5.3 PERFORMANCE TABLES AND DIAGRAMS 5.3.1 AIRSPEED CALIBRATION NOTE The position of the landing gear (extended/retracted) has no significant influence on the airspeed indicator system. Airspeed Indicator Calibration Indicated Calibrated Airspeed [KCAS] Airspeed [KIAS] at Various Flap Settings...
Page 286 Performance DA 42 NG AFM 5.3.2 FUEL FLOW CAUTION The table shows the fuel flow per hour for one engine. NOTE The fuel calculations on the FUEL CALC portion of the G1000 MFD do not use the airplane's fuel quantity indicators. The...
Page 287 DA 42 NG AFM Performance 5.3.3 INTERNATIONAL STANDARD ATMOSPHERE Doc. No. 7.01.15-E Rev. 7 02-Oct-2017 Page 5 - 5...
Page 288 Performance DA 42 NG AFM 5.3.4 STALLING SPEEDS Stalling Speeds at Various Flight Masses Airspeeds, most forward CG, power off: Bank Angle 1510 kg (3329 lb) 0° 30° 45° 60° Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS...
Page 289 DA 42 NG AFM Performance 1999 kg Bank Angle (4407 lb) 0° 30° 45° 60° Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS DOWN DOWN NOTE KIAS values may not be accurate at stall. Doc. No. 7.01.15-E Rev. 7...
Page 290 Performance DA 42 NG AFM 5.3.5 WIND COMPONENTS Flight Direction 32° 0° 10° 20° 30° 40° 50° 60° 70° 80° 90° 100° 110° 180° 160° 130° 120° Crosswind Component [kts] Example: Flight direction 360° Wind 32°/30 kts Result: Crosswind component 16 kts Max.
Page 291 DA 42 NG AFM Performance 5.3.6 TAKE-OFF DISTANCE Conditions: - Power lever ......both MAX - Flaps ......UP or APP - Runway .
Page 292 Performance DA 42 NG AFM WARNING For a safe take-off the available runway length must be at least equal to the take-off distance over a 50 ft (15 m) obstacle. WARNING Poor maintenance condition of the airplane, deviation from the given procedures, uneven runway, as well as...
Page 293 DA 42 NG AFM Performance Take-Off Distance - Normal Procedure - 1999 kg / 4407 lb Weight: 1999 kg / 4407 lb Flaps: 80 KIAS Power: 85 KIAS Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press. Alt.
Page 294 Performance DA 42 NG AFM Take-Off Distance - Normal Procedure - 1900 kg / 4189 lb Weight: 1900 kg / 4189 lb Flaps: 80 KIAS Power: 85 KIAS Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press. Alt.
Page 295 DA 42 NG AFM Performance Take-Off Distance - Normal Procedure - 1700 kg / 3748 lb Weight: 1700 kg / 3748 lb Flaps: 80 KIAS Power: 85 KIAS Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press. Alt.
Page 296 Performance DA 42 NG AFM Take-Off Distance - Short Field Procedure - 1999 kg / 4407 lb Weight: 1999 kg / 4407 lb Flaps: 76 KIAS Power: 82 KIAS Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
Page 297 DA 42 NG AFM Performance Take-Off Distance - Short Field Procedure - 1900 kg / 4189 lb Weight: 1900 kg / 4189 lb Flaps: 76 KIAS Power: 82 KIAS Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
Page 298 Performance DA 42 NG AFM Take-Off Distance - Short Field Procedure - 1700 kg / 3748 lb Weight: 1700 kg / 3748 lb Flaps: 76 KIAS Power: 82 KIAS Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
Page 299 DA 42 NG AFM Performance 5.3.7 CLIMB PERFORMANCE (ALL ENGINES OPERATING) Conditions: - Power lever ......both 92% - Flaps .
Page 300 Performance DA 42 NG AFM All Engines Operating Climb - Flaps UP Flaps: UP Power: 92% 92 KIAS (above 1900 kg / 4189 lb) 90 KIAS (up to 1900 kg / 4189 lb) Gear: retracted Rate of Climb - [ft/min] Press.
Page 301 DA 42 NG AFM Performance All Engines Operating Climb - Flaps UP Flaps: UP Power: 92% 92 KIAS (above 1900 kg / 4189 lb) 90 KIAS (up to 1900 kg / 4189 lb) Gear: retracted Rate of Climb - [ft/min] Press.
Page 302 Performance DA 42 NG AFM All Engines Operating Climb - Flaps APP Flaps: APP Power: 92% 85 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 2000 1219 4000...
Page 303 DA 42 NG AFM Performance All Engines Operating Climb - Flaps APP Flaps: APP Power: 92% 85 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 1260 1240 1230...
Page 304 Performance DA 42 NG AFM 5.3.8 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE Conditions: - Remaining engine ....92% load - Dead engine ......feathered and secured - Flaps .
Page 305 DA 42 NG AFM Performance One Engine Inoperative Climb Flaps: UP Power: feathered / 92% 85 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 2000 4000 1219 6000...
Page 306 Performance DA 42 NG AFM One Engine Inoperative Climb Flaps: UP Power: feathered / 92% 85 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 2000 4000 1219 6000...
Page 307 DA 42 NG AFM Performance 5.3.9 TIME, FUEL AND DISTANCE TO CLIMB Conditions: - Power lever ......both 92% - Flaps .
Page 308 Performance DA 42 NG AFM Time, Fuel and Distance to Climb Flaps: UP Power: 92% 92 KIAS (above 1900 kg / 4189 lb) 90 KIAS (up to 1900 kg / 4189 lb) Gear: retracted Press. Press. Dist- Alt. Alt. Time...
Page 309 DA 42 NG AFM Performance Time, Fuel and Distance to Climb Flaps: UP Power: 92% 92 KIAS (above 1900 kg / 4189 lb) 90 KIAS (up to 1900 kg / 4189 lb) Gear: retracted Press. Press. Dist- Alt. Alt. Time...
Page 310 Performance DA 42 NG AFM 5.3.10 CRUISE PERFORMANCE Conditions: - Flaps ......UP - Landing gear .
Page 311 DA 42 NG AFM Performance Cruise Performance Outside Air Temperature - [°C] ISA-10 ISA+10 ISA+20 ISA+30 Press. Alt. [ft] / [m] [kt] [kt] [kt] [kt] [kt] gal/h] gal/h] gal/h] gal/h] gal/h] 92 16.5 164 92 16.5 92 16.5 92 16.5 89 15.9...
Page 312 Performance DA 42 NG AFM Cruise Performance Outside Air Temperature - [°C] ISA-10 ISA+10 ISA+20 ISA+30 Press. Alt. [ft] / [m] [kt] [kt] [kt] [kt] [kt] gal/h] gal/h] gal/h] gal/h] gal/h] 170 79 92 16.5 92 16.5 90 16.1 14.8 13.8...
Page 313 DA 42 NG AFM Performance 5.3.11 LANDING DISTANCES Conditions: - Power lever ......both IDLE - Flaps ......LDG, APP or UP - Runway .
Page 314 Performance DA 42 NG AFM WARNING For a safe landing the available runway length must be at least equal to the landing distance over a 50 ft (15 m) obstacle. WARNING Poor maintenance condition of the airplane, deviation from the given procedures, uneven runway, as well as...
Page 315 DA 42 NG AFM Performance Landing Distance - Flaps LDG - 1999 kg / 4407 lb Weight: 1999 kg / 4407 lb Flaps: 86 KIAS Power: IDLE Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press. Alt.
Page 316 Performance DA 42 NG AFM Landing Distance - Flaps LDG - 1900 kg / 4189 lb Weight: 1900 kg / 4189 lb Flaps: 84 KIAS Power: IDLE Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press. Alt.
Page 317 DA 42 NG AFM Performance Landing Distance - Flaps LDG - 1700 kg / 3748 lb Weight: 1700 kg / 3748 lb Flaps: 84 KIAS Power: IDLE Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press. Alt.
Page 318 Performance DA 42 NG AFM Landing Distance - Abnormal Flap Position - 1999 kg / 4407 lb Weight: 1999 kg / 4407 lb Flaps: APP or UP 92 KIAS Power: IDLE Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
Page 319 DA 42 NG AFM Performance Landing Distance - Abnormal Flap Position - 1900 kg / 4189 lb Weight: 1900 kg / 4189 lb Flaps: APP or UP 86 KIAS Power: IDLE Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
Page 320 Performance DA 42 NG AFM Landing Distance - Abnormal Flap Position - 1700 kg / 3748 lb Weight: 1700 kg / 3748 lb Flaps: APP or UP 86 KIAS Power: IDLE Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
Page 321 DA 42 NG AFM Performance 5.3.12 GO-AROUND CLIMB PERFORMANCE Conditions: - Power lever ......both MAX - Flaps .
Page 322 Performance DA 42 NG AFM Go-Around Climb Performance Flaps: LDG Power: MAX : 86 KIAS above 1900 kg (4189 lb) Gear: extended 84 KIAS up to 1900 kg (4189 lb) Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt.
Page 323 DA 42 NG AFM Performance 5.3.13 APPROVED NOISE DATA Max. Flight Mass 1900 kg (4189 lb) ICAO Annex 16 Chapter X, App.6 ..78.0 dB(A) If MÄM 42-678 is carried out: Max. Flight Mass 1999 kg (4407 lb) ICAO Annex 16 Chapter X, App.6 .
Page 324 Performance DA 42 NG AFM Intentionally left blank. Page 5 - 42 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 325 DA 42 NG AFM Mass & Balance CHAPTER 6 MASS AND BALANCE Page INTRODUCTION ........6-2 DATUM PLANE .
Page 326 Mass & Balance DA 42 NG AFM 6.1 INTRODUCTION In order to achieve the performance and flight characteristics described in this Airplane Flight Manual and for safe flight operation, the airplane must be operated within the permissible mass and balance envelope.
Page 327 DA 42 NG AFM Mass & Balance NOTE Refer to Section 1.6 - UNITS OF MEASUREMENT for conversion of SI units to US units and vice versa. NOTE The mass of the winter kit - ventilation is negligible. The mass and balance data of the airplane therefore remain unchanged.
Page 328 Mass & Balance DA 42 NG AFM 6.3 MASS AND BALANCE REPORT The empty mass and the corresponding CG position established before delivery are the first entries in the Mass and Balance Report. Every change in permanently installed equipment, and every repair to the airplane which affects the empty mass or the empty mass CG must be recorded in the Mass and Balance Report.
Page 330 DA 42 NG AFM Mass & Balance MASS AND BALANCE REPORT Doc. No. 7.01.15-E Rev. 7 02-Oct-2017 Page 6 - 5...
Page 331 DA 42 NG AFM 6.4 FLIGHT MASS AND CENTER OF GRAVITY The following information enables you to operate your DA 42 NG within the permissible mass and balance limits. For the calculation of the flight mass and the corresponding CG position the following tables and diagrams are required: 6.4.1 - MOMENT ARMS...
Page 332 DA 42 NG AFM Mass & Balance CAUTION If the auxiliary tanks are in use, both tanks must be refueled to the maximum level to provide proper information for the pilot about the fuel quantity in the auxiliary fuel tanks.
Page 333 Mass & Balance DA 42 NG AFM 6.4.1 MOMENT ARMS The most important lever arms aft of the Datum Plane: Lever Arm Item [in] Occupants on front seats 2.30 90.6 Occupants on rear seats 3.25 128.0 in main tanks 2.63 103.5...
Page 334 DA 42 NG AFM Mass & Balance Lever Arm Item [in] Standard: Nose 0.60 23.6 Cabin 3.89 153.1 Baggage in Extension 4.54 178.7 compartments If OÄM 42-207 is carried out: Standard baggage 3.65 143.7 compartment Short extension 3.97 156.3 Doc. No. 7.01.15-E Rev.
Page 335 Mass & Balance DA 42 NG AFM 6.4.2 LOADING DIAGRAM Page 6 - 10 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 336 DA 42 NG AFM Mass & Balance 6.4.3 CALCULATION OF LOADING CONDITION NOTE If the optional de-icing system OÄM 42-160 is installed, the following must be observed: The consumption of fuel causes a forward movement of the CG. The consumption of the de-icing fluid causes a rearward movement of the CG (if only OÄM 42-160 is installed) or a...
Page 337 Mass & Balance DA 42 NG AFM DA 42 NG Your DA 42 NG (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 1. Empty mass (from Mass 1450 3488.0 and Balance Report)
Page 338 DA 42 NG AFM Mass & Balance DA 42 NG Your DA 42 NG (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 10. De-Icing fluid (if OÄM 42-160 AND OÄM 42-203 are installed;...
Page 339 Mass & Balance DA 42 NG AFM 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE Page 6 - 14 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 340 DA 42 NG AFM Mass & Balance The flight CG position must be within the following limits: Most forward flight CG: 2.350 m (92.52 in) aft of datum plane at 1450 kg (3197 lb) 2.350 m (92.52 in) aft of datum plane at 1468 kg (3236 lb) 2.418 m (95.20 in) aft of datum plane at max.
Page 341 Mass & Balance DA 42 NG AFM 6.4.5 PERMISSIBLE MOMENT RANGE The flight mass moments shown in the diagram are those from the example in Table 6.4.3 - CALCULATION OF LOADING CONDITION, rows 11 and 14. Page 6 - 16 Rev.
Page 342 DA 42 NG AFM Mass & Balance 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY All equipment that is approved for installation in the DA 42 NG is shown in the Equipment List below. NOTE The equipment listed below cannot be installed in any arbitrary combination.
Page 360 DA 42 NG AFM Airplane Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Page INTRODUCTION ........7-3 AIRFRAME .
Page 361 Airplane Description DA 42 NG AFM 7.12 STALL WARNING SYSTEM ......7-71 7.13...
Page 362 DA 42 NG AFM Airplane Description 7.1 INTRODUCTION Chapter 7 contains a description of the airplane and its systems, together with operating instructions. For details about optional equipment see Chapter 9. 7.2 AIRFRAME Fuselage The CFRP fuselage is of semi monocoque molded construction. The center wing is attached to the fuselage with bolts.
Page 363 Airplane Description DA 42 NG AFM 7.3 FLIGHT CONTROLS The ailerons, elevator and wing flaps are operated through control rods, while the rudder is controlled by cables. The flaps are electrically operated. Elevator forces can be balanced by a trim tab on the elevator, which is operated by a Bowden cable. Rudder forces can be balanced by a trim tab on the rudder, which is also operated by a Bowden cable.
Page 364 DA 42 NG AFM Airplane Description Flaps The flaps are a two piece construction. The inner part of the flap is mounted to the center wing and the outer part to the wing. Both parts are connected to each other with a form fit connection.
Page 365 Airplane Description DA 42 NG AFM The flaps are operated by means of a 3-position flap selector switch on the instrument panel. The positions of the switch correspond to the positions of the flaps, the Cruise position of the switch being at the top. If the switch is moved to another position, the flaps continue to travel automatically until they have reached the position selected on the switch.
Page 366 Variable Elevator Stop: The DA 42 NG is equipped with an electrically operated actuator that limits the elevator-up travel to 13° as soon as the power setting of both engines exceeds approximately 20 % (approach power setting). This is 2.5° less than the 15.5° full deflection.
Page 367 Airplane Description DA 42 NG AFM Rudder Construction: GFRP sandwich. Hinges: Upper hinge: One bolt. Lower hinge: Bearing bracket including rudder stops, held by 4 screws to the rear web of the vertical stabilizer. The mating part on the rudder is a bracket which is attached to the rudder by 2 bolts.
Page 368 DA 42 NG AFM Airplane Description Pedal Adjustment NOTE The pedals may only be adjusted on the ground! The pedals are unlocked by pulling the black handle which is located behind the rear attachment. Forward Adjustment: Whilst keeping the handle pulled, push the pedals forward with your feet. Release the handle and allow the pedals to lock into place.
Page 369 Airplane Description DA 42 NG AFM Electrical Pedal Adjustment (Optional Equipment, OÄM 42-070) NOTE The pedals may only be adjusted on the ground! The pedals are adjusted using a rocker switch, located on the rear wall of the leg room.
Page 370 DA 42 NG AFM Airplane Description 7.4 INSTRUMENT PANEL 18, 20 Optional if OÄM 42-270 is installed Optional if OÄM 42-288 is installed 27 12 14 5 3 4 3 1 2 13 Doc. No. 7.01.15-E Rev. 7 02-Oct-2017 Page 7 - 11...
Page 371 Airplane Description DA 42 NG AFM Major Instruments and Controls Electric master switch 17 Circuit breakers* Avionic master switch 18 Backup airspeed indicator Engine master switches 19 Backup artificial horizon Start switch 20 Backup altimeter Pitot-/Stall warning heat switch 21 Emergency compass...
Page 372 DA 42 NG AFM Airplane Description NOTE The figure on previous page shows the typical DA 42 NG installation position for the equipment. The actual installation may vary due to the approved equipment version. Cockpit Ventilation Ventilation in the front is provided by spherical ventilation nozzles (16) in the instrument panel.
Page 373 Airplane Description DA 42 NG AFM 7.5 LANDING GEAR The landing gear is a fully retractable, hydraulically operated, tricycle landing gear. Struts for the landing gear are air oil assemblies. The hydraulic pressure for the landing gear operation is provided by an electrically powered hydraulic pump, which is activated by a pressure switch, when the required pressure is too low.
Page 374 DA 42 NG AFM Airplane Description To test the gear warning system (refer to 4A.6.1 - PRE-FLIGHT INSPECTION) push the test button close by the gear selector switch. The aural gear alert should appear. CAUTION If the aural alert does not appear, an unscheduled maintenance is necessary.
Page 375 Hydraulic Gear Extension System Schematic The main landing gear of the DA 42 NG is extended with three hydraulic cylinders. The following schematic figures show the system conditions for each operating mode. The figure below shows the extension of the landing gear.
Page 376 DA 42 NG AFM Airplane Description The figure below shows the system status when the landing gear is extended. All hydraulic cylinders are under high pressure. The operating mode for the retraction of the landing gear is shown in the next figure. While...
Page 377 Airplane Description DA 42 NG AFM While the landing gear is retracted both valves are energized and excessive hydraulic fluid on one side is drained into the tank. This configuration of the system is shown in the following figure. For an emergency extension of the landing gear, the hydraulic fluid can pass through an emergency extension valve so that the gear is extended by gravity.
Page 378 DA 42 NG AFM Airplane Description Wheel Brakes Hydraulically operated disk brakes act on the wheels of the main landing gear. The wheel brakes are individually operated by means of toe pedals. Parking Brake The lever is located on the small center console under the instrument panel and is in the upper position when the brakes are released.
Page 379 Airplane Description DA 42 NG AFM 7.6 SEATS AND SAFETY HARNESSES To increase passive safety, the seats are constructed using a carbon fiber/Kevlar hybrid material and GFRP. The seats are removable to allow maintenance and inspection of the underlying controls. Covers on the control sticks prevent loose objects from falling into the area of the controls.
Page 380 DA 42 NG AFM Airplane Description CAUTION Don not apply a load of more than 90 daN (202lbf) tot the top of the backrest. Otherwise damage of the adjustment mechanism may result. For adjustment lift the backrest lever or press the button and bend the backrest forward or backward to the desired backrest angle.
Page 381 Airplane Description DA 42 NG AFM If seats with adjustable backrests are installed (OÄM 42-067): Lumbar Support Inboard Hinge Lamella Package Friction Adjustment Screw Seat Lever Outboard Hinge Lumbar Support Lever Page 7 - 22 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 382 DA 42 NG AFM Airplane Description If seats with adjustable backrest are installed (OÄM 42-259): Lumbar Support Inboard Hinge Bowden Cable Outboard Hinge Lumbar Support Lever Release Button Doc. No. 7.01.15-E Rev. 7 02-Oct-2017 Page 7 - 23...
Page 383 Airplane Description DA 42 NG AFM 7.7 BAGGAGE COMPARTMENT There are two baggage compartments. One is located in the nose section and it is accessible through two compartment doors. The other baggage compartment is behind the seat backs of the rear seats. As an option a short baggage extension (OÄM 42-207) may be installed.
Page 384 DA 42 NG AFM Airplane Description WARNING The airplane may be operated with the front canopy in the “cooling gap” position on the ground only. Before take-off the front canopy must be completely closed and locked. Do not block the front canopy with the locking key before flight in order to assure emergency evacuation from outside.
Page 385 Airplane Description DA 42 NG AFM Heating and Ventilation Heating and ventilation are operated using two levers located on the small center console under the instrument panel. Right lever: = HEATING ON (seats, floor) down = HEATING OFF Center lever :...
Page 386 DA 42 NG AFM Airplane Description Emergency Axe If OÄM 42-205 is incorporated an emergency axe is installed on the floor panel under the co-pilot’s seat (see Figure below). If the canopy can not be opened in case of an emergency use the emergency axe to break through the canopy.
Page 387 Airplane Description DA 42 NG AFM Emergency Egress Hammer If OÄM 42-304 is incorporated an emergency egress hammer is installed on the floor panel under the co-pilot’s seat. If the canopy can not be opened in case of an emergency use the emergency egress hammer to break through the canopy.
Page 388 DA 42 NG AFM Airplane Description 7.9 POWER PLANT 7.9.1 ENGINES, GENERAL There are two Austro Engine E4-B engines installed, which have the following specifications: - Liquid-cooled four-cylinder four-stroke engine with wet sump lubrication - Inline construction. - Common rail direct injection.
Page 389 Airplane Description DA 42 NG AFM 7.9.2 PROPELLER Two mt-Propeller MTV-6-R-C-F / CF 187-129 hydraulically regulated 3-bladed constant speed feathering propellers are installed. Each propeller has wood composite blades with fiber-reinforced plastic coating and stainless steel edge cladding; in the region of the propeller hub the leading edge is coated with adhesive PU foil.
Page 390 DA 42 NG AFM Airplane Description Pressure Accumulator: The pressure accumulator is a nitrogen oil type. It is connected to the gearbox oil circuit via an electric valve at the accumulator, which is operated with the ENGINE MASTER switch. When the ENGINE MASTER switch is set to ON the valve is opened. When the engine is running, the accumulator is filled with oil at a pressure of approximately 22 bar (320 PSI).
Page 391 Airplane Description DA 42 NG AFM Unfeathering: To unfeather the propeller, the associated ENGINE MASTER switch must be set to ON. This will open the electric valve at the pressure accumulator. The pressure stored in the accumulator will move the propeller blades into a low pitch position. As soon as the propeller starts turning and the gearbox oil operates, the accumulator will be refilled.
Page 392 DA 42 NG AFM Airplane Description 7.9.3 OPERATING CONTROLS Power Lever Engine performance is controlled by a power lever for each engine. Both power levers are situated on the large center console. ‘Front’ and ‘rear’ are defined in relation to the direction of flight.
Page 393 Airplane Description DA 42 NG AFM 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. WARNING It is possible that the propeller blades remain in the position of highest pitch in case of a malfunction of the engine control unit.
Page 394 DA 42 NG AFM Airplane Description ECU VOTER There are two VOTER switches, one for each engine. For normal operation both switches are set to AUTO. Each engine is controlled by either ECU A or ECU B. In case of a failure of the active electronic engine control unit (ECU) there should be an automatic switch-over to the other ECU.
Page 395 Airplane Description DA 42 NG AFM Alternate Air In the event of power loss because of icing or blocking of the air filter, there is the possibility of drawing air from the engine compartment. The ALTERNATE AIR operating lever which serves both engines simultaneously is located under the instrument panel to the right of the center console.
Page 396 DA 42 NG AFM Airplane Description 7.9.4 ENGINE INSTRUMENTS The engine instruments are displayed on the Garmin G1000 MFD. Also refer to Section 7.13.3 - MULTI FUNCTION DISPLAY (MFD). Indications for the LH engine are on the left side, indications for the RH engine are on the right side.
Page 397 Airplane Description DA 42 NG AFM Display when pushing the ENGINE button (if MÄM 42-978 is installed): Page 7 - 38 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 398 G1000 MFD to show the different display modes. The pictured engine instrument markings may not stringently agree with the current engine limitations of the DA 42 NG. NOTE The fuel calculations on the FUEL CALC portion do not use the airplane's fuel quantity indicators.
Page 399 Airplane Description DA 42 NG AFM 7.9.5 FUEL SYSTEM General Page 7 - 40 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 400 DA 42 NG AFM Airplane Description Fuel is stored in the tanks which are located in the wings. Normally fuel for the right engine is taken from the right wing main tank and for the left engine from the left wing main tank.
Page 401 Airplane Description DA 42 NG AFM NOTE By switching between ECU A and B the two independent electrical fuel pumps are switched over as well. In case of an emergency both pumps can be activated simultaneously by using the fuel pump switch.
Page 402 DA 42 NG AFM Airplane Description CAUTION Do not shut down an engine with the fuel selector valve. The high pressure fuel pump can be damaged. CAUTION Switching on the fuel pump in combination with CROSSFEED may cause damage to the high-pressure pump.
Page 403 Airplane Description DA 42 NG AFM Scheme of the Fuel Selector Valve Positions: Possible operating modes of the three fuel selector valve positions are outlined systematically in the following scheme. The figures below show fuel flows for the RH engine (fuel flows LH are alike):...
Page 404 DA 42 NG AFM Airplane Description With the LH fuel selector valve in crossfeed position, the fuel from the RH tank is transferred to the LH engine. Depending on the position of the RH fuel selector valve, the RH tank then feeds both engines (as shown in figure 4 below) or only the LH engine, when the fuel selector valve of the RH engine is in shut-off position (as shown in figure 5 below).
Page 405 Airplane Description DA 42 NG AFM Main Fuel Tanks Each tank consists of three aluminum chambers which are connected by a flexible hose. The tank is filled through a filler in the outboard fuel chamber. Only four liters (1 US gal) of fuel in each wing are unusable, so that a total quantity of 96 liters (25.4 US gal) in each...
Page 406 DA 42 NG AFM Airplane Description Auxiliary Fuel Tanks (if installed) The auxiliary fuel tanks are optional equipment (OÄM 42-056). Description The auxiliary fuel tanks are installed in the rear section of the engine nacelles, above the wing main spars. Each auxiliary fuel tank has a filler cap located on the top surface of the nacelle.
Page 407 Airplane Description DA 42 NG AFM When one auxiliary pump is defective, the fuel stored in the related auxiliary fuel tank is not available. For use of the remaining fuel pump refer to to Section 4B.12 - L/R FUEL TRANSFER FAIL. The flight plan must be amended accordingly.
Page 408 DA 42 NG AFM Airplane Description Alternate Means for Fuel Quantity Indication for the Fuel Tank: The alternate means for fuel quantity indication allows the fuel quantity in the tank to be determined during the preflight inspection. It functions according to the principle of communicating containers.
Page 409 Airplane Description DA 42 NG AFM Fuel Temperature Max. fuel temperature: 60 °C (140 °F) Fuel Grade Approved fuel grades are listed in Section 2.14 - FUEL. NOTE In order to provide information about the fuel grade it is recommended to enter the fuel grade in the airplane log each time fuel is refilled.
Page 410 DA 42 NG AFM Airplane Description 7.9.6 COOLING SYSTEM Each engine is liquid cooled. The liquid cooling system consists of a radiator (coolant heat exchange) and a bypass to this radiator. The bypass is in operation when coolant temperatures are low. It therefore allows the engine to warm-up quickly. Upon reaching a certain temperature (approximately 88 °C or 190 °F) the radiator is activated by a...
Page 411 Airplane Description DA 42 NG AFM 7.9.7 OIL SYSTEMS Each engine has two separate oil systems. Lubrication System (Engine and Turbo-Charger) The engine lubrication is a wet sump lubrication system. The oil is cooled by a water/oil-cooler on the upperside of the engine.
Page 412 DA 42 NG AFM Airplane Description 7.9.8 TURBO-CHARGER SYSTEM engine air inlet intercooler filter box turbine air filter alternate air valve engine charger alternate air inlet waste gate exhaust The exhaust system contains a manifold which collects exhaust gases from the outlets of the cylinders and feeds them to the turbine of the turbo charger.
Page 413 DA 42 NG AFM 7.9.9 FIRE DETECTION SYSTEM The fire detection system in the DA 42 NG consists of an overheat detector in the hot area of each engine. In case of an increase of the engine compartment temperature above 250 °C (480 °F) the overheat detector closes the electric circuit and a warning message...
Page 414 DA 42 NG AFM Airplane Description 7.10 ELECTRICAL SYSTEM If MÄM 42-403 is not carried out: Doc. No. 7.01.15-E Rev. 7 02-Oct-2017 Page 7 - 55...
Page 415 Airplane Description DA 42 NG AFM If MÄM 42-403 is carried out: Page 7 - 56 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 416 DA 42 NG AFM Airplane Description 7.10.1 GENERAL The DA 42 NG has 28 Volt DC system, which can be sub-divided into: - Power generation - Storage - Distribution - Consumers Power Generation Power generation is provided by two 70 Ampère alternators (generators) which are mounted on the bottom left side of each engine.
Page 417 Airplane Description DA 42 NG AFM Alternator Control: Each alternator has an alternator control unit. It measures the alternator output voltage and controls the current through the alternator field coils via a pulse-width modulated signal. To keep the output voltage stable in all load and speed situations, the alternator field signal is modulated accordingly.
Page 418 DA 42 NG AFM Airplane Description Distribution Electrical power is distributed via the HOT BATTERY BUS, the BATTERY BUS, the LH (RH) ECU BUS, the LH (RH) MAIN BUS, and the AVIONIC BUS. HOT BATTERY BUS: The HOT BATTERY BUS is directly connected to the main battery and cannot be disconnected from the main battery.
Page 419 Airplane Description DA 42 NG AFM Additionally, each ECU B and its fuel pump is supplied with electrical power from the opposite engine side ECU BUS via a diode and fuse. The LH (RH) ENGINE MASTER switch must be set to ON to activate the engine EECU.
Page 420 DA 42 NG AFM Airplane Description Ammeter The ammeter displays the intensity of current which is supplied to the electrical system by the LH (RH) alternator. Landing and Taxi Lights Landing and taxi lights are built into the wing center section, and are each operated by means of a switch (LANDING, TAXI) located on the row of switches on the instrument panel.
Page 421 The PITOT HT OFF is on if the Pitot heating is switched off. External Power Socket The DA 42 NG has an external 28 Volt DC power socket located on the lower surface of the fuselage nose section. When external power is connected, the control relay is energized and the external power comes online.
Page 422 DA 42 NG AFM Airplane Description 7.10.2 ELECTRONIC ENGINE CONTROL UNIT / ECU Engine Control and Regulation The Electronic ECU is used to control the engine actuators (e.g. fuel injectors) according to the engine sensor information. The ECU monitors, controls and regulates all important parameters for engine operation.
Page 423 Airplane Description DA 42 NG AFM In accordance with the received signals and a comparison with the programmed characteristic diagrams the necessary inputs are calculated and transmitted by the following signal lines to the engine: - Signal for propeller governor pressure valve...
Page 424 DA 42 NG AFM Airplane Description 7.10.3 WARNING, CAUTION AND ADVISORY MESSAGES Crew Alerting System (CAS) The G1000 crew alerting system (CAS) is designed to provide visual and aural alerts to the flight crew. Alerts are divided into three levels as follows:...
Page 425 Airplane Description DA 42 NG AFM Alert Levels Level Text Color Importance Audible Tone Warning May require Warning chime immediate tone which repeats corrective action without delay until acknowledged by the crew May require future Single warning Caution Amber corrective action...
Page 426 DA 42 NG AFM Airplane Description Warning Alerts on the G1000 Warning Alerts Meaning / Cause The annunciation is active when the engine coolant L/R ENG TEMP temperature is greater than 105 °C. The annunciation is active when the engine oil temperature is L/R OIL TEMP greater than 140 °C.
Page 427 Airplane Description DA 42 NG AFM Warning Alerts Meaning / Cause ATTITUDE FAIL The annunciation is active when the display system is not receiving attitude reference information from the AHRS. AIRSPEED FAIL The annunciation is active when the display system is not receiving airspeed input from the air data computer.
Page 428 DA 42 NG AFM Airplane Description Caution Alerts on the G1000 Caution Alerts Meaning / Cause L/R ECU A FAIL The annunciation is active when a fault in ECU A or ECU B has occurred. L/R ECU B FAIL The annunciation is active when the fuel quantity is below L/R FUEL LOW 4 ±...
Page 429 Airplane Description DA 42 NG AFM Caution Alerts Meaning / Cause DEICE PRES HI De-icing pressure is high (if installed). DEICE PRES LO De-icing pressure is low (if installed). Annunciation Advisory Alerts on the G1000 Advisory Alerts Meaning / Cause L/R GLOW ON The annunciation is active when the glow plugs are powered.
Page 430 Pitot-static system. 7.12 STALL WARNING SYSTEM The lift detector of the DA 42 NG is located on the front edge of the left wing below the wing chord line. It is supplied electrically and provides a stall warning, before the angle of attack becomes critical.
Page 431 If MÄM 42-978 is installed, refer to the Garmin G1000 NXi Cockpit Reference Guide, P/N 190-02238-( ) and Garmin G1000 NXi Pilot's Guide for the Diamond DA 42 NG, P/N 190-02237-( ) for complete descriptions of the G1000 NXi system and operating procedures.
Page 432 DA 42 NG AFM Airplane Description NOTE During retraction and extension of the landing gear the ADF-indication may be inaccurate. 7.13.2 PRIMARY FLIGHT DISPLAY (PFD) The primary flight display (PFD; see figure below) typically displays airspeed, attitude, altitude, and heading information in a traditional format. Slip information is shown as a trapezoid under the bank pointer.
Page 433 Airplane Description DA 42 NG AFM The PFD displays the crew alerting (annunciator) system. When a warning or caution message is received, a warning or caution annunciator will flash on the PFD, accompanied by an aural tone. A warning is accompanied by a repeating tone, and a caution is accompanied by a single tone.
Page 434 DA 42 NG AFM Airplane Description Advisory messages related to G1000 system status are shown in white and are accompanied by a white flashing ADVISORY alert. Refer to the G1000 Pilot's Guide and Cockpit Reference Guide for descriptions of the messages and recommended actions (if applicable).
Page 435 Airplane Description DA 42 NG AFM 7.13.4 AUDIO PANEL The audio panel contains traditional transmitter and receiver selectors, as well as an integral intercom and marker beacon system. The marker beacon lights appear on the PFD. In addition, a clearance recorder records the last 2 ½ minutes of received audio.
Page 436 DA 42 NG AFM Airplane Description 7.14 AVIONICS 7.14.1 AUTOPILOT SYSTEM General The GFC 700 automatic flight control system (AFCS) is a 3 axis autopilot and flight director system which provides the pilot with the following features: altitude preselect and altitude hold (ALT);...
Page 437 Airplane Description DA 42 NG AFM The GFC 700 may be manually disconnected by any of the following means: - Depressing the red AP DISC button on the pilot's or co-pilot's control stick - Moving the left (outboard) side of the manual electric trim switch on the pilot's...
Page 438 HDG mode, then reselecting NAV mode. The GFC 700 automatic flight control system (AFCS) installed in the Diamond DA 42 NG consists of the following components:...
Page 439 Airplane Description DA 42 NG AFM This GDU is installed as the MFD. Servos with autopilot processing logic in the pitch, roll, yaw and pitch trim control systems Servo mounts and brackets Flight director processing logic in the GIAs Control stick-mounted manual electric trim (MET) switch (split switch) for pitch trim...
Page 440 If MÄM 42-978 is installed, refer to the Garmin G1000 NXi Cockpit Reference Guide, P/N 190-02238-( ) and Garmin G1000 NXi Pilot's Guide for the Diamond DA 42 NG, P/N 190-02237-( ) for complete descriptions of the G1000 NXi system and operating procedures.
Page 441 Airplane Description DA 42 NG AFM 7.14.2 AUTOMATIC FLIGHT CONTROL SYSTEM ANNUNCIATIONS AND ALERTS Automatic Flight Control System (AFCS) Status Alerts The following annunciations can appear on the PFD above the airspeed and attitude indicators. Only one annunciation occurs at a time, and messages are priorized by criticality.
Page 442 DA 42 NG AFM Airplane Description Caution Alerts on the Automatic Flight Control System (AFCS) Caution Alerts Meaning / Cause ELEVATOR MISTRIM UP - Pitch servo providing sustained 8ELE force in the indicated direction. ELEVATOR MISTRIM DOWN - Pitch servo providing sustained 9ELE force in the indicated direction.
Page 443 MD302 standby attitude module, shown in the Pilot’s Guide are not applicable to the DA 42 NG, due to the use of the external emergency battery. 2. The MD302 standby attitude module is not connected to an external ARINC 429 source (Garmin G1000), thus heading information and automatic BARO synchronization is not available in the DA 42 NG.
Page 444 Handling, Care, DA 42 NG AFM Maintenance CHAPTER 8 AIRPLANE HANDLING, CARE AND MAINTENANCE Page INTRODUCTION ........8-2 AIRPLANE INSPECTION INTERVALS .
Page 445 Handling, Care, DA 42 NG AFM Maintenance 8.1 INTRODUCTION Chapter 8 contains the manufacturer's recommended procedures for proper ground handling and servicing of the airplane. The Airplane Maintenance Manual (Doc. No. 7.02.15) lists certain inspection and maintenance requirements which must be followed if the airplane is to retain a new plane performance and reliability.
Page 446 Handling, Care, DA 42 NG AFM Maintenance 8.3 AIRPLANE ALTERATIONS OR REPAIRS Alterations or repairs to the airplane may be carried out only according to the Airplane Maintenance Manual, Doc. No. 7.02.15, and only by authorized personnel. 8.4 SERVICING 8.4.1 REFUELING WARNING Do not allow fire, sparks or heat near fuel.
Page 447 Handling, Care, DA 42 NG AFM Maintenance CAUTION Use only approved fuel types given in Chapter 2. 1. Ground the airplane and the fuel supply vehicle electrically. Grounding points on airplane: exhaust, left and right. 2. Remove the fuel filler cap (located on top of the outer wing). Check cap retaining cable for damage.
Page 448 Handling, Care, DA 42 NG AFM Maintenance 8.4.3 GEARBOX OIL LEVEL CHECK 1. Open the inspection door on the bottom of the upper left cowling. 2. Check gearbox oil level in inspection window by using a flashlight. 3. Close the inspection door.
Page 449 Handling, Care, DA 42 NG AFM Maintenance 8.5 GROUND HANDLING / ROAD TRANSPORT 8.5.1 GROUND HANDLING To move the airplane on ground, it can be pushed or pulled by hand on the inner section of the propeller blades near the spinner or pushed at the wing nose and at the rough surface of the center wing, inboard of the nacelles.
Page 450 Handling, Care, DA 42 NG AFM Maintenance Steering Bar or Tow Bar Attachment Doc. No. 7.01.15-E Rev. 7 02-Oct-2017 Page 8 - 7...
Page 451 Handling, Care, DA 42 NG AFM Maintenance CAUTION If the airplane is towed by a tow vehicle, do not turn the nose wheel more than 40 degrees to either side from the center position. Otherwise damage to the gear will result.
Page 452 Handling, Care, DA 42 NG AFM Maintenance 8.5.2 PARKING For short term parking, the airplane must be positioned into the wind, the parking brake must be engaged and the wing flaps must be in the retracted position. For extended and unattended parking, as well as in unpredictable wind conditions, the airplane must be anchored to the ground or placed in a hangar.
Page 453 Handling, Care, DA 42 NG AFM Maintenance Control Surfaces Gust Lock The manufacturer offers a control surfaces gust lock which can be used to block the primary controls. It is recommended that the control surfaces gust lock be used when parking outdoors, because otherwise the control surfaces can hit the stops in strong tail wind.
Page 454 Handling, Care, DA 42 NG AFM Maintenance Doc. No. 7.01.15-E Rev. 7 02-Oct-2017 Page 8 - 11...
Page 455 Handling, Care, DA 42 NG AFM Maintenance 8.5.3 MOORING Near the lower end of the tail fin of the airplane there is a hole which can be used to tie down the airplane to the ground. Also on each wing near the wing tip, an eyelet with a metric M8 thread can be installed and used as tie-down points.
Page 456 Handling, Care, DA 42 NG AFM Maintenance 8.6 CLEANING AND CARE CAUTION The airplane must be kept clean. The bright surface prevents the structure from overheating. CAUTION Excessive dirt deteriorates the flight performance. 8.6.1 PAINTED SURFACES The entire surface of the airplane is painted with a white weatherproof two component paint.
Page 457 Handling, Care, DA 42 NG AFM Maintenance 8.6.3 PROPELLER Damage and malfunctions during operation must be inspected by authorized personnel. Surface The manufacturer uses PU paint or acrylic paint which is resistant to almost any solvent. The blades may be treated with commercial automotive cleaning agents or preservatives.
Page 458 Handling, Care, DA 42 NG AFM Maintenance 8.7 GROUND DE-ICING Approved deicing fluids are: Manufacturer Name Kilfrost TKS 80 Aeroshell Compound 07 AL-5 (DTD 406B) 1. Remove any snow from the airplane using a soft brush. 2. Spray deicing fluid onto ice-covered surfaces using a suitable spray bottle.
Page 459 Handling, Care, DA 42 NG AFM Maintenance Intentionally left blank. Page 8 - 16 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...
Page 460 DA 42 NG AFM Supplements CHAPTER 9 SUPPLEMENTS Page INTRODUCTION ........9-2 LIST OF SUPPLEMENTS .
Page 461 Supplements DA 42 NG AFM 9.1 INTRODUCTION Chapter 9 contains information concerning additional (optional) equipment of the DA 42 NG. Unless otherwise stated, the procedures given in the Supplements must be applied in addition to the procedures given in the main part of the Airplane Flight Manual.
Page 462 DA 42 NG AFM Supplements 9.2 LIST OF SUPPLEMENTS Airplane S/N: Registration: Date: Sup. Rev. applicable Title Date Autopilot System KAP 140 04-Dec-2013 Bendix/King Integrated Avionics System Garmin G1000 and G1000 NXi, 31-Jan-2017 SBAS and P-RNAV Operation Electronic Stability and Protection...
Page 463 Supplements DA 42 NG AFM Airplane S/N: Registration: Date: Sup. Rev. applicable Title Date Nose Pod (STD-TC) 01-Apr-2014 Belly Pod (STD-TC) 01-Apr-2014 Operator Desk 20-Apr-2015 On Top Exhaust System 01-Apr-2014 Universal Nose 28-Nov-2016 Nose Pod 01-Apr-2014 M100 Restricted Overweight Operation...
Page 464 DA 42 NG AFM Supplements Airplane S/N: Registration: Date: Sup. Rev. applicable Title Date Ice Protection System 27-May-2015 Continuous Flow Oxygen System 10-Nov-2011 G1000 Synthetic Vision 01-Mar-2009 Technology Recirculating Cabin - Air Cooling 01-Apr-2014 Removal of Variable Elevator Stop 01-Apr-2014...
Page 465 Supplements DA 42 NG AFM Airplane S/N: Registration: Date: Sup. Rev. applicable Title Date Page 9 - 6 Rev. 7 02-Oct-2017 Doc. No. 7.01.15-E...

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