Diamond DA 42 Flight Manual

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Page 2 Introduction DA 42 AFM NOTE This airplane flight manual is valid for DA42 airplanes with a KAP 140 or no autopilot system installed. Refer to the airplane flight manual “DA42 with Garmin GFC 700 (OÄM 42-102)”, Doc. No. 7.01.06-E for airplanes with a Garmin Autopilot system installed.
Page 3 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 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: Mäm
Introduction DA 42 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 AFM Introduction Rev. Chap- Date of Date Reason Page(s) Approval Verification Signature Revision Inserted [Ing. Andreas all except certification; 1 Dec 2004 2005-196 Winkler for cover page ACG] corrections 0-3, 0-5, MÄM 42-034 [10 Feb 2005 (elevator 0-7, 0-8, 0-9 stop);...
Page 6 Introduction DA 42 AFM Rev. Chap- Date of Date Reason Page(s) Approval Verification Signature Revision Inserted 0-3 thru 0-10 1-2, 1-11 2-2, 2-4, 2-7, 2-8, 2-10, 2- 2-15, 2-18, 2-21 thru 2- 2-26, 2-27, 2- MÄM 42- 3-30, 3-31, -037, -046,...
Page 7 DA 42 AFM Introduction Rev. Chap- Date of Date Reason Page(s) Approval Verification Signature Revision Inserted MÄM 42- -174/a, -186, -198/b, -206, -240, -254, -258/a, OÄM 42- Revision No. 5 of the -055/a, AFM Doc. -056/d, 7.01.05-E is -062, -065,...
Page 8 Introduction DA 42 AFM Rev. Chap- Date of Date Reason Page(s) Approval Verification Signature Revision Inserted MÄM 42- -268/a, -270, -272, -284, -292, -301, -304, -310, -336, -347, -377, -405, -443, OÄM 42- -053/d & -054/d, Revision No. 6 of the -056/e, AFM Doc.
Page 9 DA 42 AFM Introduction Rev. Chap- Date of Date Reason Page(s) Approval Verification Signature Revision Inserted MÄM 42- -529, -542, -545/a, -546, -575, -584/a, -641, -685, -716, -756, -764/c, -814, -861, Revision No. 7 of the OÄM 42- AFM Doc.
Page 10 Introduction DA 42 AFM 0.3 LIST OF EFFECTIVE PAGE Page Date Page Date 15 Nov 2007 15-Dec-2017 0-0a 15 Nov 2007 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 1-10 15-Dec-2017 15-Dec-2017...
Page 11 DA 42 AFM Introduction Page Date Page Date appr. 2-1 15-Dec-2017 appr. 2-29 15-Dec-2017 appr. 2-2 15-Dec-2017 appr. 2-30 15-Dec-2017 appr. 2-3 15-Dec-2017 appr. 2-31 15-Dec-2017 appr. 2-4 15-Dec-2017 appr. 2-32 15-Dec-2017 appr. 2-5 15-Dec-2017 appr. 2-33 15-Dec-2017 appr. 2-6 15-Dec-2017 appr.
Page 12 Introduction DA 42 AFM Page Date Page Date 3-17 15-Dec-2017 3-46 15-Dec-2017 3-18 15-Dec-2017 3-47 15-Dec-2017 3-19 15-Dec-2017 3-48 15-Dec-2017 3-20 15-Dec-2017 3-49 15-Dec-2017 3-21 15-Dec-2017 3-50 15-Dec-2017 3-22 15-Dec-2017 3-51 15-Dec-2017 3-23 15-Dec-2017 3-52 15-Dec-2017 3-24 15-Dec-2017 3-53 15-Dec-2017...
Page 13 DA 42 AFM Introduction Page Date Page Date 4A-1 15-Dec-2017 4A-30 15-Dec-2017 4A-2 15-Dec-2017 4A-31 15-Dec-2017 4A-3 15-Dec-2017 4A-32 15-Dec-2017 4A-4 15-Dec-2017 4A-33 15-Dec-2017 4A-5 15-Dec-2017 4A-34 15-Dec-2017 4A-6 15-Dec-2017 4A-35 15-Dec-2017 4A-7 15-Dec-2017 4A-36 15-Dec-2017 4A-8 15-Dec-2017 4A-37 15-Dec-2017...
Page 14 Introduction DA 42 AFM Page Date Page Date 4B-29 15-Dec-2017 4B-1 15-Dec-2017 4B-30 15-Dec-2017 4B-2 15-Dec-2017 4B-31 15-Dec-2017 4B-3 15-Dec-2017 4B-32 15-Dec-2017 4B-4 15-Dec-2017 4B-31 15-Dec-2017 4B-5 15-Dec-2017 4B-32 15-Dec-2017 4B-6 15-Dec-2017 4B-33 15-Dec-2017 4B-7 15-Dec-2017 4B-34 15-Dec-2017 4B-8 15-Dec-2017...
Page 15 DA 42 AFM Introduction Page Date Page Date 15-Dec-2017 5-30 15-Dec-2017 15-Dec-2017 5-31 15-Dec-2017 15-Dec-2017 5-32 15-Dec-2017 15-Dec-2017 5-33 15-Dec-2017 15-Dec-2017 5-34 15-Dec-2017 15-Dec-2017 5-35 15-Dec-2017 15-Dec-2017 5-36 15-Dec-2017 15-Dec-2017 15-Dec-2017 5-10 15-Dec-2017 5-11 15-Dec-2017 5-12 15-Dec-2017 5-13 15-Dec-2017 5-14...
Page 16 Introduction DA 42 AFM Page Date Page Date 15-Dec-2017 6-30 15-Dec-2017 15-Dec-2017 6-31 15-Dec-2017 15-Dec-2017 6-32 15-Dec-2017 15-Dec-2017 6-33 15-Dec-2017 15-Dec-2017 6-34 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 15-Dec-2017 6-10 15-Dec-2017 6-11 15-Dec-2017 6-12 15-Dec-2017 6-13 15-Dec-2017 6-14 15-Dec-2017 6-15 15-Dec-2017 6-16...
Page 17 DA 42 AFM Introduction Page Date Page Date 15-Dec-2017 7-30 15-Dec-2017 15-Dec-2017 7-31 15-Dec-2017 15-Dec-2017 7-32 15-Dec-2017 15-Dec-2017 7-33 15-Dec-2017 15-Dec-2017 7-34 15-Dec-2017 15-Dec-2017 7-35 15-Dec-2017 15-Dec-2017 7-36 15-Dec-2017 15-Dec-2017 7-37 15-Dec-2017 15-Dec-2017 7-38 15-Dec-2017 7-10 15-Dec-2017 7-39 15-Dec-2017 7-11...
Page 18 Introduction DA 42 AFM Page Date Page Date 7-59 15-Dec-2017 15-Dec-2017 7-60 15-Dec-2017 15-Dec-2017 7-61 15-Dec-2017 15-Dec-2017 7-62 15-Dec-2017 15-Dec-2017 7-63 15-Dec-2017 15-Dec-2017 7-64 15-Dec-2017 15-Dec-2017 7-65 15-Dec-2017 15-Dec-2017 7-66 15-Dec-2017 15-Dec-2017 7-67 15-Dec-2017 15-Dec-2017 7-68 15-Dec-2017 8-10 15-Dec-2017 7-69...
Page 19 DA 42 AFM Introduction 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) ......... . 1 OPERATING LIMITATIONS (an approved chapter) .
Page 20 Introduction DA 42 AFM Intentionally left blank. Page 0 - 18 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 21: Table Of Contents
DA 42 AFM General CHAPTER 1 GENERAL Page INTRODUCTION ........1-2 CERTIFICATION BASIS .
Page 22: Introduction
General DA 42 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 ECU Backup Battery OÄM 42-129 9 yes 9 no Exhaust End Pipe OÄM 42-130 9 yes 9 no DA 42 M - IFR OÄM 42-141 Operator Desk 9 yes 9 no OÄM 42-158 (Full Aluminum Version) Increase of Maximum 9 yes 9 no OÄM 42-188...
Page 24 General DA 42 AFM Modification Source Installed 9 yes 9 no TAE 125-02-114 Engine OÄM 42-252/b Front Seats with Adjustable 9 yes 9 no OÄM 42-259 Backrest - Hydrolok 9 yes 9 no Emergency Egress Hammer OÄM 40-304 NOTE Mapping...
Page 25: Doc. No. 7.01.05-E Rev. 8 15-Dec
DA 42 AFM General CAUTION The DA 42 is a twin engine airplane. When the operating limitations and maintenance requirements are complied with, it has the high degree of reliability which is required by the certification basis. Nevertheless, an engine failure is not completely impossible.
Page 26: Certification Basis
General DA 42 AFM 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 27: Dimensions
DA 42 AFM General 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall Dimensions Span : 13.42 m 44.0 ft 13.55 m 44.5 ft including ACL Length 8.56 m 28 ft 1 in Height 2.49 m 8 ft 2 in...
Page 28 General DA 42 AFM Wing Flaps Area (total, left + right) 2.18 m² 23.4 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 Vertical Tail Area 2.43 m²...
Page 29: Definitions And Abbreviations
DA 42 AFM General 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 30 General DA 42 AFM Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration. Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the landing configuration.
Page 31 DA 42 AFM General Density Altitude: Altitude in ISA conditions at which the air density is equal to the current air density. Indicated Pressure Altitude: Altitude reading with altimeter set to 1,013.25 hPa (29.92 inHg). Pressure Altitude: Altitude indicated by a barometric altimeter, which is set to 1,013.25 hPa (29.92 inHg).
Page 32 General DA 42 AFM (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. Its distance from the Datum Plane is equal to the Center of Gravity Moment Arm.
Page 33 DA 42 AFM General Usable Fuel: The quantity of fuel available for flight planning. Unusable Fuel: The quantity of fuel remaining in the tank which cannot be used for flight. Useful Load: The difference between take-off mass and empty mass.
Page 34 General DA 42 AFM (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 35 DA 42 AFM General 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 Weather Radar...
Page 36 General DA 42 AFM RH ENG ECU BUS: ECU BUS RH ECU Bus ECU B RH ECU B ECU A RH ECU A (g) Equipment ELT: Emergency Locator Transmitter. (h) Design Change Advisories MÄM: Mandatory Design Change Advisory. OÄM: Optional Design Change Advisory.
Page 37: Units Of Measurement
DA 42 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 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. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 39: Conversion Chart Liters / Us Gallons
DA 42 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 31.7...
Page 40: Three-View Drawing
General DA 42 AFM 1.7 THREE-VIEW DRAWING Page 1 - 20 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 41: G1000 Avionics System
DA 42 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 General DA 42 AFM (b) The systems meets RNP5 airspace (BRNAV) requirements of AC 90-96 and in accordance with AC 20-138A, and FAA Order 8110.60 for oceanic and remote airspace operations, provided it is receiving useable navigation information from the GPS receiver. The system meets the accuracy requirements of EASA AMC 20-4 for Basic RNAV.
Page 43 The display may indicate clear areas between intense returns, but this does not necessarily mean it is safe to fly between them. As installed on the DA 42, the Garmin GWX 68 has a demonstrated range of 160 nautical miles. Refer to Garmin G1000 Pilot’s Guide for the DA 42, P/N 190-00649-04 in the latest effective issue for...
Page 44: Source Documentation
General DA 42 AFM 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 45: Propeller
DA 42 AFM General 1.9.2 PROPELLER Address: mt-propeller Airport Straubing Wallmühle D-94348 Atting GERMANY Phone: +49-(9429)-9409-0 E-mail: sales@mt-propeller.com Website: www.mt-propeller.de Documents: E-124, Operation and Installation Manual Hydraulically controlled variable pitch propeller MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25 1.9.3 AVIONICS SYSTEM...
Page 46 General DA 42 AFM Intentionally left blank. Page 1 - 26 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 47 DA 42 AFM Operating Limitations CHAPTER 2 OPERATING LIMITATIONS Page INTRODUCTION ........2-3 AIRSPEED .
Page 48 Operating Limitations DA 42 AFM 2.16.6 GARMIN G1000 AVIONICS SYSTEM ....2-33 2.16.7 SMOKING ........2-37 2.16.8 GROUND OPERATION .
Page 49: Operating Limitations
DA 42 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 50: Airspeed
Operating Limitations DA 42 AFM 2.2 AIRSPEED Airspeed Remarks Maneuvering above 1542 kg 126 KIAS Do not make full or abrupt speed if (3400 lb) control surface movement MÄM 42-088 or above this speed. OÄM 42-054 or up to 1542 kg...
Page 51 DA 42 AFM Operating Limitations Airspeed Remarks Max. structural cruising speed 155 KIAS Do not exceed this speed except in smooth air, and then only with caution. Never exceed speed in smooth air 194 KIAS Do not exceed this speed in any operation.
Page 52: Airspeed Indicator Markings
Operating Limitations DA 42 AFM 2.3 AIRSPEED INDICATOR MARKINGS Marking KIAS Significance White arc 56 - 111 KIAS Operating range with flaps fully extended. Green arc 62 - 155 KIAS Normal operating range. Yellow arc 155 - 194 KIAS ‘Caution range’ - “Only in smooth air”.
Page 53: Power-Plant Limitations
DA 42 AFM Operating Limitations 2.4 POWER-PLANT LIMITATIONS a) Number of engines b) Engine manufacturer : Thielert Aircraft Engines c) Engine designation : TAE 125-01 Centurion 1.7 TAE 125-02-99 (if MÄM 42-198 is carried out) (P/N see Equipment List in Chapter 6)
Page 54 Operating Limitations DA 42 AFM i) Oil temperature: TAE 125-01 TAE 125-02-99 (MÄM 42-198 carried out) Minimum Maximum +140 +140 j) Gearbox temperature Maximum : 120 °C k) Coolant temperature: TAE 125-01 TAE 125-02-99 (MÄM 42-198 carried out) Minimum Maximum...
Page 55 DA 42 AFM Operating Limitations r) Approved fuel grades : see Section 2.14 - FUEL s) Oil specification : SHELL Helix Ultra 5W-30 SHELL Helix Ultra 5W-40 AEROSHELL Oil Diesel 10W-40 AERO SHELL Oil Diesel Ultra 5W-30 t) Gearbox oil (propeller gearbox): SHELL EP 75W90 API GL-4...
Page 56: Engine Instrument Markings
Operating Limitations DA 42 AFM 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the tables below. If the TAE 125-01 engine is installed: Indi- Yellow Green Yellow cation arc/bar arc/bar arc/bar arc/bar arc/bar...
Page 57 DA 42 AFM Operating Limitations If the TAE 125-02-99 engine is installed (MÄM 42-198 carried out): 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 up to...
Page 58: Warning, Caution And Advisory Alerts
Operating Limitations DA 42 AFM 2.6 WARNING, CAUTION AND ADVISORY ALERTS 2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000 NOTE The alerts described in the following are displayed on the Garmin G1000. Section 7.10.3 - WARNING, CAUTION AND ADVISORY MESSAGES includes a detailed description of the alerts.
Page 59 DA 42 AFM Operating Limitations Warning Alerts Meaning / Cause (red) L/R STARTER Left / Right engine starter is engaged. DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed and locked. POSN ERROR G1000 will no longer provide GPS based navigational guidance.
Page 60 Operating Limitations DA 42 AFM 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 (one reset of minor faults is possible) L/R ECU A FAIL * ECU A is being tested during FADEC-test procedure during the 'before take-off check'.
Page 61: Other Warning Alerts
DA 42 AFM Operating Limitations Caution Alerts Meaning / Cause (amber) CHECK GEAR Landing gear is not down and locked. (if installed) 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.
Page 62: Mass (Weight)
Operating Limitations DA 42 AFM 2.7 MASS (WEIGHT) Value Mass (Weight) Minimum flight mass 1250 kg 2756 lb Maximum take-off MÄM 42-088 not carried out 1700 kg 3748 lb mass MÄM 42-088 carried out 1785 kg 3935 lb Maximum zero fuel mass...
Page 63 DA 42 AFM Operating Limitations 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 64: Center Of Gravity
Operating Limitations DA 42 AFM 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 65: Approved Maneuvers
DA 42 AFM Operating Limitations 2.9 APPROVED MANEUVERS The airplane is certified in the Normal Category in accordance with JAR-23. Approved Maneuvers 1) All normal flight maneuvers; 2) Stalling (with the exception of dynamic stalling); and 3) Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which an angle of bank of not more than 60°...
Page 66: Maneuvering Load Factors
Operating Limitations DA 42 AFM 2.10 MANEUVERING LOAD FACTORS NOTE The tables below show structural limitations. The load factor limits for the TAE 125 engine must also be observed. Refer to the corresponding Operation & Maintenance Manual for the engine.
Page 67: Operating Altitude
DA 42 AFM Operating Limitations 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...
Page 68 Operating Limitations DA 42 AFM NOTE Many of the items of minimum equipment listed in the following table are integrated in the G1000. Minimum Operational Equipment (Serviceable) For Daytime VFR In Addition In addition Flights for Night VFR Flights for IFR Flights...
Page 69 DA 42 AFM Operating Limitations Minimum Operational Equipment (Serviceable) For Daytime VFR In Addition In addition Flights for Night VFR Flights for IFR Flights Engine * Fuel qty. (2x) * Ammeter Instru- * Oil press. (2x) * Voltmeter ments * Oil temp. (2x) * Coolant temp.
Page 70 Operating Limitations DA 42 AFM Minimum Operational Equipment (Serviceable) For Daytime VFR In Addition In addition Flights for Night VFR Flights for IFR Flights Other * Stall warning * Pitot heating * Emergency battery Opera- system system (for backup attitude...
Page 71: Fuel
Diesel (EN 590) and blends of the above listed Jet Fuel grades, and Diesel. CAUTION Limitations for DA 42 registered and/or operated in the following countries: Indonesia, Malaysia: Use of Diesel Fuel is NOT approved. CAUTION If the airplane is operated with Diesel Fuel or a blend of Diesel Fuel with Jet Fuel, the use of the auxiliary tanks, if installed (OÄM 42-056), is not permitted.
Page 72 Operating Limitations DA 42 AFM CAUTION Additional temperature limitations must be observed if the airplane is operated with Diesel Fuel or blends of Diesel Fuel with Jet Fuel. Refer to Section 2.16.1. NOTE Use only uncontaminated fuel from reliable sources.
Page 73: Limitation Placards
DA 42 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. 7.02.01), Chapter 11. On the Instrument Panel: THIS AIRPLANE MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANE MÄM 42-088 or...
Page 74 Operating Limitations DA 42 AFM On the Instrument Panel, Next to the Fuel Quantity Indication: (a) Standard Tank: (b) Auxiliary Tank (if installed): max. usable max. usable fuel fuel: 2 x 25 US gal main tank: max. difference LH/RH 2 x 25 US gal...
Page 75 DA 42 AFM Operating Limitations In Each Cowling, on the Door for the Oil Filler Neck: Shell Helix Ultra 5W-30 or see AFM Next to the Flap Selector Switch: Flaps 137 KIAS 111 KIAS In the Cabin, on the Left Fuselage Sidewall: EASA Doc.
Page 76 Operating Limitations DA 42 AFM Next to the Cabin Baggage Compartment: 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 unlocked during flight...
Page 77: Other Limitations
DA 42 AFM Operating Limitations 2.16 OTHER LIMITATIONS 2.16.1 FUEL TEMPERATURE JET Fuel grades and blends thereof: from -30 °C to +75 °C (from -22 °F to +167 °F) NOTE Operation with Diesel Fuel, or blends of Diesel Fuel with Jet Fuel, is only approved when MÄM 42-037 is incorporated.
Page 78: Emergency Switch
Operating Limitations DA 42 AFM 2.16.3 EMERGENCY SWITCH IFR flights are not permitted when the seal on the emergency switch is broken. 2.16.4 DOOR LOCKING DEVICE The canopy and the passenger door must not be blocked by the key lock during operation of the airplane.
Page 79: Garmin G1000 Avionics System
DA 42 AFM Operating Limitations 2.16.6 GARMIN G1000 AVIONICS SYSTEM 1. The Garmin G1000 Cockpit Reference Guide, P/N 190-00406-( ), latest effective issue must be immediately available to the flight crew. 2. If MÄM 42-101 has been implemented (refer to Section 1.1), the G1000 must utilize the software Garmin P/N: 010-00370-11, or later approved software in accordance with the Mandatory Service Bulletin DAI MSB 42-008, latest version.
Page 80 Operating Limitations DA 42 AFM Approved Software Part Number Function Version 006-D0202-( ) for approved 006-B0261-( ) GDC1-GIA1 version see DAI MSB 006-B0081-( ) COM1, COM2 42-008, latest 006-B0083-( ) GS1, GS2 version 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 81 DA 42 AFM Operating Limitations Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay with the G1000 GPS receiver is not authorized. 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.
Page 82 Operating Limitations DA 42 AFM 7. When AHRS is required to meet the items listed in the minimum operational equipment (serviceable) table in Section 2.13 - KINDS OF OPERATION, operation is prohibited in the following areas: North of 72° N latitude at all longitudes.
Page 83: Smoking
DA 42 AFM Operating Limitations 2.16.7 SMOKING Smoking in the airplane is not permitted. 2.16.8 GROUND OPERATION Take-off and landing has been demonstrated on hard paved surfaces (asphalt, concrete, etc.) and grass runways. 2.16.9 USE OF THE SUN VISORS The sun visors (if installed, OÄM 42-101 or OÄM 42-142) may only be used during cruise.
Page 84: Garmin Gwx 68 Weather Radar Operation
Operating Limitations DA 42 AFM 2.16.11 GARMIN GWX 68 WEATHER RADAR OPERATION WARNING The Garmin GWX 68 Weather Radar System (if installed) must not be operated on ground. If the system is transmitting, it may result in bodily injury if persons are within the minimum safe distance of 2.8 m (9.16 ft).
Page 85 Emergency DA 42 AFM Procedures CHAPTER 3 EMERGENCY PROCEDURES Page INTRODUCTION ........3-4 3.1.1 GENERAL .
Page 86 Emergency DA 42 AFM Procedures 3.4.1 NAVIGATION INFORMATION FAILURE ....3-16 3.4.2 PFD OR MFD DISPLAY FAILURE ....3-16 3.4.3 AHRS FAILURE .
Page 87 Emergency DA 42 AFM Procedures SMOKE AND FIRE ........3-55 3.8.1 ENGINE FIRE ON GROUND .
Page 88: Emergency Procedures
Emergency DA 42 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 89: Certain Airspeeds In Emergencies
Emergency DA 42 AFM Procedures 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event Airspeed One engine inoperative minimum control speed (air) v 68 KIAS One engine inoperative speed for best rate of climb v 82 KIAS 3.1.3 SELECTING EMERGENCY FREQUENCY In an in-flight emergency, depressing and holding the Com transfer button »º on the G1000 for 2 seconds will tune the emergency frequency of 121.500 MHz.
Page 90: Airplane-Related G1000 Warnings
Emergency DA 42 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. A warning chime tone of 1.5 seconds duration will sound and repeat without delay until the alarm is acknowledged by the crew.
Page 91 Emergency DA 42 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 92: L/R Oil Temp
Emergency DA 42 AFM Procedures 3.2.3 L/R OIL TEMP L/R OIL TEMP Left / Right engine oil temperature is in the upper red range (too high / above 140 °C). Oil temperatures above the limit value of 140 °C can lead to a total loss of power due to engine failure.
Page 93: L/R Oil Pres
Emergency DA 42 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 94: L/R Gbox Temp
Emergency DA 42 AFM Procedures 3.2.5 L/R GBOX TEMP Left / Right engine gearbox temperature is in the upper L/R GBOX TEMP 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 95: L/R Fuel Temp
Emergency DA 42 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 75 °C). Fuel temperatures above the limit value of 75 °C can lead to a noticeable reduction of the high pressure pump efficiency.
Page 96: L/R Altn Amps
Emergency DA 42 AFM Procedures 3.2.7 L/R ALTN AMPS Left / Right engine alternator output is in the upper red L/R ALTN AMPS range (too high / above 60 amps). Proceed according to: 3.7.2 - HIGH CURRENT 3.2.8 L/R ENG FIRE Left / Right engine fire detected.
Page 97: L/R Starter
Emergency DA 42 AFM Procedures 3.2.9 L/R STARTER L/R STARTER Left / Right engine starter is engaged. Proceed according to: 3.7.3 - STARTER MALFUNCTION 3.2.10 DOOR OPEN Front and/or rear canopy and/or baggage door are/is DOOR OPEN not closed and locked.
Page 98: G1000 System Warnings
Emergency DA 42 AFM Procedures 3.3 G1000 SYSTEM WARNINGS 3.3.1 RED X A red X through any display field, such as COM frequencies, NAV frequencies, or engine data, indicates that display field is not receiving valid data. 3.3.2 POSN ERROR...
Page 99: Altitude Fail
Emergency DA 42 AFM Procedures 3.3.5 ALTITUDE FAIL The display system is not receiving altitude input from the ALTITUDE FAIL air data computer; accompanied by a red X through the altimeter display. Revert to the standby altimeter. 3.3.6 VERT SPEED FAIL...
Page 100: G1000 Failures
Emergency DA 42 AFM Procedures 3.4 G1000 FAILURES 3.4.1 NAVIGATION INFORMATION FAILURE If Garmin G1000 GPS navigation information is not available or invalid, utilize remaining operational navigation equipment as required. 3.4.2 PFD OR MFD DISPLAY FAILURE 1. DISPLAY BACKUP button on audio panel . . PUSH...
Page 101 Emergency DA 42 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 102 Emergency DA 42 AFM Procedures 3.4.4 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 103 Emergency DA 42 AFM Procedures 3.4.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS NOTE Loss of an engine parameter is indicated by a red X through the data field. Erroneous information may be identified by indications which do not agree with other system information.
Page 104 Emergency DA 42 AFM Procedures 3.4.6 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 105 Emergency DA 42 AFM Procedures 3.5 ONE ENGINE INOPERATIVE PROCEDURES WARNING In certain combinations of airplane weight, configuration, ambient conditions, speed and pilot skill, negative climb performance result. Refer Chapter PERFORMANCE for one engine inoperative performance data. In any event the sudden application of power during one-engine inoperative operation makes the control of the airplane more difficult.
Page 106 Emergency DA 42 AFM Procedures 3.5.2 ENGINE TROUBLESHOOTING WARNING Control over the flight attitude has priority over attempts to solve the current problem ("first fly the aircraft"). NOTE With respect to handling and performance, the left-hand engine (pilots view) is considered the "critical" engine.
Page 107 Emergency DA 42 AFM Procedures 3. Fuel quantity ......check NOTE In case of low fuel quantity in the affected engine’s fuel tank you may feed it from the other engine’s fuel tank by setting...
Page 108 Emergency DA 42 AFM Procedures 3.5.3 ENGINE SECURING (FEATHERING) PROCEDURE Depending on the situation attempts can be made to restore engine power prior to securing the engine (see Section 3.5.2 - ENGINE TROUBLESHOOTING). Shut down and feathering of the affected engine: 1.
Page 109 Emergency DA 42 AFM Procedures 3.5.4 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT WARNING Do not attempt to restart the feathered engine when the reason of the engine failure cannot be identified since the un-feathered propeller of an inoperative engine might not be able to be feathered again.
Page 110 Emergency DA 42 AFM Procedures 1. Airspeed ......80 KIAS to 120 KIAS 2.
Page 111 Emergency DA 42 AFM Procedures Feathering the engine, if engine does not start: WARNING One attempt to feather the engine results in a loss of altitude of up to 500 ft. Do not attempt to feather the engine if the altitude is insufficient to execute the procedure.
Page 112 Emergency DA 42 AFM Procedures 15. Propeller ......check feathered 16. Alternator inoperative engine ... . OFF 17.
Page 113 Emergency DA 42 AFM Procedures If TAE 125-02 engines are installed (MÄM 42-198 carried out): NOTE Restarting the engine in flight is possible at altitudes below 8000 ft pressure altitude. Above 8000 ft pressure altitude restart in flight has not been demonstrated.
Page 114 Emergency DA 42 AFM Procedures CAUTION After the engine has started, the power lever should be set to a moderate power setting, until engine temperatures have reached the green range. 8. Circuit breakers ..... . . check Restarting the engine by windmilling: 9.
Page 115 Emergency DA 42 AFM Procedures CAUTION If the propeller does not feather after the first attempt, do not carry out further attempts to feather the propeller to avoid further loss of altitude. NOTE In order to feather the propeller the propeller RPM must be above 1800 RPM.
Page 116 Emergency DA 42 AFM Procedures NOTE The remaining fuel in the tank of the failed engine can be used for the remaining engine, to extend range and maintain lateral balance by setting the fuel selector of the remaining engine to the CROSSFEED position. If one of the power levers is set to low settings the landing gear warning horn is activated.
Page 117 Emergency DA 42 AFM Procedures 3.5.5 ENGINE FAILURE DURING TAKE-OFF (a) Engine Failure During Ground Roll Abort take-off. 1. POWER lever ......IDLE / BOTH 2.
Page 118 Emergency DA 42 AFM Procedures (b) Engine Failure After Lift Off If landing gear is still extended and the remaining runway / surface is adequate: Abort the take-off & land straight ahead, turning to avoid obstacles. If the remaining runway / surface is inadequate: Decide whether to abort or to continue the take-off.
Page 119 Emergency DA 42 AFM Procedures 6. Inoperative engine ....secure according to 3.5.3 - ENGINE SECURING (FEATHERING) PROCEDURE Continue according to Section 3.5.9 - FLIGHT WITH ONE ENGINE INOPERATIVE and land as soon as possible according to 3.5.7 - LANDING WITH ONE ENGINE...
Page 120 Emergency DA 42 AFM Procedures 3.5.6 ENGINE FAILURES IN FLIGHT (a) Engine Failure During Initial Climb at Airspeeds Below v = 68 KIAS WARNING As the climb is a flight condition which is associated with high power settings, airspeeds lower than v...
Page 121 Emergency DA 42 AFM Procedures (b) Engine Failure During Initial Climb at Airspeeds Above v = 68 KIAS 1. Rudder ......maintain directional control 2.
Page 122 Emergency DA 42 AFM Procedures (c) Engine Failure During Flight 1. Rudder ......maintain directional control 2.
Page 123 Emergency DA 42 AFM Procedures 3.5.7 LANDING WITH ONE ENGINE INOPERATIVE Preparation: WARNING 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 124 Emergency DA 42 AFM Procedures Not before being certain of "making the field“: 7. Airspeed ......reduce to operate landing gear 8.
Page 125 Emergency DA 42 AFM Procedures NOTE Higher approach speeds result in a significantly longer landing distance during flare. CAUTION In conditions such as (e.g.) strong wind, danger of wind shear or turbulence a higher approach speed should be selected. Perform normal touchdown and deceleration on ground.
Page 126 Emergency DA 42 AFM Procedures If the approach to land is not successful you may consider: 3.5.8 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 127 Emergency DA 42 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 128 Emergency DA 42 AFM Procedures If landing with landing gear extended: 10. LANDING GEAR ..... . DOWN, check 3 green 11.
Page 129 Emergency DA 42 AFM Procedures 3.5.9 FLIGHT WITH ONE ENGINE INOPERATIVE CAUTION Even if a positive flight performance can be established with one engine inoperative, land as soon as practicable at the next suitable airfield / airport. 1. Airspeed ......above v...
Page 130 Emergency DA 42 AFM Procedures 3.6 LANDING GEAR SYSTEM FAILURES 3.6.1 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 131 Emergency DA 42 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 132 Emergency DA 42 AFM Procedures 3.6.2 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 156 KIAS. The manual extension of the landing gear may take up to 20 seconds.
Page 133 Emergency DA 42 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 134 Emergency DA 42 AFM Procedures 3.6.3 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 135 Emergency DA 42 AFM Procedures 3.6.4 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 136 Emergency DA 42 AFM Procedures 3.6.5 LANDING WITH DEFECTIVE BRAKES Consider the greater rolling distance. Safety harness ......check fastened and tightened...
Page 137 Emergency DA 42 AFM Procedures 3.7 FAILURES IN THE ELECTRICAL SYSTEM 3.7.1 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 138 Emergency DA 42 AFM Procedures 3.7.2 HIGH CURRENT If high current is indicated on the G1000: 1. Circuit breakers ..... . . check 2.
Page 139: Smoke And Fire
Emergency DA 42 AFM Procedures 3.8 SMOKE AND FIRE NOTE In the event of smoke or fire, prepare to land the airplane without delay while completing fire suppression and/or smoke evacuation procedures. If it cannot be visually verified that the fire has been completely extinguished, whether the smoke has cleared or not, land immediately at the nearest suitable airfield or landing site.
Page 140 Emergency DA 42 AFM Procedures 3.8.2 ENGINE FIRE DURING TAKE-OFF Proceed according to 3.5.5 - ENGINE FAILURES DURING TAKE-OFF. 1. Cabin heat & defrost ....OFF...
Page 141 Emergency DA 42 AFM Procedures 3.8.4 ELECTRICAL FIRE ON GROUND 1. ELECT. MASTER ..... OFF If the engine is running: 2.
Page 142 Emergency DA 42 AFM Procedures 3.8.5 ELECTRICAL FIRE IN FLIGHT 1. EMERGENCY SWITCH ....ON, if installed 2. AVIONIC MASTER ....OFF 3.
Page 143: Other Emergencies
Emergency DA 42 AFM Procedures 3.9 OTHER EMERGENCIES 3.9.1 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 144 Emergency DA 42 AFM Procedures 3.9.2 UNLOCKED DOORS 1. Airspeed ......reduce immediately 2.
Page 145 Emergency DA 42 AFM Procedures Front Baggage Door Open 5. Airspeed ......reduce, so that door is in a stable position 6.
Page 146 Emergency DA 42 AFM Procedures 3.9.3 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 147 Emergency DA 42 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 148 Emergency DA 42 AFM Procedures 3.9.4 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 149 Emergency DA 42 AFM Procedures 3.9.5 FUEL SUPPLY FAILURE 1. FUEL SELECTOR ....CROSSFEED / affected engine WARNING When the high pressure fuel pump of the engine takes in air an inspection of the pump is necessary prior to next flight.
Page 150 Emergency DA 42 AFM Procedures 3.9.6 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. In the event a spin is encountered unintentionally, immediate recovery actions must be taken.
Page 151 Emergency DA 42 AFM Procedures When rotation has stopped: 6. Rudder ......neutral 7.
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Page 153 Normal Operating DA 42 AFM Procedures CHAPTER 4A NORMAL OPERATING PROCEDURES Page 4A.1 INTRODUCTION ........4A-3 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES .
Page 154 Normal Operating DA 42 AFM Procedures 4A.6.13 AFTER LANDING ......4A-41 4A.6.14 SHUT-DOWN ....... . 4A-42 4A.6.15 EXIT AIRPLANE .
Page 155: Introduction
Normal Operating DA 42 AFM Procedures 4A.1 INTRODUCTION Chapter 4A contains checklists and describes procedures for the normal operation of the airplane. NOTE Readability of the G1000 PFD and MFD displays may be degraded when wearing polarized sunglasses. 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES...
Page 156 1785 kg (3935 lb) constitutes an abnormal operating procedure. NOTE is always less than v . For the DA 42 however, the actual value of v would be below the minimum safe speed. The minimum airspeed for best angle of climb was therefore raised...
Page 157: Advisory Alerts On The G1000
Normal Operating DA 42 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 158: Flight Characteristics
Procedures 4A.4 FLIGHT CHARACTERISTICS The DA 42 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 159: Checklists For Normal Operating Procedures
Normal Operating DA 42 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 160 Normal Operating DA 42 AFM Procedures Below Instrument Panel in Front of Right Seat: a) ALTERNATE AIR ..... check CLOSED On the Instrument Panel: ALTERNATOR .
Page 161 Normal Operating DA 42 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 162 Normal Operating DA 42 AFM Procedures f) Gear warning/ fire detector TEST BUTTON ... . . PUSH, check aural alert / L/R ENG FIRE warnings and aural alert and CHECK GEAR...
Page 163 Normal Operating DA 42 AFM Procedures CAUTION The proper function of the variable elevator backstop is indispensable for the safety of flight, as the handling qualities during power-on stalls are degraded significantly. For more details see Chapter 7 - AIRPLANE DESCRIPTION AND SYSTEMS.
Page 164 Normal Operating DA 42 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 165 Normal Operating DA 42 AFM Procedures 1. Left Main Landing Gear: a) Landing gear strut and lock ... . . visual inspection, sufficient height (typical visible length of bare piston: at least 4 cm / 1.6 in) b) Down and uplock switches (2x) .
Page 166 Normal Operating DA 42 AFM Procedures c) Gearbox oil level ..... . check visually (inspection hole in the lower cowling) d) Cowling .
Page 167 Normal Operating DA 42 AFM Procedures 3. Left Wing: a) Entire wing surface ....visual inspection b) Tank air outlet on lower surface ..visual inspection c) Tank drain/tank air inlet .
Page 168 Normal Operating DA 42 AFM Procedures 4. Fuselage, Left Side, Underside: a) Canopy, left side ..... . visual inspection b) Rear cabin door & window ....visual inspection c) Fuselage skin .
Page 169 Normal Operating DA 42 AFM Procedures 7. Right Main Landing Gear: a) Landing gear strut and lock ... . . visual inspection, sufficient height (typical visible length of bare piston: at least 4 cm / 1.6 in) b) Down and uplock switches (2x) .
Page 170 Normal Operating DA 42 AFM Procedures e) Tank filler ......visual inspection, check closed f) Wing tip .
Page 171 Normal Operating DA 42 AFM Procedures CAUTION Do not check the engine oil level within 5 minutes after engine shut down. The engine oil returns to the oil pan slowly; after 5 minutes 80 %, after 15 minutes 90 % and after 30 minutes 100 % of the engine oil has returned to the oil pan.
Page 172 Normal Operating DA 42 AFM Procedures De-Icing boots on propeller (if OÄM 42-053 or/and OÄM 42-054 carried out) ..check for de-bonding Nacelle underside ..... check for excessive...
Page 173 Normal Operating DA 42 AFM Procedures k) OAT sensor ......check EPU connector ..... . . check m) Tow bar .
Page 174: 6.2 Before Starting Engine
Normal Operating DA 42 AFM Procedures 4A.6.2 BEFORE STARTING ENGINE 1. Preflight inspection ....complete 2. Passengers ......instructed...
Page 175 Normal Operating DA 42 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 position...
Page 176 Normal Operating DA 42 AFM Procedures 15. G1000 ......wait until power-up completed.
Page 177: 6.3 Starting Engine
Normal Operating DA 42 AFM Procedures 4A.6.3 STARTING ENGINE 1. Strobe lights (ACL) ....ON 2. ENGINE MASTER ....ON (L/R) NOTE It is recommended to start the LH engine (pilot side) first.
Page 178 Normal Operating DA 42 AFM Procedures CAUTION Do not overheat the starter motor. Do not operate the starter motor for more than 10 seconds. After operating the starter motor, let it cool off for 20 seconds. After 6 attempts to start the engine, let the starter cool off for half an hour.
Page 179: 6.4 Before Taxiing
Normal Operating DA 42 AFM Procedures 4A.6.4 BEFORE TAXIING 1. AVIONIC MASTER ....ON 2. Electrical equipment ....ON as required 3.
Page 180: 6.5 Taxiing
Normal Operating DA 42 AFM Procedures 4A.6.5 TAXIING 1. Parking brake ......release 2. Brakes ......test on moving off 3.
Page 181: 6.6 Before Take-Off
Normal Operating DA 42 AFM Procedures 4A.6.6 BEFORE TAKE-OFF 1. Position airplane into wind if possible. 2. Parking brake ......set...
Page 182 Normal Operating DA 42 AFM Procedures 10. Circuit breakers ..... . . check pressed in 11. Longitudinal trim ..... . set T/O 12.
Page 183 Normal Operating DA 42 AFM Procedures Annunciations in the Following Sequence: 3. ECU A/B FAIL LIGHTS ....ON 4. Propeller RPM ..... . . increase 5.
Page 184 Normal Operating DA 42 AFM Procedures CAUTION Running the engine with the ECU SWAP on ECU B, other than for this test or in an emergency is prohibited. The engines control system redundancy is only given with the ECU SWAP set on AUTO.
Page 185 Normal Operating DA 42 AFM Procedures WARNING If the airplane is operated with Diesel Fuel or a blend of Diesel Fuel with Jet Fuel (only approved if MÄM 42-037 is incorporated), or if the fuel grade is unknown, the fuel temperature must be in the green range before take-off.
Page 186: 6.7 Take-Off
Normal Operating DA 42 AFM Procedures 4A.6.7 TAKE-OFF 1. Transponder ......as required 2. POWER lever ......MAX...
Page 187 Normal Operating DA 42 AFM Procedures When safe climb is established: 7. Landing gear ......apply brakes; UP,...
Page 188: 6.8 Climb
Normal Operating DA 42 AFM Procedures 4A.6.8 CLIMB Initial Climb Check 1. Landing light ......OFF / as required 2.
Page 189: 6.9 Cruise
Normal Operating DA 42 AFM Procedures 4A.6.9 CRUISE 1. POWER lever ......performance as required NOTE The engine manufacturer recommends a cruise power setting of 70 %.
Page 190: 6.10 Descent
Normal Operating DA 42 AFM Procedures 1. Transfer the first half of the auxiliary fuel: As soon as the fuel quantity in each main fuel tank is 17 US gal or less, set both FUEL TRANSFER switches to ON until the main tanks are full again.
Page 191: 6.11 Approach & Landing
Normal Operating DA 42 AFM Procedures 4A.6.11 APPROACH & LANDING Approach: WARNING For landing the adjustable backrests (if installed) must be fixed in the upright position. 1. Adjustable backrests (if installed) ..adjust to the upright...
Page 192 Normal Operating DA 42 AFM Procedures Before Landing: 10. Airspeed up to 1700 kg (3748 lb) ....min. 82 KIAS with FLAPS APP above 1700 kg (3748 lb) ....min. 82 KIAS with FLAPS APP up to 1700 kg (3748 lb) .
Page 193: 6.12 Go Around
Normal Operating DA 42 AFM Procedures 4A.6.12 GO AROUND 1. POWER lever ......MAX 2. FLAPS ......position APP 3.
Page 194 Normal Operating DA 42 AFM Procedures 4A.6.14 SHUT-DOWN 1. Parking brake ......set 2. POWER lever ......IDLE for 2 minutes 3.
Page 195: 6.15 Exit Airplane
Normal Operating DA 42 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 196: 6.18 Flight In Rain
Normal Operating DA 42 AFM Procedures 4A.6.18 FLIGHT IN RAIN NOTE Performance deteriorates in rain; this applies particularly to the take-off distance and to the maximum horizontal speed. The effect on the flight characteristics is minimal. Flight through very heavy rain should be avoided because of the associated visibility problems.
Page 197: 6.20 Flight At High Altitude
Normal Operating DA 42 AFM Procedures Refueling of the Auxiliary Tanks (if installed) CAUTION If the auxiliary tanks are used, then both tanks must be refueled to the maximum level. Only then the pilot has proper information concerning the fuel quantity in the auxiliary tanks.
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Page 199 Abnormal Operating DA 42 AFM Procedures CHAPTER 4B ABNORMAL OPERATING PROCEDURES Page 4B.1 PRECAUTIONARY LANDING ......4B-3 4B.2 CANOPY IN COOLING GAP POSITION .
Page 200 Abnormal Operating DA 42 AFM Procedures 4B.4.13 RAIM UNAVAIL ....... 4B-22 4B.4.14 AHRS ALIGNING - KEEP WINGS LEVEL .
Page 201: Precautionary Landing
Abnormal Operating DA 42 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 202 Abnormal Operating DA 42 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 203: Canopy In Cooling Gap Position
Abnormal Operating DA 42 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 204: 3.2 Coolant Temperature
Abnormal Operating DA 42 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 205: 3.3 Oil Temperature
Abnormal Operating DA 42 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 206: 3.4 Oil Pressure
Abnormal Operating DA 42 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 207: 3.5 Gearbox Temperature
Abnormal Operating DA 42 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 208: 3.7 Voltage
Abnormal Operating DA 42 AFM Procedures 4B.3.7 VOLTAGE (a) Low Voltage Indication on the Ground 1. Circuit breakers ..... . . check 2.
Page 209: Caution-Alerts On The G1000
Abnormal Operating DA 42 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 * Amber color coded text. CHARACTERISTICS * Single warning chime tone of 1.5 seconds duration.
Page 210: 4.2 L/R Ecu A Fail
Abnormal Operating DA 42 AFM Procedures 4B.4.2 L/R ECU A FAIL * Left / Right engine ECU A has failed L/R ECU A FAIL * is being tested during FADEC test procedure before take-off check. (a) 'ECU A' Caution on the Ground Terminate flight preparation.
Page 211: 4.3 L/R Ecu B Fail
Abnormal Operating DA 42 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 FADEC test procedure before take-off check. (a) 'ECU B' Caution on the Ground Terminate flight preparation.
Page 212: 4.4 L/R Fuel Low
Abnormal Operating DA 42 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 213: 4.5 Low Voltage Caution (Low Volts)
Abnormal Operating DA 42 AFM Procedures 4B.4.5 LOW VOLTAGE CAUTION (LOW VOLTS) Left / Right bus voltage is less than 25 Volts. L/R VOLTS LOW Possible reasons are: - A fault in the power supply. - RPM too low. Continue with 4B.3.7 - VOLTAGE.
Page 214: 4.6 L/R Altn Fail
Abnormal Operating DA 42 AFM Procedures 4B.4.6 L/R ALTN FAIL Left / Right engine alternator has failed. L/R ALTN FAIL (a) One Alternator Failed 1. ALTERNATOR ..... . . OFF / affected side 2.
Page 215: 4.7 L/R Cool Lvl
Abnormal Operating DA 42 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 216: 4.8 Pitot Fail / Ht Off
Abnormal Operating DA 42 AFM Procedures 4B.4.8 PITOT FAIL / HT OFF Pitot heating system has failed. PITOT FAIL Pitot heating system is OFF. PITOT HT OFF 1. PITOT HEAT ......check ON / as required...
Page 217: 4.9 Stall Ht Fail/Off
Abnormal Operating DA 42 AFM Procedures 4B.4.9 STALL HT FAIL/OFF Stall warning heat has failed. STAL HT FAIL Stall warning heat is OFF. STAL HT OFF 1. PITOT HEAT ......check ON / as required...
Page 218: 4.10 L/R Auxiliary Fuel Tank Empty
Abnormal Operating DA 42 AFM Procedures 4B.4.10 L/R AUXILIARY FUEL TANK EMPTY (IF AUX. TANKS INSTALLED) Left / Right auxiliary fuel tank empty (displayed only L/R AUX FUEL E when FUEL TRANSFER pump is ON). The auxiliary tank empty caution message indicates an empty auxiliary fuel tank while the fuel pump is switched ON.
Page 219: 4.11 Stick Limit
Abnormal Operating DA 42 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 and the position of the flap selector switch. The system has two failure modes which can...
Page 220: 4.12 Check Gear (If Installed)
Abnormal Operating DA 42 AFM Procedures 4B.4.12 CHECK GEAR (IF INSTALLED) Landing gear is not down and locked. CHECK GEAR 1. Landing gear ......down / as required...
Page 221: 4.14 Ahrs Aligning - Keep Wings Level
Abnormal Operating DA 42 AFM Procedures (b) Final Approach If the RAIM UNAVAIL annunciation is displayed while on the final approach segment, GPS based navigation will continue for up to 5 minutes with approach CDI sensitivity (0.3 nautical miles). After 5 minutes the system will flag and no longer provide course guidance with approach sensitivity.
Page 222: Failures In Flap Operating System
Abnormal Operating DA 42 AFM Procedures 4B.5 FAILURES IN FLAP OPERATING SYSTEM Failure in Position Indication or Function 1. FLAPS position ..... . . check visually 2.
Page 223: Failures In Electrical Rudder Pedal Adjustment . 4B-25
Abnormal Operating DA 42 AFM Procedures 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 224: Failures In Hydraulic System
Abnormal Operating DA 42 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 3.6.2 - MANUAL EXTENSION OF THE LANDING GEAR.
Page 225: 7.2 Hydraulic Pump Failure
Abnormal Operating DA 42 AFM Procedures 4B.7.2 HYDRAULIC PUMP FAILURE 1. Landing gear indication lights ... . check 2. Prepare for manual landing gear extension. Refer to Section 3.6.2 - MANUAL EXTENSION OF THE LANDING GEAR.
Page 226: Starting Engine With External Power
Abnormal Operating DA 42 AFM Procedures 4B.8 STARTING ENGINE WITH EXTERNAL POWER 4B.8.1 BEFORE STARTING ENGINE 1. Pre-flight inspection ....complete 2.
Page 227 Abnormal Operating DA 42 AFM Procedures CAUTION When switching the external power unit ON, the electrically driven hydraulic gear pump may activate itself for 5 to 20 seconds in order to restore the system pressure. Should the pump continue to operate continuously or periodically, terminate flight.
Page 228: 8.2 Starting Engine
Abnormal Operating DA 42 AFM Procedures 4B.8.2 STARTING ENGINE 1. Strobe lights (ACL) ....ON 2. ELECT. MASTER ..... ON 3.
Page 229 Abnormal Operating DA 42 AFM Procedures 7. Annunciations / Engine / System Page ..check OK / normal range 8. Annunciations / Starter ....check OFF 9.
Page 230: Lightning Strike
Abnormal Operating DA 42 AFM Procedures 4B.9 LIGHTNING STRIKE 1. Airspeed ......as low as practicable, do not...
Page 231: 10 Landing With Mass Above Maximum Landing Mass
Abnormal Operating DA 42 AFM Procedures 4B.10 LANDING WITH MASS ABOVE MAXIMUM LANDING MASS NOTE Refer to Section 4A.6.11 - APPROACH & LANDING if OÄM 42-195 is carried out and for landings with a mass up to 1700 kg (3748 lb).
Page 232: 11 L/R Fuel Transfer Fail (If Aux. Tanks Are Installed)
Abnormal Operating DA 42 AFM Procedures 4B.11 L/R 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 fuel transfer pumps. CAUTION An imbalance in the auxiliary tanks is approved when the imbalance in the main tanks is less than 1 US gal (3.8 liter).
Page 233 DA 42 AFM Performance CHAPTER 5 PERFORMANCE Page INTRODUCTION ........5-2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS .
Page 234: Introduction
Performance DA 42 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 they allow comprehensive and sufficiently accurate flight planning. The values...
Page 235: Performance Tables And Diagrams
DA 42 AFM Performance 5.3 PERFORMANCE TABLES AND DIAGRAMS 5.3.1 AIRSPEED CALIBRATION NOTE The position of the landing gear (extended/retracted) has no influence on the airspeed indicator system. Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 3...
Page 236 Performance DA 42 AFM Page 5 - 4 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 237 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 5...
Page 238: Fuel Flow Diagram
Performance DA 42 AFM 5.3.2 FUEL FLOW DIAGRAM CAUTION The diagram 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 239: International Standard Atmosphere
DA 42 AFM Performance 5.3.3 INTERNATIONAL STANDARD ATMOSPHERE Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 7...
Page 240: Stalling Speeds
Performance DA 42 AFM 5.3.4 STALLING SPEEDS CAUTION The calculated stalling speeds may be higher than the maximum approved / limiting flap-extended and / or maneuvering airspeeds. Stalling Speeds at Various Flight Masses Airspeeds in KIAS at idle power: 1400 kg (3086 lb)
Page 241: Wind Components
DA 42 AFM Performance 5.3.5 WIND COMPONENTS Example: Flight direction 360° Wind 32°/30 kts Result: Crosswind component 16 kts Max. demonstrated crosswind component 20 kts Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 9...
Page 242: Take-Off Distance
Performance DA 42 AFM 5.3.6 TAKE-OFF DISTANCE Conditions: - POWER lever ......both MAX @ 2300 RPM - Flaps .
Page 243 DA 42 AFM Performance 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 unfavorable...
Page 244 Performance DA 42 AFM NOTE For wet grass, an additional 10 % increase in take-off roll must be expected. NOTE An uphill slope of 2 % (2 m per 100 m or 2 ft per 100 ft) results in an increase in the take-off distance of approximately 10 %.
Page 245 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 13...
Page 246 Performance DA 42 AFM Page 5 - 14 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 247 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 15...
Page 248 Performance DA 42 AFM Page 5 - 16 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 249: Climb Performance - Take-Off Climb
DA 42 AFM Performance 5.3.7 CLIMB PERFORMANCE - TAKE-OFF CLIMB Conditions: - POWER lever ..... . . both MAX @ 2300 RPM - Flaps .
Page 250 Performance DA 42 AFM Page 5 - 18 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 251 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 19...
Page 252: Climb Performance - Cruise Climb
Performance DA 42 AFM 5.3.8 CLIMB PERFORMANCE - CRUISE CLIMB Conditions: - POWER lever ......both MAX @ 2300 RPM - Flaps .
Page 253 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 21...
Page 254 Performance DA 42 AFM Page 5 - 22 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 255: One Engine Inoperative Climb Performance
DA 42 AFM Performance 5.3.9 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE Conditions: - Remaining engine (RH) ....MAX @ 2300 RPM - Dead engine ......feathered and secured - Flaps .
Page 256 Performance DA 42 AFM Page 5 - 24 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 257 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 25...
Page 258: Cruising (True Airspeed Tas)
Performance DA 42 AFM 5.3.10 CRUISING (TRUE AIRSPEED TAS) Conditions: - Engines ......all operating - POWER lever .
Page 259 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 27...
Page 260: Landing Distance
Performance DA 42 AFM 5.3.11 LANDING DISTANCE Conditions: - POWER lever ... . . both IDLE - Flaps ....LDG - Runway .
Page 261 DA 42 AFM Performance WARNING Poor maintenance condition of the airplane, deviation from the given procedures, uneven runway, as well as unfavorable external factors (high temperature, rain, unfavorable wind conditions, including cross-wind) will increase the landing distance. CAUTION The figures in the following NOTE are typical values. On wet ground or wet soft grass covered runways the landing distance may become significantly longer than stated below.
Page 262 Performance DA 42 AFM Page 5 - 30 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 263 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 31...
Page 264 Performance DA 42 AFM Page 5 - 32 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 265 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 5 - 33...
Page 266: Gradient Of Climb On Go-Around
Performance DA 42 AFM 5.3.12 GRADIENT OF CLIMB ON GO-AROUND Conditions: - POWER lever ......both MAX @ 2300 RPM - Flaps .
Page 267 DA 42 AFM Performance 5.3.13 APPROVED NOISE DATA Max. Flight Mass 1700 kg (3748 lb) ICAO Annex 16 Chapter X, App. 6 ... . 75.2 dB(A) JAR-36 Subpart C ......75.2 dB(A) Max.
Page 268 Performance DA 42 AFM Intentionally left blank. Page 5 - 36 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 269 DA 42 AFM Mass and Balance CHAPTER 6 MASS AND BALANCE Page INTRODUCTION ........6-2 DATUM PLANE .
Page 270: Introduction
Mass and Balance DA 42 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 271: Datum Plane
DA 42 AFM Mass and 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 272: Mass And Balance Report
Mass and Balance DA 42 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 273 DA 42 AFM Mass and Balance MASS AND BALANCE REPORT Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 6 - 5...
Page 274: Flight Mass And Center Of Gravity
DA 42 AFM 6.4 FLIGHT MASS AND CENTER OF GRAVITY The following information enables you to operate your DA 42 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 275 DA 42 AFM Mass and 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. If the auxiliary tanks are not in use, the pilot must ensure that they are empty.
Page 276 Mass and Balance DA 42 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 277 DA 42 AFM Mass and Balance 6.4.2 LOADING DIAGRAM Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 6 - 9...
Page 278 Mass and Balance DA 42 AFM 6.4.3 CALCULATION OF LOADING CONDITION NOTE If the optional de-icing system (OÄM 42-053 or OÄM 42-054) is installed, the following must be observed: The consumption of fuel causes a forward movement of the CG. The consumption of de-icing fluid causes a rearward movement of the CG.
Page 279: Calculation Of Loading Condition
DA 42 AFM Mass and Balance DA 42 (Example) Your DA 42 CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 1. Empty mass (from Mass and 1250 2937.5 Balance Report) 2756 254,965 2.
Page 280 Mass and Balance DA 42 AFM DA 42 (Example) Your DA 42 CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 10. Usable fuel, auxiliary tanks (if installed; OÄM 42-056) 268.8 (0.84 kg/liter) 23,310 (7.01 lb/US gal)
Page 281: Permissible Center Of Gravity Range
DA 42 AFM Mass and Balance 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 6 - 13...
Page 282 Mass and Balance DA 42 AFM The flight CG position must be within the following limits: Most forward flight CG: 2.35 m (92.52 in) aft of Datum Plane at 1250 kg (2756 lb) 2.35 m (92.52 in) aft of Datum Plane at 1468 kg (3236 lb) 2.40 m (94.49 in) aft of Datum Plane at max.
Page 283: Permissible Moment Range
DA 42 AFM Mass and Balance 6.4.5 PERMISSIBLE MOMENT RANGE The flight mass moments shown in the diagram are those from the example in Table 6.4.3 (a) 'CALCULATION OF LOADING CONDITION', rows 8 and 11. Doc. No. 7.01.05-E Rev. 8...
Page 284: Equipment List And Equipment Inventory
Mass and Balance DA 42 AFM 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY All equipment that is approved for installation in the DA 42 is shown in the Equipment List below. NOTE The equipment listed below cannot be installed in any arbitrary combination.
Page 303 DA 42 AFM Airplane Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Page INTRODUCTION ........7-3 AIRFRAME .
Page 304 Airplane Description DA 42 AFM 7.12 STALL WARNING SYSTEM ......7-68 7.13 GARMIN G1000 INTEGRATED AVIONICS SYSTEM .
Page 305: Introduction
DA 42 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 306: Flight Controls
Airplane Description DA 42 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 307 DA 42 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 308 Airplane Description DA 42 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 309 Variable Elevator Stop: The DA 42 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) and the flap selector switch is set to LDG. This is 2.5° less than the 15.5°...
Page 310 Airplane Description DA 42 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. The bolts and nuts are accessible to visual inspection.
Page 311 DA 42 AFM Airplane Description Elevator Trim The trim control is a black wheel in the center console to the rear of the power lever. To guard against overrotating, the trim wheel incorporates a friction device. A mark on the wheel shows the take-off (T/O) position.
Page 312 Airplane Description DA 42 AFM Rearward Adjustment: Using the unlocking handle, pull the pedals back to the desired position. Release the handle and push the pedals forward with your feet until they lock into place. Electrical Pedal Adjustment (Optional Equipment, OÄM 42-070)
Page 313: Instrument Panel
DA 42 AFM Airplane Description 7.4 INSTRUMENT PANEL Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 7 - 11...
Page 314 *) Designations and abbreviations used to identify the circuit breakers are explained in Section 1.5 - DEFINITIONS AND ABBREVIATIONS. NOTE The Figure on the previous page shows the typical DA 42 installation position for the equipment. The actual installation may vary due to the approved equipment version.
Page 315 DA 42 AFM Airplane Description Cockpit Ventilation Ventilation in the front is provided by spherical ventilation nozzles (16) in the instrument panel. Furthermore there are spherical nozzles in the roll bar on the left and right side next to the front seats as well as on the central console above the passengers* heads.
Page 316: Landing Gear
Airplane Description DA 42 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 317 DA 42 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 318 DA 42 AFM Hydraulic Gear Extension System Schematic The main landing gear of the DA 42 is extended with three hydraulic cylinders. The following schematic Figures show the system conditions for each operating mode. In Figure 1 the extension of the landing gear is shown. To reduce the amount of pumped hydraulic fluid during this operation, the return flow is partly led into the feeding flow of the system.
Page 319 DA 42 AFM Airplane Description The operating mode for the retraction of the landing gear is shown in the next Figure. While energizing the right hydraulic valve, the fluid flow in the hydraulic system is started due to different piston areas of the landing gear cylinders although the pressure on both sides of the system is equal.
Page 320 Airplane Description DA 42 AFM For an emergency extension of the landing gear, the hydraulic fluid can pass through an emergency extension valve so that the gear is extended by gravity. The condition of the system is shown in the Figure below.
Page 321 DA 42 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 322: Seats And Safety Harnesses
Airplane Description DA 42 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 323 DA 42 AFM Airplane Description CAUTION Do not apply a load of more than 90 daN (202 lbf) to 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 324 Airplane Description DA 42 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. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 325 DA 42 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. 7.01.05-E Rev. 8 15-Dec-2017 Page 7 - 23...
Page 326: Baggage Compartment
Airplane Description DA 42 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. Baggage may be loaded there provided it is restrained by means of a baggage net.
Page 327 DA 42 AFM Airplane Description Rear Door The rear door is closed in the same way, by pulling down on the frame and locking it with the handle. A gas pressure damper prevents the door from dropping; in strong winds the assembly must be securely held.
Page 328 Airplane Description DA 42 AFM 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 329 DA 42 AFM Airplane Description 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 330: Power Plant
Airplane Description DA 42 AFM 7.9 POWER PLANT 7.9.1 ENGINES, GENERAL There are two TAE125 engines installed, which have the following principal specifications: - Liquid-cooled four-cylinder four-stroke Diesel-cycle engine with wet sump lubrication - Inline construction - Common rail direct injection - Propeller speed reducing gear 1:1.69...
Page 331: Propeller
DA 42 AFM Airplane Description 7.9.2 PROPELLER Two mt-Propeller MTV-6-A-C-F/CF187-129 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. These blades combine the lowest weight whilst minimizing vibration.
Page 332 Airplane Description DA 42 AFM 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 20 bar (290 PSI).
Page 333 DA 42 AFM Airplane Description 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 334: Operating Controls
Airplane Description DA 42 AFM 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 335 DA 42 AFM Airplane Description 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 336 Airplane Description DA 42 AFM START Turning START key switch to the left starts the LH engine. Turning it to the right side starts the RH engine. ECU SWAP There are two ECU SWAP switches, one for each engine. For normal operation both switches are set to AUTOMATIC.
Page 337 DA 42 AFM Airplane Description 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 338: Engine Instruments
Airplane Description DA 42 AFM 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 339 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. NOTE The fuel calculations on the FUEL CALC portion do not use the airplane’s fuel quantity indicators.
Page 340: Fuel System
Airplane Description DA 42 AFM 7.9.5 FUEL SYSTEM General Page 7 - 38 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 341 DA 42 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 342 Airplane Description DA 42 AFM Fuel Selector Valves For each engine one fuel selector valve is provided. The control levers for the fuel selector valves are situated on the center console behind the power levers. The positions are ON, CROSSFEED and OFF. During normal operation each engine takes the fuel from the tank on the same side as the engine.
Page 343 DA 42 AFM Airplane Description 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 344 Airplane Description DA 42 AFM 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 345 DA 42 AFM Airplane Description 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 liter (1 US gal) of fuel in each wing are unusable, so that a total quantity of 94.6 liter (25 US gal) in each...
Page 346 Airplane Description DA 42 AFM 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 347 DA 42 AFM Airplane Description When one fuel transfer pump is defective, the fuel stored in the related auxiliary fuel tank is not available. For use of the remaining fuel pump refer to Section 4B.11 - L/R FUEL TRANSFER FAIL. The flight plan must be amended accordingly.
Page 348 Airplane Description DA 42 AFM 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 349 DA 42 AFM Airplane Description Fuel Temperature A fuel temperature sensor measures the fuel temperature in each main tank. The indication is provided by the G1000 flight display. Information about fuel temperature limitations can be found in Chapter 2 - OPERATING LIMITATIONS.
Page 350 Airplane Description DA 42 AFM 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. CAUTION If the airplane is operated with Diesel Fuel or a blend of Diesel Fuel with Jet Fuel the use of the auxiliary tanks, if installed (OÄM 42-056), is not permitted.
Page 351: Cooling System
DA 42 AFM Airplane Description 7.9.6 COOLING SYSTEM Each engine is liquid cooled. The liquid cooling system consists of a radiator 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 thermostat valve.
Page 352: Oil Systems
Airplane Description DA 42 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 separate cooler on the underside of the engine.
Page 353 DA 42 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 354 DA 42 AFM 7.9.9 FIRE DETECTION SYSTEM The fire detection system in the DA 42 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 appears in the annunciation window of the G1000 PFD.
Page 355: Electrical System
DA 42 AFM Airplane Description 7.10 ELECTRICAL SYSTEM Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 7 - 53...
Page 356: General
Airplane Description DA 42 AFM 7.10.1 GENERAL The DA 42 has 28 Volt DC system, which can be sub-divided into: - Power generation - Storage - Distribution - Consumers Power Generation Power generation is provided by two 60 Ampère alternators (generators) which are mounted on the bottom left side of each engine.
Page 357 DA 42 AFM Airplane Description 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 358 Airplane Description DA 42 AFM 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 359 DA 42 AFM Airplane Description MAIN BUS: The LH (RH) MAIN BUS is connected to the BATTERY BUS via a 90 Ampère circuit breaker. The LH MAIN BUS provides power to the consumers directly connected to the LH MAIN BUS. The RH MAIN BUS provides power to the consumers directly connected to the RH MAIN BUS and the AVIONIC BUS via the AVIONICS MASTER relay.
Page 360 Airplane Description DA 42 AFM Position and Strobe Lights Combined position and strobe lights (anti collision lights) are installed on both wing tips. Each system is operated by a switch (POSITION, STROBE) located on the row of switches on the instrument panel.
Page 361 Airplane Description External Power Socket The DA 42 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 362 Airplane Description DA 42 AFM 7.10.2 ENGINE CONTROL UNIT / ECU Engine Control and Regulation The ECU monitors, controls and regulates all important parameters for engine operation. Sensors installed are: - Oil temperature (lubrication system engine) / OIL TEMP - Oil pressure (lubrication system engine) / OIL PRES...
Page 363 DA 42 AFM Airplane Description 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: - Activation of starter (relay) - Signal for propeller governor pressure valve...
Page 364 Airplane Description DA 42 AFM 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 365 DA 42 AFM Airplane Description Alert Levels Level Text Color Importance Audible Tone Warning chime May require tone which repeats Warning immediate without delay until corrective action acknowledged by the crew May require future Single warning Caution Amber corrective action...
Page 366 Airplane Description DA 42 AFM Warning Alerts on the G1000 Warning Alerts Meaning / Cause The annunciation is active when the engine coolant temperature L/R ENG TEMP is greater than 105 °C. The annunciation is active when the engine oil temperature is L/R OIL TEMP greater than 140 °C.
Page 367 DA 42 AFM Airplane Description Warning Alerts Meaning / Cause The annunciation is active when the display system is not receiving valid heading input from the AHRS. WARN This annunciation constitutes a RAIM position warning. The nav deviation bar is removed.
Page 368 Airplane Description DA 42 AFM Caution Alerts on the G1000 Caution Alerts Meaning / Cause The annunciation is active when a fault in ECU A or ECU B has occurred. L/R ECU A FAIL In case of minor faults, the annunciation can be reset once by pressing the ECU TEST button for more than 2 seconds.
Page 369 DA 42 AFM Airplane Description Annunciation Advisory Alerts on the G1000 Advisory Alerts Meaning / Cause L/R GLOW ON The annunciation is active when the glow plugs are powered. L/R FUEL XFER The annunciation is active when fuel transfer from auxiliary to main tank is in progress.
Page 370: Stall Warning System
7.12 STALL WARNING SYSTEM The lift detector of the DA 42 is located on the front edge of the left wing below the wing chord line. It is supplied electrically and provides a stall warning, before the angle of attack becomes critical.
Page 371 DA 42 AFM Airplane Description 7.13 GARMIN G1000 INTEGRATED AVIONICS SYSTEM 7.13.1 GENERAL The Gamin G1000 is a fully integrated flight, engine, communication, navigation and surveillance instrumentation system. This Integrated Avionics System consists of a Primary Flight Display (PFD), a Multifunction Display (MFD), an Audio Panel, an Attitude and Heading Reference System (AHRS), an Air Data Computer (ADC) and the sensors and computers to process flight and engine information for display to the pilot.
Page 372 Airplane Description DA 42 AFM 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. One width of the trapezoid is equal to a one ball width slip.
Page 373 DA 42 AFM Airplane Description 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 374 Airplane Description DA 42 AFM 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 375 DA 42 AFM Airplane Description 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 376 Airplane Description DA 42 AFM 7.14 STRUCTURAL TEMPERATURE INDICATOR If OÄM 42-188 is carried out a structural temperature indicator, installed in the LH and RH main landing gear bay (see Figure below) indicates when the structural temperature limitation is exceeded (refer to Section 2.16.10). The indicator needs to be checked if the zero fuel mass exceeds 1650 kg (3638 lb).
Page 377 DA 42 AFM Airplane Description Location of Temperature Indicator and Placard LH MLG bay shown, RH MLG bay opposite: PLACARD TEMPERATURE INDICATOR Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 7 - 75...
Page 378 Airplane Description DA 42 AFM Intentionally left blank. Page 7 - 76 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 379 Handling, Care, DA 42 AFM Maintenance CHAPTER 8 AIRPLANE HANDLING, CARE AND MAINTENANCE Page INTRODUCTION ........8-2 AIRPLANE INSPECTION INTERVALS .
Page 380: Introduction
Handling, Care, DA 42 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. 7.02.01) lists certain inspection and maintenance requirements which must be followed if the airplane is to retain a new plane performance and reliability.
Page 381: Airplane Alterations Or Repairs
Handling, Care, DA 42 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. 7.02.01, and only by authorized personnel. 8.4 SERVICING 8.4.1 REFUELING WARNING Do not allow fire, sparks or heat near fuel.
Page 382 Handling, Care, DA 42 AFM Maintenance WARNING Do not operate electrical switches in the airplane during refueling. CAUTION Use only approved fuel types given in Chapter 2. 1. Ground the airplane and the fuel supply vehicle electrically. 2. Remove the fuel filler cap (located on top of the outer wing). Check cap retaining cable for damage.
Page 383: Engine Oil Level Check
Handling, Care, DA 42 AFM Maintenance 8.4.2 ENGINE OIL LEVEL CHECK CAUTION Do not check the engine oil level within 5 minutes after engine shut down. The engine oil returns to the oil pan slowly; after 5 minutes 80%, after 15 minutes 90% and after 30 minutes 100% of the engine oil has returned to the oil pan.
Page 384: Gearbox Oil Level Check
Handling, Care, DA 42 AFM Maintenance 8.4.3 GEARBOX OIL LEVEL CHECK 1. Open the inspection door on the forward left side of the lower cowling. 2. Check gearbox oil level in inspection window. 3. Close the inspection door. 4. Repeat steps 1 to 3 for the other engine.
Page 385: Ground Handling / Road Transport
Handling, Care, DA 42 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 386 Handling, Care, DA 42 AFM Maintenance Nose Landing Gear Leg Max. 40° Max. 40° Tow Bar Steering Bar Steering Bar or Tow Bar Attachment Page 8 - 8 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 387 Handling, Care, DA 42 AFM Maintenance CAUTION If the airplane is towed by steering / tow bar by hand or a tow vehicle, do not turn the nose wheel more than 40 degrees to either side from the center position. Otherwise damage to the torque links of the nose landing gear will result.
Page 388: Parking
Handling, Care, DA 42 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 389 Handling, Care, DA 42 AFM Maintenance The control surfaces gust lock is installed as follows: 1. Move the rudder pedals fully forward. 2. Engage the control surfaces gustlock with the pedals. 3. Engage the stick, wrap straps around stick once.
Page 390 Handling, Care, DA 42 AFM Maintenance Page 8 - 12 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...
Page 391: Mooring
Handling, Care, DA 42 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 392: Cleaning And Care
Handling, Care, DA 42 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 393: Propeller
Handling, Care, DA 42 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 394 Handling, Care, DA 42 AFM Maintenance 8.7 GROUND DE-ICING Approved deicing fluids are: Manufacturer Name Kilfrost TKS 80 Aeroshell Compound 07 Any source AL-5 (DTD 406B) 1. Remove any snow from the airplane using a soft brush. 2. Spray deicing fluid onto ice-covered surfaces using a suitable spray bottle.
Page 395 DA 42 AFM Supplements CHAPTER 9 SUPPLEMENTS Page INTRODUCTION ........9-2 LIST OF SUPPLEMENTS .
Page 396 DA 42 AFM 9.1 INTRODUCTION Chapter 9 contains information concerning additional (optional) equipment of the DA 42. 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 397 DA 42 AFM Supplements 9.2 LIST OF SUPPLEMENTS Airplane S/N: Registration: Date: Sup. Rev. applicable Title Date Autopilot System, 01-Dec-2004 Bendix/King KAP 140 DA 42 M 05-Sep-2011 Belly Pod 30-Apr-2008 Riegl Laserscanner System 18-Feb-2008 Operator Desk 20-Apr-2015 Universal Nose 23-Jan-2012...
Page 398 Supplements DA 42 AFM Airplane S/N: Registration: Date: Sup. Rev. applicable Title Date Cooling - Baffle for Cold Weather 27-Feb-2015 Operation Ice Protection System (if OÄM 42-053 is installed and 12-Jan-2007 OÄM 42-054 is not installed) Ice Protection System - Known...
Page 399 DA 42 AFM Supplements Airplane S/N: Registration: Date: Sup. Rev. applicable Title Date Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 9 - 5...
Page 400 Supplements DA 42 AFM NOTE The Supplement S05 is only valid if VÄM 42-002 has not been carried out. If VÄM 42-002 was carried out Supplement S05 is replaced by Supplement M00. Page 9 - 6 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E...

Diamond DA 42 Flight Manual

General

Operating Limitations

Emergency Procedures

A Normal Operating Procedures

B Abnormal Operating Procedures

Performance

Mass and Balance

Description of the Airplane and Its Systems

Airplane Handling, Care and Maintenance

Quick Links

Chapters

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Summary of Contents for Diamond DA 42