Page 2 Introduction DA 42 AFM Intentionally left blank. Page 0 - 0a Rev. 3 15-Oct-2005 Doc. # 7.01.05-E...
Page 3 Before this airplane is operated for the first time, the pilot must familiarize himself with the complete contents of this Airplane Flight Manual. In the event that you have obtained your DIAMOND DA 42 second-hand, please let us know your address, so that we can supply you with the publications necessary for the safe operation of your airplane.
Page 4 Introduction DA 42 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. all except cover Andreas certification; 1 Dec 2004 2005-196 page Winkler for corrections ACG] 0-3, 0-5, MÄM 42-034 [10 Feb (elevator 0-7, 0-8, 0-9 2005 stop);...
Page 7 DA 42 AFM Introduction 0.3 LIST OF EFFECTIVE PAGES Ch. Page Date Ch. Page Date 15-Oct-2005 29-Apr-2004 30-Nov-2005 0-0a 15-Oct-2005 appr. 2-3 15-Oct-2005 15-Oct-2005 appr. 2-4 30-Nov-2005 15-Oct-2005 appr. 2-5 15-Oct-2005 30-Nov-2005 appr. 2-6 15-Oct-2005 30-Nov-2005 appr. 2-7 30-Nov-2005 30-Nov-2005 appr.
Page 8 Introduction DA 42 AFM Ch. Page Date Ch. Page Date 15-Oct-2005 3-31 30-Nov-2005 15-Oct-2005 3-32 30-Nov-2005 15-Oct-2005 3-33 15-Oct-2005 15-Oct-2005 3-34 15-Oct-2005 15-Oct-2005 3-35 15-Oct-2005 15-Oct-2005 3-36 15-Oct-2005 15-Oct-2005 3-37 15-Oct-2005 15-Oct-2005 3-38 30-Nov-2005 15-Oct-2005 3-39 15-Oct-2005 3-10 15-Oct-2005 3-40...
Page 9 DA 42 AFM Introduction Ch. Page Date Ch. Page Date 4A-1 30-Nov-2005 4B-1 15-Oct-2005 4A-2 30-Nov-2005 4B-2 30-Nov-2005 4A-3 30-Nov-2005 4B-3 15-Oct-2005 4A-4 30-Nov-2005 4B-4 15-Oct-2005 4A-5 30-Nov-2005 4B-5 15-Oct-2005 4A-6 30-Nov-2005 4B-6 15-Oct-2005 4A-7 30-Nov-2005 4B-7 15-Oct-2005 4A-8 30-Nov-2005...
Page 10 Introduction DA 42 AFM Ch. Page Date Ch. Page Date 30-Nov-2005 15-Oct-2005 30-Nov-2005 15-Oct-2005 30-Nov-2005 15-Oct-2005 30-Nov-2005 15-Oct-2005 30-Nov-2005 30-Nov-2005 30-Nov-2005 15-Oct-2005 30-Nov-2005 15-Oct-2005 30-Nov-2005 30-Nov-2005 30-Nov-2005 15-Oct-2005 5-10 30-Nov-2005 6-10 30-Nov-2005 5-11 30-Nov-2005 6-11 30-Nov-2005 5-12 30-Nov-2005 6-12 30-Nov-2005...
Page 11 DA 42 AFM Introduction Ch. Page Date Ch. Page Date 30-Nov-2005 7-38 15-Oct-2005 30-Nov-2005 7-39 15-Oct-2005 15-Oct-2005 7-40 30-Nov-2005 15-Oct-2005 7-41 30-Nov-2005 15-Oct-2005 7-42 30-Nov-2005 15-Oct-2005 7-43 30-Nov-2005 15-Oct-2005 7-44 30-Nov-2005 15-Oct-2005 7-45 30-Nov-2005 15-Oct-2005 7-46 30-Nov-2005 7-10 15-Oct-2005 7-47...
Page 12 Introduction DA 42 AFM Ch. Page Date 15-Oct-2005 15-Oct-2005 15-Oct-2005 30-Nov-2005 15-Oct-2005 15-Oct-2005 15-Oct-2005 15-Oct-2005 15-Oct-2005 8-10 15-Oct-2005 8-11 15-Oct-2005 8-12 30-Nov-2005 15-Oct-2005 30-Nov-2005 Page 0 - 10 Rev. 4 30-Nov-2005 Doc. # 7.01.05-E...
Page 13 DA 42 AFM Introduction 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) ......... . 1 OPERATING LIMITATIONS (an approved chapter) .
Page 14 Introduction DA 42 AFM Intentionally left blank. Page 0 - 12 Rev. 3 15-Oct-2005 Doc. # 7.01.05-E...
Page 15: Table Of Contents
DA 42 AFM General CHAPTER 1 GENERAL Page INTRODUCTION ........1-2 CERTIFICATION BASIS .
Page 16: 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 17: Certification Basis
Cockpit Reference Guide is the bag on the rear side of the forward left seat. 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.
Page 18: Warnings, Cautions And Notes
General DA 42 AFM 1.3 WARNINGS, CAUTIONS AND NOTES Special statements in the Airplane Flight Manual concerning the safety or operation of the airplane are highlighted by being prefixed by one of the following terms: WARNING means that the non-observation of the corresponding procedure leads to an immediate or important degradation in flight safety.
Page 19: Dimensions
DA 42 AFM General 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall dimensions Span : 13.42 m 44 ft Length : 8.56 m 28 ft 1 in Height : 2.49 m 8 ft 2 in Wing Airfoil : Wortmann FX 63-137/20 - W4 Wing Area : 16.29 m²...
Page 20 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...
Page 21: 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. KCAS: CAS in knots. KIAS: IAS in knots. IAS: Indicated Airspeed as shown on an airspeed indicator.
Page 22 General DA 42 AFM Maximum Structural Cruising Speed. This speed may be exceeded only in smooth air, and then only with caution. Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration.
Page 23 DA 42 AFM General QNH: Theoretical atmospheric pressure at MSL, calculated from the elevation of the measuring point above MSL and the actual atmospheric pressure at the measuring point. Density Altitude: Altitude in ISA conditions at which the air density is equal to the current air density.
Page 24 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 25 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 26 General DA 42 AFM RH MAIN BUS: Multi Function Display Artificial Horizon STALL WRN Stall Warning System FLAP Flap System LDG LT/START Landing Light / Start INST LT/ NAV LT Instrument-, Navigation (Position) Light AV/CDU/FAN Avionic-, CDU-Cooling Fans AVIONIC BUS Avionic Bus AV CONT./AP.
Page 27 DA 42 AFM General LH BUS: ALT.LH LH Alternator BATT Battery RH BUS: BATT Battery ALT.RH RH Alternator RH ENG ECU BUS: ECU BUS RH ECU Bus ECU B RH ECU B ECU A RH ECU A (g) Equipment ELT:...
Page 28 General DA 42 AFM (i) Miscellaneous ACG: Austro Control GmbH (formerly BAZ, Federal Office of Civil Aviation) ATC: Air Traffic Control CFRP: Carbon Fiber Reinforced Plastic EASA: European Aviation Safety Agency EPU: External Power Unit GIA: Garmin Integrated Avionics GFRP:...
Page 29: 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 30 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 - 16 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E...
Page 31: 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 32: Three-View Drawing
General DA 42 AFM 1.7 THREE-VIEW DRAWING Page 1 - 18 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E...
Page 33: 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 34: Source Documentation
General DA 42 AFM (b) RNAV (GPS) Approaches - The G1000 GPS meets the requirements of AC 20-138(A) for GPS based RNAV approaches. This includes RNAV approaches labeled as RNAV (GPS), provided GPS sensor data is valid. (c) The systems meets RNP5 airspace (BRNAV) requirements of AC 90-96 and in accordance with AC 20-138A, EASA AMC 20-4, and FAA Order 8110.60 for oceanic...
Page 35: 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 36 General DA 42 AFM Intentionally left blank. Page 1 - 22 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E...
Page 37 DA 42 AFM Operating Limitations CHAPTER 2 OPERATING LIMITATIONS Page INTRODUCTION ........2-3 AIRSPEED .
Page 38 Operating Limitations DA 42 AFM 2.16 OTHER LIMITATIONS ....... . . 2-26 2.16.1 FUEL TEMPERATURE .
Page 39: Introduction
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 power-plants, standard systems and standard equipment. The limitations included in this Chapter are approved.
Page 40: Airspeed
Operating Limitations DA 42 AFM 2.2 AIRSPEED Airspeed Remarks Maneuvering above 1542 kg 126 KIAS Do not make full or abrupt speed (3400 lb) control surface movement above this speed. up to 1542 kg 120 KIAS (3400 lb) Max. flaps...
Page 41: Airspeed Indicator Markings
DA 42 AFM Operating Limitations 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 42: Power-Plant Limitations
Operating Limitations DA 42 AFM 2.4 POWER-PLANT LIMITATIONS a) Number of engines b) Engine manufacturer : Thielert Aircraft Engines c) Engine designation : TAE 125-01 Centurion 1.7 (P/N see Equipment List in Chapter 6) d) RPM limitations (shown as propeller RPM)
Page 43 DA 42 AFM Operating Limitations k) Coolant temperature Minimum -32 °C Maximum : 105 °C l) Voltage Minimum : 24.1 V Maximum : 32.0 V m) Amperage Maximum : 60 A n) Propeller manufacturer : mt-Propeller o) Propeller designation : MTV-6-A-C-F/CF 187-129...
Page 44 Operating Limitations DA 42 AFM CAUTION If the coolant or gearbox oil level is low, the reason must be determined and the problem must be corrected by authorized personnel. v) Maximum restart altitude 6000 ft w) Restart airspeed 80 to 120 KIAS Page 2 - 8 Rev.
Page 45: Engine Instrument Markings
DA 42 AFM Operating Limitations 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the table below: Indi- Yellow Green Yellow cation arc/bar arc/bar arc/bar arc/bar arc/bar lower caution normal caution upper prohibited range...
Page 46: 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 includes a detailed description of the alerts.
Page 47 DA 42 AFM Operating Limitations Warning alerts Meaning / Cause (red) L/R ENG FIRE Left / Right engine fire detected. L/R STARTER Left / Right engine starter is engaged. DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed and locked.
Page 48 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)
Page 49: Other Warning Alerts
DA 42 AFM Operating Limitations Color and significance of the advisory alerts on the G1000 advisory alerts Meaning / Cause (white) L/R GLOW ON Left / Right engine glow plug active. L/R FUEL XFER Fuel transfer from auxiliary to main tank is in progress.
Page 50: Mass (Weight)
Operating Limitations DA 42 AFM 2.7 MASS (WEIGHT) Value Mass (Weight) Minimum flight mass 1250 kg 2756 lb Maximum take-off mass MÄM 42-088 not carried out 1700 kg 3748 lb MÄM 42-088 carried out 1785 kg 3935 lb Maximum zero fuel mass...
Page 51: Center Of Gravity
DA 42 AFM Operating Limitations 2.8 CENTER OF GRAVITY Datum Plane The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and in front of the airplane as seen from the direction of flight. The airplane’s longitudinal axis is parallel with the floor of the nose baggage compartment.
Page 52: Approved Maneuvers
Operating Limitations DA 42 AFM 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 53: Maneuvering Load Factors
DA 42 AFM Operating Limitations 2.10 MANEUVERING LOAD FACTORS at v at v with flaps in APP or LDG position Positive Negative -1.52 WARNING Exceeding the maximum structural load factors will lead to overstressing of the airplane. CAUTION Exceeding the maximum powerplant load factors and time limits listed below will lead to a L/R OIL PRES warning.
Page 54: Operating Altitude
Operating Limitations DA 42 AFM 2.11 OPERATING ALTITUDE The maximum operating altitude is 18,000 ft (5,486 m) pressure altitude. 2.12 FLIGHT CREW Minimum crew 1 (one person) Maximum number of occupants 4 (four persons) 2.13 KINDS OF OPERATION Provided that national operational requirements are met, the following kinds of operation are approved: •...
Page 55 DA 42 AFM Operating Limitations for daytime VFR in addition in addition for night VFR flights for IFR flights flights Flight & airspeed indicator vertical speed second airspeed naviga- (on G1000 PFD or indicator (VSI) indicator (both, on tion backup)
Page 56 Operating Limitations DA 42 AFM for daytime VFR in addition in addition for night VFR flights for IFR flights flights lighting position lights strobe lights (anti collision lights) landing light instrument lighting flood light flashlight other stall warning system Pitot heating system...
Page 57: Fuel
DA 42 AFM Operating Limitations 2.14 FUEL Approved fuel grades JET A-1 (ASTM 1655) only if MÄM 42-037 is carried out: Diesel (EN590) CAUTION Limitations for operation in the following countries: Malaysia: JET A-1 (ASTM 1655) only. Use of Diesel fuel is NOT approved.
Page 58: Limitation Placards
Operating Limitations DA 42 AFM 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 59 DA 42 AFM Operating Limitations On the instrument panel, next to the fuel quantity indication: (a) Standard Tank: (b) Auxiliary Tank (if installed): max. usable fuel max. usable main tank: fuel: 2 x 25 US gal 2 x 25 US gal max.
Page 60 Operating Limitations DA 42 AFM In each cowling, on the door for the oil filler neck: Shell Helix Ultra 5W30 synth. API SL/CF or see AFM Next to the flap selector switch: Flaps 137 KIAS 111 KIAS In the cockpit, on the left fuselage sidewall: Page 2 - 24 Rev.
Page 61 DA 42 AFM Operating Limitations Next to the cockpit 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 62: Other Limitations
Operating Limitations DA 42 AFM 2.16 OTHER LIMITATIONS 2.16.1 FUEL TEMPERATURE JET A-1: 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 carried out.
Page 63: Emergency Switch
DA 42 AFM Operating Limitations 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 64: Garmin G1000 Avionics System
Operating Limitations DA 42 AFM 2.16.6 GARMIN G1000 AVIONICS SYSTEM 1. The Garmin G1000 Cockpit Reference Guide, P/N 190-00406-00, dated September 2004 or later appropriate revision 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 65 DA 42 AFM Operating Limitations NOTE The database version is displayed on the MFD power-up page immediately after system power-up must acknowledged. The remaining system software versions can be verified on the AUX group sub-page 5, "AUX - SYSTEM STATUS".
Page 66 Operating Limitations DA 42 AFM 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 67 DA 42 AFM Operating Limitations NOTE In some areas, datums other than WGS-84 or NAD-83 may be used. If the G1000 is authorized for use by the appropriate Airworthiness Authority, the required geodetic datum must be set in the G1000 prior to its use for navigation.
Page 68: Smoking
Operating Limitations DA 42 AFM 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. Page 2 - 32 Rev. 4 30-Nov-2005...
Page 69 Emergency DA 42 AFM Procedures CHAPTER 3 EMERGENCY PROCEDURES Page INTRODUCTION ........3-4 3.1.1 GENERAL .
Page 70 Emergency DA 42 AFM Procedures G1000 FAILURES ........3-13 3.4.1 NAVIGATION INFORMATION FAILURE .
Page 71 Emergency DA 42 AFM Procedures FAILURES IN THE ELECTRICAL SYSTEM ....3-42 3.7.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . . 3-42 3.7.2 HIGH CURRENT .
Page 72: Introduction
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 73: Certain Airspeeds In Emergencies
Emergency DA 42 AFM Procedures 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event One engine inoperative minimum 68 KIAS control speed (Air) v One engine inoperative speed for 82 KIAS best rate of climb v 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 74: 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 75: L/R Oil Temp
Emergency DA 42 AFM Procedures 3.2.3 L/R OIL TEMP Left / Right engine oil temperature is in the upper red L/R OIL TEMP range (too high / above 140 °C). Oil temperatures above the limit value of 140 °C can lead to a total loss of power due to engine failure.
Page 76: L/R Gbox Temp
Emergency DA 42 AFM Procedures 3.2.5 L/R GBOX TEMP Left / Right engine gearbox temperature is in the L/R GBOX TEMP upper red range (too high / above 120 °C). Gearbox temperatures above the limit value of 120 °C can lead to a total loss of power due to engine failure.
Page 77: 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...
Page 78: L/R Starter
Emergency DA 42 AFM Procedures 3.2.9 L/R STARTER Left / Right engine starter is engaged L/R STARTER 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 79: 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 80: Altitude Fail
Emergency DA 42 AFM Procedures 3.3.5 ALTITUDE FAIL ALTITUDE FAIL The display system is not receiving altitude input from the air data computer; accompanied by a red X through the altimeter display. Revert to the standby altimeter. 3.3.6 VERT SPEED FAIL...
Page 81: 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 3.4.3 AHRS FAILURE...
Page 82: Air Data Computer (Adc) Failure
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 83: Warning/Caution Annunciators
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 84: One Engine Inoperative Procedures
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 may result. Refer to Chapter 5, PERFORMANCE for one engine inoperative performance data.
Page 85: Engine Troubleshooting
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 86 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 the affected engine's fuel selector to CROSSFEED.
Page 87 Emergency DA 42 AFM Procedures NOTE If resetting the circuit breakers has restored engine power land as soon as possible. If the engine power could not be restored by following the procedure of this section prepare for 3.5.6 - ENGINE FAILURES IN FLIGHT and land as soon as possible.
Page 88 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 89 Emergency DA 42 AFM Procedures 3.5.4 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT NOTE Restarting the engine in flight is possible at altitudes below 6000 ft pressure altitude. 1. Airspeed ......80 KIAS to 120 KIAS 2.
Page 90 Emergency DA 42 AFM Procedures In case of a failed restart you may, depending on the situation, proceed with 3.5.2 - ENGINE TROUBLESHOOTING. 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.
Page 91 Emergency DA 42 AFM Procedures 3.5.5 ENGINE FAILURE DURING TAKEOFF a) Engine failure during ground roll - abort takeoff 1. POWER lever ......IDLE / BOTH 2.
Page 92 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 takeoff & land straight ahead, turning to avoid obstacles If the remaining runway / surface is inadequate:...
Page 93 Emergency DA 42 AFM Procedures 6. Engine ......secure according to 3.5.3 - ENGINE SECURING (FEATHERING) PROCEDURE Continue according to Section 3.5.9 - FLIGHT WITH ONE ENGINE INOPERATIVE and...
Page 94 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 68 KIAS should be avoided as a sudden engine failure can lead to loss of control.
Page 95: Engine Securing (Feathering) Procedure
Emergency DA 42 AFM Procedures Establish minimum / zero sideslip condition. (approx. half ball towards good engine; 3° to 5° bank) 5. Inoperative engine ....Secure according to 3.5.3 -...
Page 96 Emergency DA 42 AFM Procedures (b) Engine Failure during Initial Climb at Airspeeds above vmCA 68 KIAS 1. Rudder ......maintain directional control 2.
Page 97 Emergency DA 42 AFM Procedures (c) Engine Failure during Flight 1. Rudder ......maintain directional control 2.
Page 98: Landing With One Engine Inoperative
Emergency DA 42 AFM Procedures 3.5.7 LANDING WITH ONE ENGINE INOPERATIVE Preparation: 1. Safety harnesses ..... check fastened & tightened 2.
Page 99 Emergency DA 42 AFM Procedures at 1785 kg (3935 lb) ....86 KIAS (v /FLAPS UP) 82 KIAS (v /FLAPS APP) 78 KIAS (v...
Page 100 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 101 Emergency DA 42 AFM Procedures If a positive rate of climb cannot be established: - Land so as to keep clear of obstacles with the landing gear extended. If time allows the following steps can reduce the risk of fire in an event of collision with obstacles after touchdown: 19.
Page 102: Flight With One Engine Inoperative
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 103: Landing Gear System Failures
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 104 Emergency DA 42 AFM Procedures With the landing gear extended and at aft CG-locations, with flaps up and full power applied, the aircraft will easily recover from sideslip if the trim is set to neutral (normal procedure). Otherwise it may require corrective action with a moderate amount of rudder input.
Page 105: Manual Extension Of The Landing Gear
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 106 Emergency DA 42 AFM Procedures Manual landing gear extension procedure: 5. Gear selector ......select DOWN 6. Manual gear extension handle ... pull out...
Page 107: Landing With Gear Up
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 108 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 109: Landing With Defective Brakes
Emergency DA 42 AFM Procedures 3.6.5 LANDING WITH DEFECTIVE BRAKES Consider the greater rolling distance. Safety harness ......check fastened and tightened...
Page 110: Failures In The Electrical System
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 111: High Current
Emergency DA 42 AFM Procedures 3.7.2 HIGH CURRENT If high current is indicated on the G1000: 1. Circuit breakers ..... . check 2.
Page 112: Smoke And Fire
Emergency DA 42 AFM Procedures 3.8 SMOKE AND FIRE 3.8.1 ENGINE FIRE ON GROUND 1. ENGINE MASTER ....both OFF 2. FUEL SELECTOR ..... both OFF 3.
Page 113: Engine Fire In Flight
Emergency DA 42 AFM Procedures 3.8.3 ENGINE FIRE IN FLIGHT 1. Cabin heat & Defrost ....OFF Proceed according to 3.5.6 ENGINE FAILURES IN FLIGHT and shut down the engine according to 3.5.3 ENGINE SECURING (FEATHERING) PROCEDURE.
Page 114: Electrical Fire On Ground
Emergency DA 42 AFM Procedures 3.8.4 ELECTRICAL FIRE ON GROUND 1. ELECT. MASTER ..... OFF if the engine is running: 2.
Page 115: Electrical Fire In Flight
Emergency DA 42 AFM Procedures 3.8.5 ELECTRICAL FIRE IN FLIGHT 1. EMERGENCY SWITCH ....ON, if installed 2. AVIONIC MASTER ....OFF 3.
Page 116: 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 117: Unlocked Doors
Emergency DA 42 AFM Procedures 3.9.2 UNLOCKED DOORS 1. Airspeed ......reduce 2. Canopy ......check visually if closed 3.
Page 118: Defective Propeller Rpm Regulating System
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 119 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 120: Unintentional Flight Into Icing
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 121: Fuel Supply Failure
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 122: Recovery From An Unintentional Spin
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 123 Emergency DA 42 AFM Procedures when rotation has stopped: 6. Rudder ......neutral 7.
Page 124 Emergency DA 42 AFM Procedures 3.9.7 EMERGENCY DESCENT 1. FLAPS ......UP 2.
Page 125 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 126 Normal Operating DA 42 AFM Procedures 4A.6.14 SHUT-DOWN ....... . 4A-37 4A.6.15 PARKING .
Page 127: 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 128 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 129: 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 4A.3.3 L/R FUEL XFER...
Page 130: 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 131: Daily Check
Normal Operating DA 42 AFM Procedures 4A.5 DAILY CHECK Before the first flight of a day it must be ensured that the following functions are operable without failure. * On-condition check of the canopy, the side door and the baggage compartment doors for cracks and major scratches.
Page 132 Normal Operating DA 42 AFM Procedures Center console: FUEL SELECTOR ..... check ON POWER Lever ......check condition, freedom of...
Page 133 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 134 Normal Operating DA 42 AFM Procedures g) Control stick ......pull fully aft / hold at backstop h) FLAPS .
Page 135 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 136 Normal Operating DA 42 AFM Procedures 2. Left engine nacelle: a) 3 air inlets / 2 air outlets ....clear b) Engine oil level ..... . . check dipstick (inspection hole in the upper cowling) c) Gearbox oil level .
Page 137 Normal Operating DA 42 AFM Procedures Nacelle underside ..... check for excessive contamination particularly by oil, fuel, and other fluids Auxiliary tank vent outlet on lower surface .
Page 138 Normal Operating DA 42 AFM Procedures Position light, strobe light (ACL) ..visual inspection k) Tie-down ......check, clear Aileron and linkage .
Page 139 Normal Operating DA 42 AFM Procedures 6. Fuselage, right side: a) Fuselage skin ......visual inspection b) Rear window ......visual inspection c) Canopy, right side .
Page 140 Normal Operating DA 42 AFM Procedures e) Tank filler ......visual inspection, check closed f) Pitot probe .
Page 141 Normal Operating DA 42 AFM Procedures e) Gascolator / air inlet ....drain off to check for water and sediment (drain until no water comes out) / clear f) Venting pipe .
Page 142 Normal Operating DA 42 AFM Procedures 10. Front fuselage and nose landing gear: a) Left and right front baggage door ..visual inspection, closed & locked b) Nose landing gear strut ....visual inspection, sufficient height (typical visible length of bare piston: at least 15 cm/5.9")
Page 143: 6.2 Before Starting Engine
Normal Operating DA 42 AFM Procedures 4A.6.2 BEFORE STARTING ENGINE 1. Pre-flight inspection ....complete 2. Passengers ......instructed...
Page 144 Normal Operating DA 42 AFM Procedures 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. Should the pump continue to operate continuously or periodically, terminate flight preparation.
Page 145: 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 146 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 147: 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 148: 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 149: 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 3.
Page 150 Normal Operating DA 42 AFM Procedures NOTE The following test sequence can be executed for both engines simultaneously, or in sequence. FADEC test sequence: CAUTION If the „L/R ECU A/B FAIL“ do not illuminate and extinguish during the test sequence there is a malfunction in the engine control system.
Page 151 Normal Operating DA 42 AFM Procedures Annunciations in the following sequence: 3. ECU A/B FAIL LIGHTS ....ON 4. Propeller RPM ..... . . increase 5.
Page 152 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 153 Normal Operating DA 42 AFM Procedures WARNING If the airplane is operated with Diesel fuel or a blend of Diesel fuel with JET A-1 (only approved if MÄM 42-037 is carried out), or if the fuel grade is unknown, the fuel temperature must be in the green range before take-off.
Page 154: 6.7 Take-Off
Normal Operating DA 42 AFM Procedures 4A.6.7 TAKE-OFF 1. Transponder ......as required 2. POWER lever ......MAX...
Page 155 Normal Operating DA 42 AFM Procedures when safe climb is established: 7. LANDING GEAR ..... . apply brakes; UP, check unsafe light off...
Page 156: 6.8 Climb
Normal Operating DA 42 AFM Procedures 4A.6.8 CLIMB Initial climb check 1. Landing light ......OFF / as required 2.
Page 157: 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 158: 6.10 Descent
Normal Operating DA 42 AFM Procedures 2. Transfer the second half of the auxiliary fuel: Repeat the procedure described above. NOTE Transfer the fuel from the auxiliary tanks to the main tanks as soon as possible. The fuel in the auxiliary tanks must be transferred to the main tanks to become available for the current flight mission.
Page 159: 6.11 Approach & Landing
Normal Operating DA 42 AFM Procedures 4A.6.11 APPROACH & LANDING NOTE If the landing mass exceeds 1700 kg (3748 lb), the landing constitutes an abnormal operating procedure. Refer to Section 4B.8. Approach: 1. Safety harnesses ..... check fastened & tightened 2.
Page 160 Normal Operating DA 42 AFM Procedures 4A.6.12 GO-AROUND 1. POWER lever ......MAX 2. Airspeed ......min. 82 KIAS 3.
Page 161 Normal Operating DA 42 AFM Procedures 4A.6.14 SHUT-DOWN 1. Parking brake ......set 2. POWER lever ......IDLE for 2 minutes 3.
Page 162 Normal Operating DA 42 AFM Procedures 4A.6.15 PARKING 1. Parking brake ......release, use chocks 2. Airplane ......moor, if unsupervised for extended period 3.
Page 163 Normal Operating DA 42 AFM Procedures 4A.6.19 REFUELING CAUTION Before refueling, the airplane must be connected to electrical ground. Grounding points: unpainted areas on steps, left and right. Refer to Section 2.14 for approved fuel grades. NOTE If the airplane is operated with Diesel fuel (only approved if MÄM 42-037 is carried out), additional temperature limitations...
Page 164 Normal Operating DA 42 AFM Procedures 4A.6.20 FLIGHT AT HIGH ALTITUDE At high altitudes the provision of oxygen for the occupants is necessary. Legal requirements for the provision of oxygen should be adhered to. Also see Section 2.11 - OPERATING ALTITUDE.
Page 165 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 166 Abnormal Operating DA 42 AFM Procedures 4B.4.12 STICK LIMIT ....... . . 4B-25 4B.4.13 RAIM UNAVAIL .
Page 167 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 168 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 169: 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 170: 3.2 Coolant Temperature
Abnormal Operating DA 42 AFM Procedures 4B.3.2 COOLANT TEMPERATURE (a) High coolant temperature Check G1000 for L/R COOL LVL caution message (low coolant level) L/R COOL LVL caution message not displayed: during climb: Reduce power on affected engine by 10 % or more as required.
Page 171 Abnormal Operating DA 42 AFM Procedures L/R COOL LVL caution message displayed: Reduce power on affected engine. Expect loss of coolant. WARNING A further increase in coolant temperature must be expected. Prepare for an engine failure in accordance with 3.5.6 - ENGINE FAILURES IN FLIGHT.
Page 172: 3.3 Oil Temperature
Abnormal Operating DA 42 AFM Procedures 4B.3.3 OIL TEMPERATURE (a) High oil temperature Check oil pressure. if the oil pressure is outside of the green range (lower limit): Reduce power on affected engine. Expect loss of engine oil. WARNING A further increase in oil temperature must be expected.
Page 173 Abnormal Operating DA 42 AFM Procedures (b) Low oil temperature NOTE During an extended descent from high altitudes with a low power setting oil temperature may decrease. In this case an increase in power can help. Increase power. Reduce airspeed.
Page 174: 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 175 Abnormal Operating DA 42 AFM Procedures (b) Low oil pressure Reduce power on affected engine. Expect loss of oil. WARNING Land at the nearest suitable airfield. Prepare for an engine failure in accordance with 3.5.6 - ENGINE FAILURES IN FLIGHT.
Page 176: 3.5 Gearbox Temperature
Abnormal Operating DA 42 AFM Procedures 4B.3.5 GEARBOX TEMPERATURE High gearbox temperature Reduce power on affected engine. Increase airspeed. CAUTION At high ambient temperature conditions and / or at low airspeeds with high power settings, it can be assumed that there is no technical defect in the gearbox and that the above mentioned procedure will decrease the temperature(s).
Page 177: 3.6 Fuel Temperature
Abnormal Operating DA 42 AFM Procedures 4B.3.6 FUEL TEMPERATURE (a) High fuel temperature Reduce power on affected engine. Increase airspeed. CAUTION At high ambient temperature conditions and / or at low airspeeds with high power settings and low fuel quantities, it can be assumed that the above mentioned procedure will decrease the temperature(s).
Page 178: 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 179: 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 Doc.
Page 180: 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 181: 4.3 L/R Ecu B Fail
Abnormal Operating DA 42 AFM Procedures 4B.4.3 L/R ECU B FAIL L/R ECU B FAIL * Left / Right engine ECU B has failed * is being tested during FADEC test procedure before take-off check. (a) 'ECU B' caution on the ground Terminate flight preparation.
Page 182: 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 183: 4.5 Low Voltage Caution (Low Volts)
Abnormal Operating DA 42 AFM Procedures 4B.4.5 LOW VOLTAGE CAUTION (LOW VOLTS) Left / Right engine bus voltage is too low (less than L/R VOLTS LOW 25 volts) Possible reasons are: - A fault in the power supply. - RPM too low.
Page 184: 4.6 L/R Altn Fail
Abnormal Operating DA 42 AFM Procedures 4B.4.6 L/R ALTN FAIL L/R ALTN FAIL Left / Right engine alternator has failed. (a) One alternator failed 1. ALTERNATOR ..... . . OFF / affected side 2.
Page 185: 4.7 L/R Cool Lvl
Abnormal Operating DA 42 AFM Procedures 4B.4.7 L/R COOL LVL L/R COOL LVL Left / Right engine coolant level is low. 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 186: 4.8 Pitot Fail / Ht Off
Abnormal Operating DA 42 AFM Procedures 4B.4.8 PITOT FAIL / HT OFF PITOT FAIL Pitot heating system has failed. Pitot heating system is OFF. PITOT HT OFF 1. PITOT HEAT ......check ON / as required...
Page 187: 4.9 Stall Ht Fail / Off
Abnormal Operating DA 42 AFM Procedures 4B.4.9 STALL HT FAIL / OFF STALL HT FAIL Stall warning heat has failed. Stall warning heat is OFF. STALL HT OFF 1. PITOT HEAT ......check ON / as required...
Page 188: 4.10 L/R Fuel Transfer Fail
Abnormal Operating DA 42 AFM Procedures 4B.4.10 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 liters).
Page 189: 4.12 Stick Limit
Abnormal Operating DA 42 AFM Procedures 4B.4.12 STICK LIMIT STICK LIMIT Control stick limiting system (variable elevator stop) has 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 190: 4.13 Raim Unavail
Abnormal Operating DA 42 AFM Procedures 4B.4.13 RAIM UNAVAIL RAIM (Receiver Autonomous Integrity Monitor) is not INTEG available. RAIM not available (a) Enroute, oceanic, terminal, or initial approach phase of flight If the "RAIM UNAVAIL" annunciation is displayed in the enroute, oceanic, terminal, or...
Page 191: 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 192: Failures In Hydraulic System
Abnormal Operating DA 42 AFM Procedures 4B.6 FAILURES IN HYDRAULIC SYSTEM 4B.6.1 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 193: Starting Engine With External Power
Abnormal Operating DA 42 AFM Procedures 4B.7 STARTING ENGINE WITH EXTERNAL POWER 4B.7.1 BEFORE STARTING ENGINE 1. Pre-flight inspection ....complete 2. Passengers ......instructed...
Page 194 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 195: 7.2 Starting Engine
Abnormal Operating DA 42 AFM Procedures 4B.7.2 STARTING ENGINE 1. Strobe lights (ACL) ....ON 2. ELECT. MASTER ..... ON 3.
Page 196 Abnormal 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 197: Landing With High Landing Mass
Abnormal Operating DA 42 AFM Procedures 4B.8 LANDING WITH HIGH LANDING MASS CAUTION Damage of the landing gear can result from a hard landing with a flight mass above the maximum landing mass. NOTE If MÄM 42-088 is carried out, a landing with a mass between 1700 kg (3748 lb) and 1785 kg (3935 lb) is admissible.
Page 198 Abnormal Operating DA 42 AFM Procedures Intentionally left blank. Page 4B - 34 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 199 DA 42 AFM Performance CHAPTER 5 PERFORMANCE Page INTRODUCTION ........5-2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS .
Page 200: 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 201: 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. 4 30-Nov-2005 Page 5 - 3...
Page 202 Performance DA 42 AFM Page 5 - 4 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 203 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 5...
Page 204: 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 205: International Standard Atmosphere
DA 42 AFM Performance 5.3.3 INTERNATIONAL STANDARD ATMOSPHERE Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 7...
Page 206: 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 207: 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. 4 30-Nov-2005 Page 5 - 9...
Page 208: Take-Off Distance
Performance DA 42 AFM 5.3.6 TAKE-OFF DISTANCE Conditions: - Power lever ......both MAX @ 2300 RPM - Flaps .
Page 209 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 take-off distance. CAUTION The figures in the following NOTE are typical values. On wet ground or wet soft grass covered runways the take-off roll may become significantly longer than stated below.
Page 210 Performance DA 42 AFM Page 5 - 12 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 211 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 13...
Page 212 Performance DA 42 AFM Page 5 - 14 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 213 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 15...
Page 214: Climb Performance - Take-Off Climb
Performance DA 42 AFM 5.3.7 CLIMB PERFORMANCE - TAKE-OFF CLIMB Conditions: - Power lever ......both MAX @ 2300 RPM - Flaps .
Page 215 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 17...
Page 216 Performance DA 42 AFM Page 5 - 18 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 217: Climb Performance - Cruise Climb
DA 42 AFM Performance 5.3.8 CLIMB PERFORMANCE - CRUISE CLIMB Conditions: - Power lever ......both MAX @ 2300 RPM - Flaps .
Page 218 Performance DA 42 AFM Page 5 - 20 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 219 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 21...
Page 220: One Engine Inoperative Climb Performance
Performance DA 42 AFM 5.3.9 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE Conditions: - Remaining Engine (RH) ....MAX @ 2300 RPM - Dead Engine ......feathered and secured - Flaps .
Page 221 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 23...
Page 222 Performance DA 42 AFM Page 5 - 24 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 223: Cruising (True Airspeed Tas)
DA 42 AFM Performance 5.3.10 CRUISING (TRUE AIRSPEED TAS) Conditions: - Engines ......all operating - Power lever .
Page 224 Performance DA 42 AFM Page 5 - 26 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 225: Landing Distance
DA 42 AFM Performance 5.3.11 LANDING DISTANCE Conditions: - Power lever ....both IDLE - Flaps ....LDG - Runway .
Page 226 Performance DA 42 AFM 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 227 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 29...
Page 228 Performance DA 42 AFM Page 5 - 30 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 229 DA 42 AFM Performance Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 31...
Page 230 Performance DA 42 AFM Page 5 - 32 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E...
Page 231: Gradient Of Climb On Go-Around
DA 42 AFM Performance 5.3.12 GRADIENT OF CLIMB ON GO-AROUND Conditions: - Power lever ......both MAX @ 2300 RPM - Flaps .
Page 232 Performance DA 42 AFM 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 233 DA 42 AFM Mass and Balance CHAPTER 6 MASS AND BALANCE Page INTRODUCTION ........6-2 DATUM PLANE .
Page 234: 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 235: 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. 6.2 DATUM PLANE The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and in front of the airplane as seen from the direction of flight.
Page 236: 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 237 DA 42 AFM Mass and Balance MASS AND BALANCE REPORT ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' '...
Page 238: 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 239 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 240 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 241 DA 42 AFM Mass and Balance 6.4.2 LOADING DIAGRAM Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 6 - 9...
Page 242 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 243 DA 42 AFM Mass and Balance DA 42 (Example) Your DA 42 Mass Moment Mass Moment CALCULATION OF [kg] [kgm] [kg] [kgm] LOADING CONDITION [lb] [in.lb] [lb] [in.lb] 1. Empty mass (from Mass and 1250 2937.5 Balance Report) 2756 254,965 2.
Page 244 Mass and Balance DA 42 AFM The CG's shown in the following diagrams are those from the example in Section 6.4.3 'CALCULATION OF LOADING CONDITION', rows 8 and 11. 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE Page 6 - 12 Rev. 4 30-Nov-2005 Doc.
Page 245 DA 42 AFM Mass and Balance 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 246 Mass and Balance DA 42 AFM 6.4.5 PERMISSIBLE MOMENT RANGE The flight mass moments shown in the diagram are those from the example in Table 6.4.3 (a) 'CALCULATION OF LOADING CONDITION', rows 8 and 11. Page 6 - 14 Rev. 4 30-Nov-2005 Doc.
Page 247 DA 42 AFM Mass and Balance 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 248 Mass and Balance DA 42 AFM Airplane Serial No.: Registration: Date: inst‘d Description Type Part No. Manufacturer Emergency Battery D60-2560-91-00 Diamond Aircraft External Power Connector DA4-2443-10-00 Diamond Aircraft LH Alternator 02-7150-55110R2 Thielert RH Alternator 02-7150-55110R2 Thielert LH Alternator Regulator 02-7150-55112R2...
Page 249 DA 42 AFM Mass and Balance Airplane Serial No.: Registration: Date: Description Type Part No. Manufacturer inst‘d INDICATING / REC. SYSTEM Primary Flight Display (PFD) GDU 1040 011-00972-02 Garmin Multi Function Display (MFD) GDU 1040 011-00972-02 Garmin LANDING GEAR Main landing gear LH...
Page 250 Mass and Balance DA 42 AFM Airplane Serial No.: Registration: Date: Description Type Part No. Manufacturer inst‘d COMMUNICATION / NAVIGATION COMM #1 antenna DMC63-1/A COMM #2 antenna DMC63-2 Audio Panel / Marker / ICS GMA 1347 011-00809-00 Rev. 3 Garmin...
Page 251 DA 42 AFM Mass and Balance Airplane Serial No.: Registration: Date: Description Type Part No. Manufacturer inst‘d ENGINE LH Engine TAE-125-01 125-01-(017)-( ) Thielert RH Engine TAE-125-01 125-01-(017)-( ) Thielert LH ENGINE CONTROL UNIT 02-7610-55003R(*) Thielert ECU Firmware 02-7610-55101R( )*...
Page 252 Mass and Balance DA 42 AFM Airplane Serial No.: Registration: Date: Description Type Part No. Manufacturer inst‘d ICE PROTECTION SYSTEM porous panel, outer wing, LH 12102-21 CAV Aerospace porous panel, outer wing, RH 12102-22 CAV Aerospace porous panel, center wing, LH...
Page 253 DA 42 AFM Airplane Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Page INTRODUCTION ........7-3 AIRFRAME .
Page 254 Airplane Description DA 42 AFM 7.11 PITOT-STATIC SYSTEM ....... 7-61 7.12...
Page 255: 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 256: 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 257 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 258 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 259 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 260 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 261 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 over-rotating, the trim wheel incorporates a friction device. A mark on the wheel shows the take-off (T/O) position.
Page 262: Instrument Panel
Airplane Description DA 42 AFM 7.4 INSTRUMENT PANEL Page 7 - 10 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E...
Page 263 *) Designations and abbreviations used to identify the circuit breakers are explained in Section 1.5 DEFINITIONS AND ABBREVIATIONS. NOTE The figure on previous page shows the typical DA 42 installation position for the equipment. The actual installation may vary due to the approved equipment version (e.g., there is no oxygen system approved at present).
Page 264 Airplane Description DA 42 AFM 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 265: Landing Gear
DA 42 AFM Airplane Description 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 266 Airplane Description DA 42 AFM 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 267 Airplane Description 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 268 Airplane Description DA 42 AFM 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 269 DA 42 AFM Airplane Description 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 270 Airplane Description DA 42 AFM 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 271: Seats And Safety Harnesses
DA 42 AFM Airplane Description 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 the maintenance and inspection of the underlying controls. Covers on the control sticks prevent loose objects from falling into the area of the controls.
Page 272: Canopy, Rear Door, And Cabin Interior
Airplane Description DA 42 AFM 7.8 CANOPY, REAR DOOR, AND CABIN INTERIOR Front canopy The front canopy is closed by pulling down on the canopy frame, following which it is locked by means of a handle on the left hand side of the frame. On locking, steel bolts lock into mating holes in polyethylene blocks.
Page 273 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 274: Power Plant
Airplane Description DA 42 AFM 7.9 POWER PLANT 7.9.1 ENGINES, GENERAL There are two Thielert Aircraft Engines TAE125 installed, which have the following principal specifications: - Liquid-cooled four-cylinder-four-stroke Diesel-cycle engine with wet sump lubrication - In-line construction - Common-rail direct injection - Propeller speed-reducing gear 1:1.69...
Page 275: 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 276 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 277 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 278: 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 279 DA 42 AFM Airplane Description 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. In this case the reduced engine performance should be taken into consideration.
Page 280 Airplane Description DA 42 AFM ECU SWAP There are two ECU SWAP switches, one for each engine. For normal operation both switches are set to AUTOMATIC. Each engine is controlled by its ECU A. In case of a failure of the active engine control unit (ECU) there should be an automatic switch-over to the appropriate ECU B.
Page 281 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 282: 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 7.10.3 - 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 283 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 284: Fuel System
Airplane Description DA 42 AFM 7.9.5 FUEL SYSTEM General TAE 125 return line ENGINE TAE Diesel filter firewall sediment bowl FUSELAGE drain fuel supply cross- fuel selector valves feed check valve lines with capillary aux. fuel vent line tank (op- aux.
Page 285 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 286 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, X-Feed and OFF. During normal operation each engine takes the fuel from the tank on the same side as the engine.
Page 287 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 288 Airplane Description DA 42 AFM With the LH fuel selector valve in cross-feed 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 289 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 liters (1 US gal) of fuel in each wing are unusable, so that a total quantity of 96 liters (25.4 US gal) in each...
Page 290 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 291 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 to Section 4B.4.10, LH/RH FUEL XFER FAIL. The flight plan must be amended accordingly.
Page 292 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 pre-flight inspection. It functions according to the principle of communicating containers.
Page 293 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 294 Airplane Description DA 42 AFM Fuel grade Approved fuel grades are listed in Section 2.14. As the fuel grade is important concerning operating temperature limitations, the pilot must be sure about the fuel grade. Cold Diesel fuel tends to flocculate, which can lead to clogging of the fuel filter. The fuel filter is not heated.
Page 295: 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 296: 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 297: Turbo-Charger System
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 298: Fire Detection System
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 299: Electrical System
DA 42 AFM Airplane Description 7.10 ELECTRICAL SYSTEM Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 47...
Page 300: 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 301 DA 42 AFM Airplane Description The alternator control unit includes a comprehensive set of diagnostic functions that will warn the operator using a caution message (L/R ALTN FAIL) on the G1000 PFD in case of over- or undervoltage as well as a couple of other internal warning levels.
Page 302 Airplane Description DA 42 AFM Hot battery bus: The 'hot battery bus' is directly connected to the 'main'-battery via a 20 A fuse installed in the relay junction box and cannot be disconnected from the 'main'-battery. The 'hot battery bus' provides power to the pilot map/reading light which is protected by its own fuse.
Page 303 DA 42 AFM Airplane Description Consumers The individual consumers (e.g. radio, position lights, etc.) are connected to the appropriate bus via automatic circuit breakers. Designations and abbreviations used to identify the circuit breakers are explained in Section 1.5 DEFINITIONS AND ABBREVIATIONS.
Page 304 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 on-line.
Page 305: Engine Control Unit / Ecu
DA 42 AFM Airplane Description 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 306 Airplane Description DA 42 AFM In accordance with the received signals and a comparison with the programmed characteristic diagrams the necessary inputs are calculated and transmitted by the following signal lines to the engine: - Activation of starter (relay) - Signal for propeller governor pressure valve...
Page 307: Warning, Caution And Advisory Messages
DA 42 AFM Airplane Description 7.10.3 WARNING, CAUTION AND ADVISORY MESSAGES Crew Alerting System (CAS) The G1000 Crew Alerting System (CAS) is designed to provide visual and aural alerts to the flight crew. Alerts are divided into three levels as follows:...
Page 308 Airplane Description DA 42 AFM Alert levels Level Text Color Importance Audible Tone Warning May require Warning chime tone immediate w h i c h r e p e a t s corrective action without delay until acknowledged by the crew...
Page 309 DA 42 AFM Airplane Description 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 310 Airplane Description DA 42 AFM Warning alerts Meaning / Cause WARN This annunciation constitutes a RAIM position warning. The nav deviation bar is removed. Audible warning alerts Warning alerts Meaning / Cause A warning chime tone which repeats without delay is active...
Page 311 DA 42 AFM Airplane Description 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 312 Airplane Description DA 42 AFM 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 313: Pitot-Static 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 314: Garmin G1000 Integrated Avionics System
Airplane Description DA 42 AFM 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 Multi-Function 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 315: Primary Flight Display (Pfd)
DA 42 AFM Airplane Description 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 316 Airplane Description DA 42 AFM The PFD displays the crew alerting (annunciator) system. When a warning or caution message is received, a warning or caution annunciator will flash on the PFD, accompanied by an aural tone. A warning is accompanied by a repeating tone, and a caution is accompanied by a single tone.
Page 317: Multi-Function Display (Mfd)
DA 42 AFM Airplane Description Advisory messages related to G1000 system status are shown in white and are accompanied by a white flashing ADVISORY alert. Refer to the G1000 Pilot's Guide and Cockpit Reference Guide for descriptions of the messages and recommended actions (if applicable).
Page 318: Audio Panel
Airplane Description DA 42 AFM 7.13.4 AUDIO PANEL The audio panel contains traditional transmitter and receiver selectors, as well as an integral intercom and marker beacon system. The marker beacon lights appear on the PFD. In addition, a clearance recorder records the last 2 ½ minutes of received audio.
Page 319 Handling, Care, DA 42 AFM Maintenance CHAPTER 8 AIRPLANE HANDLING, CARE AND MAINTENANCE Page INTRODUCTION ........8-2 AIRPLANE INSPECTION INTERVALS .
Page 320: 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 321: 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 322: Engine Oil Level Check
Handling, Care, DA 42 AFM Maintenance 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 323: Tire Inflation Pressure Check
Handling, Care, DA 42 AFM Maintenance 8.4.4 TIRE INFLATION PRESSURE CHECK 1. Remove the wheel cover (main wheels only). 2. Remove dust cap from valve stem by turning counter-clockwise. 3. Connect tire gauge to valve stem, read pressure. 4. Correct pressure if necessary (nose tire 6.0 bar/87 psi, main tires 4.5 bar/65 psi).
Page 324: Ground Handling / Road Transport
Handling, Care, DA 42 AFM Maintenance 8.5 GROUND HANDLING / ROAD TRANSPORT 8.5.1 GROUND HANDLING For pushing or pulling the airplane on the ground, it is recommended to use the tow bar which is available from the manufacturer. The tow bar is engaged in the appropriate hole in the nose wheel as shown on the picture.
Page 325: Parking
Handling, Care, DA 42 AFM Maintenance CAUTION Towing with towing vehicles is not approved. 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 326 Handling, Care, DA 42 AFM Maintenance Page 8 - 8 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E...
Page 327: 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 328: 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 329: Canopy And Rear Door
Handling, Care, DA 42 AFM Maintenance 8.6.2 CANOPY AND REAR DOOR The canopy, rear door and rear window should be cleaned with 'Plexiklar' or any other acrylic glass detergent if available; otherwise use lukewarm water. Final cleaning should be carried out with a clean piece of chamois-leather or soft cloth. Never rub or polish dry acrylic glass.
Page 330: Ground De-Icing
Handling, Care, DA 42 AFM Maintenance 8.7 GROUND DE-ICING Approved de-icing fluids are: Manufacturer Name Kilfrost TKS 80 Aeroshell Compound 07 AL-5 (DTD 406B) 1. Remove any snow from the airplane using a soft brush. 2. Spray de-icing fluid onto ice-covered surfaces using a suitable spray bottle.
Page 331 DA 42 AFM Supplements CHAPTER 9 SUPPLEMENTS Page INTRODUCTION ........9-2 LIST OF SUPPLEMENTS .
Page 332 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.

Diamond Aircraft 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

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Chapters

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Summary of Contents for Diamond Aircraft DA 42