DA 42 AFM Rev. 4 DA42_Diamond Twin_Flight Manual DA42 Diamond Twin Flight

User Manual: DA42_Diamond-Twin_FlightManual

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FRONT MATTER
1 GENERAL
2 OPERATING LIMITATIONS
3 EMERGENCY PROCEDURES
4A NORMAL OPERATING PROCEDURES
4B ABNORMAL OPERATING PROCEDURES
5 PERFORMANCE
6 MASS AND BALANCE
7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS
8 AIRPLANE HANDLING, CARE AND MAINTENANCE
9 SUPPLEMENTS
- 9.1 Introduction
- 9.2 List of Supplements

Introduction DA 42 AFM

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DA 42 AFM Introduction

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FOREWORD

We congratulate you on the acquisition of your new DIAMOND DA 42 Twin Star.

Skillful operation of an airplane increases both safety and the enjoyment of flying. Please

take the time therefore, to familiarize yourself with your new DIAMOND DA 42.

This airplane may only be operated in accordance with the procedures and operating

limitations of this Airplane Flight Manual.

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.

This document is protected by copyright. All associated rights, in particular those of

translation, reprinting, radio transmission, reproduction by photo-mechanical or similar

means and storing in data processing facilities, in whole or part, are reserved.

N.A. Otto-Strasse 5

A-2700 Wiener Neustadt, Austria

Phone : +43-2622-26700

Fax : +43-2622-26780

E-Mail : office@diamond-air.at

Introduction DA 42 AFM

Page 0 - 2 Rev. 3 15-Oct-2005 Doc. # 7.01.05-E

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 -

• Temporary Revisions,

• updates of the modification level (Section 1.1),

• updated mass and balance information (Section 6.3),

• updates of the Equipment Inventory (Section 6.5), and

• updates of the List of Supplements (Section 9.2)

must be recorded in the following table.

The new or amended text is indicated by a vertical black line at the left hand side of the

revised page, with the revision number and date appearing at the bottom of the page.

If pages are revised which contain information valid for your particular serial number

(modification level of the airplane, weighing data, Equipment Inventory, List of

Supplements), then this information must be transferred to the new pages in hand-writing.

The cover pages of Temporary Revisions, if applicable, are inserted behind the cover

page of this manual; the following pages of the Temporary Revision are inserted in front

of the corresponding pages of this AFM. Temporary Revisions are used to provide

information on systems or equipment until the next 'permanent' Revision of the Airplane

Flight Manual. When a 'permanent' Revision covers a Mandatory or Optional Design

Change Advisory (MÄM or OÄM), then the corresponding Temporary Revision is

superseded. Example: Revision 3 covers OÄM 42-053, therefore the Temporary Revision

TR-OÄM-42-053 is superseded by the 'permanent' Revision 3.

DA 42 AFM Introduction

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Rev.

No. Reason Chap-

ter Page(s) Date of

Revision Approval Verification Date

Inserted Signature

IFR

certification;

corrections

all all except cover

page 1 Dec 2004 2005-196

[Ing.

Andreas

Winkler for

ACG]

MÄM 42-034

(elevator

stop);

OÄM 42-060

(T&B

coordinat.);

Take-off

diagrams

0-3, 0-5,

0-7, 0-8, 0-9

4A-9

4B-25

5-11, 5-12

6-18

7-7

28 Jan 2005

[10 Feb

2005

Dipl.-Ing.

(FH)

Manfred

Reichel

for DAI]

FAA

Certification

MÄM 42-

-062, -070/a,

-079, -080,

-091, -101,

-111/b

(TR-MÄM-

42-111/a),

-115

OÄM 42-

-053, -056,

-057, -059,

-079

Corrections

all all 15 Oct 2005

[25 Oct

2005

Ing.

Andreas

Winkler for

ACG]

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DA 42 AFM Introduction

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0.4 TABLE OF CONTENTS

Chapter

GENERAL

(a non-approved chapter) .......................................... 1

OPERATING LIMITATIONS

(an approved chapter) ............................................. 2

EMERGENCY PROCEDURES

(a non-approved chapter) .......................................... 3

NORMAL OPERATING PROCEDURES

(a non-approved chapter) ......................................... 4A

ABNORMAL OPERATING PROCEDURES

(a non-approved chapter) ......................................... 4B

PERFORMANCE

(a non-approved chapter) .......................................... 5

MASS AND BALANCE / EQUIPMENT LIST

(a non-approved chapter) .......................................... 6

DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS

(a non-approved chapter) .......................................... 7

AIRPLANE HANDLING, CARE AND MAINTENANCE

(a non-approved chapter) .......................................... 8

SUPPLEMENTS ................................................... 9

Introduction DA 42 AFM

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DA 42 AFM General

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CHAPTER 1

GENERAL

Page

1.1 INTRODUCTION .......................................1-2

1.2 CERTIFICATION BASIS ..................................1-3

1.3 WARNINGS, CAUTIONS AND NOTES ......................1-4

1.4 DIMENSIONS ..........................................1-5

1.5 DEFINITIONS AND ABBREVIATIONS .......................1-7

1.6 UNITS OF MEASUREMENT .............................1-15

1.6.1 CONVERSION FACTORS ..........................1-15

1.6.2 CONVERSION CHART LITERS / US GALLONS .........1-17

1.7 THREE-VIEW DRAWING................................1-18

1.8 G1000 AVIONICS SYSTEM ..............................1-19

1.9 SOURCE DOCUMENTATION ............................1-20

1.9.1 ENGINE ........................................1-20

1.9.2 PROPELLER ....................................1-21

1.9.3 AVIONICS SYSTEM ...............................1-21

General DA 42 AFM

Page 1 - 2 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

1.1 INTRODUCTION

This Airplane Flight Manual has been prepared in order to provide pilots and instructors

with all the information required for the safe and efficient operation of the airplane.

The Airplane Flight Manual includes all the data which must be made available to the pilot

according to the JAR-23 requirement. Beyond this, it contains further data and operating

instructions which, in the manufacturer’s opinion, could be of value to the pilot.

This Airplane Flight Manual is valid for all serial numbers. Equipment and modification

level (design details) of the airplane may vary from serial number to serial number.

Therefore, some of the information contained in this manual is applicable depending on

the respective equipment and modification level. The exact equipment of your serial

number is recorded in the Equipment Inventory in Section 6.5. The modification level is

recorded in the following table (as far as necessary for this manual).

Modification Source Installed

New Engine Instrument Markings MÄM 42-101 9 yes 9 no

Increased Take-Off Mass

MÄM 42-088

9 yes 9 no

Use of Diesel fuel

MÄM 42-037

9 yes 9 no

Ice Protection System OÄM 42-053 9 yes 9 no

Ice Protection System

(Known Icing)

OÄM 42-054

9 yes 9 no

Auxiliary Fuel Tanks OÄM 42-056 9 yes 9 no

Removable Fuselage Nose Cone

OÄM 42-077

9 yes 9 no

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 1 - 3

This Airplane Flight Manual must be kept on board the airplane at all times. Its designated

place is the side bag of the forward left seat. The designated place for the Garmin G1000

Cockpit Reference Guide is the bag on the rear side of the forward left seat.

CAUTION

The DA 42 is a twin engine airplane. When the operating

limitations and maintenance requirements are complied with,

it has the high degree of reliability which is required by the

certification basis. Nevertheless, an engine failure is not

completely impossible. For this reason it is highly recom-

mended for flights during the night, on top, under IMC, or

above terrain which is unsuitable for a landing, to select flight

times and flight routes such that reduced performance in case

of single engine operation does not constitute a risk.

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.

General DA 42 AFM

Page 1 - 4 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

1.3 WARNINGS, CAUTIONS AND NOTES

Special statements in the Airplane Flight Manual concerning the safety or operation of

the airplane are highlighted by being prefixed by one of the following terms:

WARNING

means that the non-observation of the corresponding

procedure leads to an immediate or important degradation

in flight safety.

CAUTION

means that the non-observation of the corresponding

procedure leads to a minor or to a more or less long term

degradation in flight safety.

NOTE

draws the attention to any special item not directly related to

safety but which is important or unusual.

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 1 - 5

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 175.3 sq.ft.

Mean aerodynamic chord : 1.271 m 4 ft 2 in

Aspect ratio : 11.06

Dihedral : 5°

Leading edge sweep : 1°

Aileron

Area (total, left + right) : 0.66 m² 7.1 sq.ft.

General DA 42 AFM

Page 1 - 6 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

Wing flaps

Area (total, left + right) : 2.18 m² 23.4 sq.ft.

Horizontal tail

Area : 2.35 m225.3 sq.ft.

Elevator area : 0.66 m² 7.1 sq.ft.

Angle of incidence : -1.1° relative to longitudinal axis of airplane

Vertical tail

Area : 2.43 m² 26.2 sq.ft.

Rudder area : 0.78 m² 8.4 sq.ft.

Landing gear

Track : 2.95 m (9 ft 8 in)

Wheelbase : 1.735 m (5 ft 8 in)

Nose wheel : 5.00-5; 10 PR, 120 mph

Main wheel : 15x6.0-6; 6 PR, 120 mph

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 1 - 7

1.5 DEFINITIONS AND ABBREVIATIONS

(a) Airspeeds

CAS: Calibrated Airspeed. Indicated airspeed, corrected for installation and instrument

errors. CAS equals TAS at standard atmospheric conditions (ISA) at MSL.

KCAS: CAS in knots.

KIAS: IAS in knots.

IAS: Indicated Airspeed as shown on an airspeed indicator.

TAS: True Airspeed. The speed of the airplane relative to the air. TAS is CAS

corrected for errors due to altitude and temperature.

vA: Maneuvering Speed. Full or abrupt control surface movement is not permissible

above this speed.

vFE: Maximum Flaps Extended Speed. This speed must not be exceeded with the

given flap setting.

vLO: Maximum Landing Gear Operating Speed. This speed may not be exceeded

during the extension or retraction of the landing gear.

vLE: Maximum Landing Gear Extended Speed. This speed may not be exceeded

if the landing gear is extended.

vMC: Minimum Control Speed. Minimum speed necessary to be able to control the

airplane in case of one engine inoperative.

vNE: Never Exceed Speed in smooth air. This speed must not be exceeded in any

operation.

General DA 42 AFM

Page 1 - 8 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

vNO: Maximum Structural Cruising Speed. This speed may be exceeded only in

smooth air, and then only with caution.

vS: Stalling Speed, or the minimum continuous speed at which the airplane is still

controllable in the given configuration.

vS0: Stalling Speed, or the minimum continuous speed at which the airplane is still

controllable in the landing configuration.

vS1: Stalling Speed, or the minimum continuous speed at which the airplane is still

controllable with flaps and landing gear retracted.

vSSE: Minimum Control Speed for Schooling. Minimum speed necessary in case of

one engine intentionally inoperative / idle (training purposes).

vx: Best Angle-of-Climb Speed.

vy: Best Rate-of-Climb Speed.

vYSE: Best Rate of-Climb Speed for one engine inoperative.

(b) Meteorological terms

ISA: International Standard Atmosphere. Conditions at which air is identified

as an ideal dry gas. The temperature at mean sea level is 15 °C (59 °F),

air pressure at MSL is 1013.25 hPa (29.92 inHg); the temperature

gradient up to the altitude at which the temperature reaches -56.5 °C

(-69.7 °F) is -0.0065 °C/m (-0.00357 °F/ft), and above this 0 °C/m (0 °F/ft).

MSL: Mean Sea Level.

OAT: Outside Air Temperature.

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 1 - 9

QNH: Theoretical atmospheric pressure at MSL, calculated from the elevation

of the measuring point above MSL and the actual atmospheric pressure

at the measuring point.

Density Altitude:

Altitude in ISA conditions at which the air density is equal to the current

air density.

Indicated Pressure Altitude:

Altitude reading with altimeter set to 1013.25 hPa (29.92 inHg).

Pressure Altitude:

Altitude indicated by a barometric altimeter, which is set to 1013.25 hPa

(29.92 inHg). The Pressure Altitude is the Indicated Pressure Altitude

corrected for installation and instrument errors.

In this Airplane Flight Manual altimeter instrument errors are regarded

as zero.

Wind: The wind speeds which are shown as variables in the diagrams in this

manual should be regarded as headwind or tailwind components of the

measured wind.

Demonstrated Crosswind Component:

The speed of the crosswind component at which adequate maneuverabil-

ity for take-off and landing has been demonstrated during type

certification.

MET: Weather, weather advice.

NAV: Navigation, route planning.

RoC: Rate of Climb.

General DA 42 AFM

Page 1 - 10 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

(d) Mass and balance

CG: Center of Gravity, also called 'center of mass'. Imaginary point in which

the airplane mass is assumed to be concentrated for mass and balance

calculations. Its distance from the Datum Plane is equal to the Center

of Gravity Moment Arm.

Center of Gravity Moment Arm:

The Moment Arm which is obtained if one divides the sum of the individual

moments of the airplane by its total mass.

Center of Gravity Limits:

The Center of Gravity range within which the airplane, at a given mass,

must be operated.

DP: Datum Plane; an imaginary vertical plane from which all horizontal

distances for center of gravity calculations are measured.

Empty Mass: The mass of the airplane including unusable fuel, all operating

consumables and the maximum quantity of oil.

Maximum Take-off Mass:

The maximum permissible mass for take-off.

Maximum Landing Mass:

The highest mass for landing conditions at the maximum descent velocity.

This velocity was used in the strength calculations to determine the

landing gear loads during a particularly hard landing.

Moment Arm: The horizontal distance from the Datum Plane to the Center of Gravity

of a component.

Moment: The mass of a component multiplied by its moment arm.

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 1 - 11

Usable Fuel: The quantity of fuel available for flight planning.

Unusable Fuel: The quantity of fuel remaining in the tank which cannot be used for flight.

Useful Load: The difference between take-off mass and empty mass.

(e) Engine

ECU: Engine Control Unit

FADEC: Full Authority Digital Engine Control

RPM: Revolutions per minute (rotational speed of the propeller)

Engine starting fuel temperature: Above this fuel temperature the engine may be

started.

Take-off fuel temperature: Above this fuel temperature take-off power setting

is permitted.

(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

XFR PUMP/DE-ICE Fuel Transfer Pump / De-Icing System

TAXI/MAP/ACL Taxi-, Map-, Anti Collision Light

FLOOD/OXY Flood Light / Oxygen System

PFD Primary Flight Display

ADC Air Data Computer

AHRS Attitude Heading Reference System

GEAR WRN/ELEV. LIMIT Landing Gear Annunciation / Variable Elevator Stop

GEAR Landing Gear Control

General DA 42 AFM

Page 1 - 12 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

RH MAIN BUS:

MFD Multi Function Display

AH Artificial Horizon

STALL WRN Stall Warning System

FLAP Flap System

LDG LT/START Landing Light / Start

INST LT/ NAV LT Instrument-, Navigation (Position) Light

AV/CDU/FAN Avionic-, CDU-Cooling Fans

AVIONIC BUS Avionic Bus

AV CONT./AP. WRN. Avionic Control / Autopilot Warning

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

DATA LINK Data Link System GDL 49

Wx 500 Stormscope

ADF Automatic Direction Finder

DME Distance Measuring Equipment

Wx RDR Weather Radar

LH ENG ECU BUS:

ECU BUS LH ECU Bus

ECU B LH ECU B

ECU A LH ECU A

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 1 - 13

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: Emergency Locator Transmitter

(h) Design Change Advisories

MÄM: Mandatory Design Change Advisory

OÄM: Optional Design Change Advisory

General DA 42 AFM

Page 1 - 14 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

(i) Miscellaneous

ACG: Austro Control GmbH (formerly BAZ, Federal Office of Civil Aviation)

ATC: Air Traffic Control

CFRP: Carbon Fiber Reinforced Plastic

EASA: European Aviation Safety Agency

EPU: External Power Unit

GIA: Garmin Integrated Avionics

GFRP: Glass Fiber Reinforced Plastic

JAR: Joint Aviation Requirements

JC/VP: Joint Certification/Validation Procedure

PCA: Primary Certification Authority

DA 42 AFM General

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1.6 UNITS OF MEASUREMENT

1.6.1 CONVERSION FACTORS

Dimension SI-Units US Units Conversion

Length [mm] millimeters

[m] meters

[km] kilometers

[in] inches

[ft] feet

[NM] nautical

miles

[mm] / 25.4 = [in]

[m] / 0.3048 = [ft]

[km] / 1.852 = [NM]

Volume [l] liters [US gal] US gallons

[qts] US quarts

[l] / 3.7854 = [US gal]

[l] / 0.9464 = [qts]

Speed [km/h] kilometers

per hour

[m/s] meters per

second

[kts] knots

[mph] miles per

hour

[fpm] feet per

minute

[km/h] / 1.852 = [kts]

[km/h] / 1.609 = [mph]

[m/s] x 196.85 = [fpm]

Speed of

rotation [RPM] revolutions per minute --

Mass [kg] kilograms [lb] pounds [kg] x 2.2046 = [lb]

Force,

weight [N] newtons [lbf] pounds

force [N] x 0.2248 = [lbf]

Pressure [hPa] hecto-

pascals

[mbar] millibars

[bar] bars

[inHg] inches of

mercury

[psi] pounds per

square inch

[hPa] = [mbar]

[hPa] / 33.86 = [inHg]

[bar] x 14.504 = [psi]

Tempera-

ture [°C] degrees

Celsius [°F] degrees

Fahrenheit [°C]x1.8 + 32 = [°F]

([°F] - 32)/1.8 = [°C]

General DA 42 AFM

Dimension SI-Units US Units Conversion

Page 1 - 16 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

Intensity of

electric

current

[A] ampères --

Electric

charge

(battery

capacity)

[Ah] ampère-hours

Electric

potential [V] volts --

Time [sec] seconds --

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 1 - 17

1.6.2 CONVERSION CHART LITERS / US GALLONS

Liters US Gallons US Gallons Liters

5 1.3 1 3.8

10 2.6 2 7.6

15 4.0 4 15.1

20 5.3 6 22.7

25 6.6 8 30.3

30 7.9 10 37.9

35 9.2 12 45.4

40 10.6 14 53.0

45 11.9 16 60.6

50 13.2 18 68.1

60 15.9 20 75.7

70 18.5 22 83.3

80 21.1 24 90.9

90 23.8 26 98.4

100 26.4 28 106.0

110 29.1 30 113.6

120 31.7 32 121.1

130 34.3 34 128.7

140 37.0 36 136.3

150 39.6 38 143.8

160 42.3 40 151.4

170 44.9 45 170.3

180 47.6 50 189.3

General DA 42 AFM

Page 1 - 18 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

1.7 THREE-VIEW DRAWING

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 1 - 19

1.8 G1000 AVIONICS SYSTEM

1. The G1000 Integrated Avionics System is a fully integrated flight, engine,

communication, navigation and surveillance instrumentation system. The system

consists of a Primary Flight Display (PFD), Multi-Function Display (MFD), audio panel,

Air Data Computer (ADC), Attitude and Heading Reference System (AHRS), engine

sensors and processing unit (GEA), and integrated avionics (GIA) containing VHF

communications, VHF navigation, and GPS (Global Positioning System).

2. The primary function of the PFD is to provide attitude, heading, air data, navigation,

and alerting information to the pilot. The PFD may also be used for flight planning.

The primary function of the MFD is to provide engine information, mapping, terrain

information, and for flight planning. The audio panel is used for selection of radios for

transmitting and listening, intercom functions, and marker beacon functions.

3. The primary function of the VHF Communication portion of the G1000 is to enable

external radio communication. The primary function of the VOR/ILS Receiver portion

of the equipment is to receive and demodulate VOR, Localizer, and Glide Slope signals.

The primary function of the GPS portion of the system is to acquire signals from the

GPS satellites, recover orbital data, make range and Doppler measurements, and

process this information in real-time to obtain the user's position, velocity, and time.

4. Provided a Garmin G1000 GPS receiver is receiving adequate usable signals, it has

been demonstrated capable of and has been shown to meet the accuracy specifications

for:

(a) VFR/IFR enroute, oceanic, terminal, and non-precision instrument approach (GPS,

Loran-C, VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV) operation within the

U.S. National Airspace System in accordance with AC 20-138A.

General DA 42 AFM

Page 1 - 20 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

(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.

accordance with AC 20-138A, EASA AMC 20-4, and FAA Order 8110.60 for oceanic

and remote airspace operations, provided it is receiving usable navigation

information from the GPS receiver.

Navigation is accomplished using the WGS-84 (NAD-83) coordinate reference datum.

GPS navigation data is based upon use of only the GPS operated by the United States

of America.

1.9 SOURCE DOCUMENTATION

This section lists documents, manuals and other literature that were used as sources for

the Airplane Flight Manual, and indicates the respective publisher. However, only the

information given in the Airplane Flight Manual is valid.

1.9.1 ENGINE

Address: Thielert Aircraft Engines GmbH

Platanenstrasse 14

D-09350 Lichtenstein

GERMANY

Phone: +49-37204-696-90

Fax: +49-37204-696-50

Website: www.thielert.com

Documents: TAE 125-01 Operation and Maintenance Manual

Doc. No.: OM-02-01, Version 2/7

DA 42 AFM General

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 1 - 21

1.9.2 PROPELLER

Address: mt-propeller

Airport Straubing Wallmühle

D-94348 Atting

GERMANY

Phone: +49-9429-9409-0

E-mail: sales@mt-propeller.com

Website: www.mt-propeller.de

Documents: E-124, Operation and Installation Manual

Hydraulically controlled variable pitch propeller

MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25

1.9.3 AVIONICS SYSTEM

Address: Garmin International, Inc.

1200 East 151st Street

Olathe, Kansas 66062

USA

Phone: +1-(913)-3978200

Fax: +1-(913)-3978282

Website: www.garmin.com

Documents: G1000 Cockpit Reference Guide

P/N 190-00406-00, Sept. 2004

General DA 42 AFM

Page 1 - 22 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

Intentionally left blank.

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 1

CHAPTER 2

OPERATING LIMITATIONS

Page

2.1 INTRODUCTION .......................................2-3

2.2 AIRSPEED ............................................2-4

2.3 AIRSPEED INDICATOR MARKINGS ........................2-5

2.4 POWER-PLANT LIMITATIONS ............................2-6

2.5 ENGINE INSTRUMENT MARKINGS ........................2-9

2.6 WARNING, CAUTION AND ADVISORY ALERTS .............2-10

2.6.1 WARNING, CAUTION AND ADVISORY

ALERTS ON THE G1000 ...........................2-10

2.6.2 OTHER WARNING ALERTS ........................2-13

2.7 MASS (WEIGHT) ......................................2-14

2.8 CENTER OF GRAVITY .................................2-15

2.9 APPROVED MANEUVERS ..............................2-16

2.10 MANEUVERING LOAD FACTORS ........................2-17

2.11 OPERATING ALTITUDE ................................2-18

2.12 FLIGHT CREW ........................................2-18

2.13 KINDS OF OPERATION.................................2-18

2.14 FUEL................................................2-21

2.15 LIMITATION PLACARDS ................................2-22

Operating Limitations DA 42 AFM

Page 2 - 2 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

2.16 OTHER LIMITATIONS ................................. 2-26

2.16.1 FUEL TEMPERATURE ........................... 2-26

2.16.2 BATTERY CHARGE ............................. 2-26

2.16.3 EMERGENCY SWITCH .......................... 2-27

2.16.4 DOOR LOCKING DEVICE ........................ 2-27

2.16.5 ELECTRONIC EQUIPMENT....................... 2-27

2.16.6 GARMIN G1000 AVIONICS SYSTEM ............... 2-28

2.16.7 SMOKING ..................................... 2-32

2.16.8 GROUND OPERATION .......................... 2-32

DA 42 AFM Operating Limitations

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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.

WARNING

Operation of the airplane outside of the approved operating

limitations is not permissible.

Operating Limitations DA 42 AFM

Page 2 - 4 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

2.2 AIRSPEED

Airspeed IAS Remarks

vAManeuvering

speed above 1542 kg

(3400 lb)

126 KIAS

Do not make full or abrupt

control surface movement

above this speed.

up to 1542 kg

(3400 lb)

120 KIAS

vFE Max. flaps

extended

speed

LDG 111 KIAS Do not exceed these

speeds with the given flap

setting.

APP 137 KIAS

vLO Max. landing

gear operating

speed

Extension vLOE

194 KIAS Do not operate the landing

gear above this speed.

Retraction vLOR

156 KIAS

vLE Max. landing gear extended

speed 194 KIAS Do not exceed this speed

with the landing gear

extended.

vMCA Minimum control speed airborne 68 KIAS With one engine

inoperative, keep airspeed

above this limit.

vNO Max. structural cruising speed 155 KIAS Do not exceed this speed

except in smooth air, and

then only with caution.

vNE Never exceed speed in smooth

air 194 KIAS Do not exceed this speed

in any operation.

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 5

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”.

Blue radial 82 KIAS Best rate of climb speed, single engine.

Red radial 68 KIAS Minimum control speed, single engine.

Red radial 194 KIAS Maximum speed for all operations - vNE.

Operating Limitations DA 42 AFM

Page 2 - 6 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

2.4 POWER-PLANT LIMITATIONS

a) Number of engines : 2

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)

Maximum : 2300 RPM

Maximum overspeed : 2500 RPM (max. 20 sec.)

e) Engine power

Max. take-off power : 99 kW (135 DIN-hp) at 2300 RPM (100 % load)

Max. continuous power : 99 kW (135 DIN-hp) at 2300 RPM (100 % load)

f) Fuel temperature

Minimum : -30 °C

Maximum : 75 °C

g) Oil pressure (indicated values are corrected for pressure altitude)

Minimum : 1.0 bar

Maximum : 6.5 bar

h) Oil quantity (per engine)

Minimum : 4.5 liters (appr. 4.8 US qts)

Maximum : 6.0 liters (appr. 6.3 US qts)

Maximum oil consumption : 0.1 liters/hr (appr. 0.1 US qts/hr)

i) Oil temperature

Minimum : -32 °C

Maximum : 140 °C

j) Gearbox temperature

Maximum : 120 °C

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 2 - 7

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

p) Propeller diameter : 187 cm (6 ft 2 in)

q) Prop. pitch angle (@ 0.75 R) : 12° ±0.2° (low pitch)

15° ±1° (start lock position)

81° ±1° (feathered position)

r) Approved fuel grades : see Section 2.14 - FUEL

s) Oil specification : SHELL HELIX ULTRA 5W30 synthetic API SL/CF

SHELL HELIX ULTRA 5W40 synthetic API SL/CF

AERO SHELL OIL Diesel 10W-40

t) Gearbox oil (propeller gearbox) : SHELL EP 75W90 API GL-4

u) Coolant : Water / Cooler protection (BASF Glysantin Protect

Plus/G48) 1/1. The freezing point of the coolant

is -36 °C (-32.8 °F).

Operating Limitations DA 42 AFM

Page 2 - 8 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 9

2.5 ENGINE INSTRUMENT MARKINGS

Engine instrument markings and their color code significance are shown in the table below:

Indi-

cation Red

arc/bar

lower

prohibited

range

Yellow

arc/bar

caution

range

Green

arc/bar

normal

operating

range

Yellow

arc/bar

caution

range

Red

arc/bar

upper

prohibited

range

RPM -- -- up to

2300 RPM above

2300 RPM

Oil

pressure below

1.0 bar 1.0 to 2.3 bar 2.3 to 5.2 bar 5.2 to 6.5 bar above

6.5 bar

Oil

temp. below

-32 °C -32 to 50 °C 50 to 125 °C 1

50 to 130 °C 2

125 to 140 °C 1

131 to 140 °C 2

above

140 °C

Coolant

temp. below

-32 °C -32 to 60 °C 60 to 96 °C 1

60 to 101 °C 2

96 to 105 °C 1

102 to 105 °C 2

above

105 °C

Gearbox

temp. -- -- up to 115 °C 115 to 120 °C above

120 °C

Load -- -- 0 to 100 % -- --

Fuel

temp. below

-30 °C -30 to -22 °C 1

-30 to +4 °C 2

-22 to 70 °C 1

+5 to 69 °C 2

70 to 75 °C above

75 °C

Ammeter -- -- up to 60 A -- above

60 A

Volt-

meter below

24.1 V 24.1 to 25 V 25 to 30 V 30 to 32 V above

32 V

Fuel qty. 0 US gal -- 0 to 25

US gal -- --

1) MÄM 42-101 not implemented

2) MÄM 42-101 implemented (refer to Section 1.1)

Operating Limitations DA 42 AFM

Page 2 - 10 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

2.6 WARNING, CAUTION AND ADVISORY ALERTS

2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000

NOTE

The alerts described in the following are displayed on the

Garmin G1000. Section 7.10 includes a detailed description

of the alerts.

The following tables show the color and significance of the warning, caution and advisory

alerts lights on the G1000.

Color and significance of the warning alerts on the G1000

Warning alerts

(red) Meaning / Cause

WARNING One of the Warnings listed below is being indicated.

L/R ENG TEMP Left / Right engine coolant temperature is in the upper red

range (too high / > 105 °C).

L/R OIL TEMP Left / Right engine oil temperature is in the upper red range

(too high / >140 °C).

L/R OIL PRES Left / Right engine oil pressure is in the lower red range

(too low / < 1.0 bar).

FUEL TEMP Left / Right fuel temperature is in the upper red range (too

high / > 75 °C)

L/R GBOX TEMP Left / Right engine gearbox temperature is in the upper red

range (too high / > 120 °C).

L/R ALTN AMPS Left / Right engine alternator output is in the upper red range

(too high / > 60 amps).

DA 42 AFM Operating Limitations

Warning alerts

(red) Meaning / Cause

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 11

L/R ENG FIRE Left / Right engine fire detected.

L/R STARTER Left / Right engine starter is engaged.

DOOR OPEN Front and/or rear canopy and/or baggage door are/is not

closed and locked.

POSN ERROR G1000 will no longer provide GPS based navigational

guidance.

ATTITUDE FAIL The display system is not receiving attitude reference

information from the AHRS.

AIRSPEED FAIL The display system is not receiving airspeed input from the

air data computer.

ALTITUDE FAIL The display system is not receiving altitude input from the air

data computer.

VERT SPEED

FAIL The display system is not receiving vertical speed input from

the air data computer.

HDG The display system is not receiving valid heading input from

the AHRS.

WARN RAIM position warning. The nav deviation bar is removed.

Operating Limitations DA 42 AFM

Page 2 - 12 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

Color and significance of the caution alerts on the G1000

Caution-alerts

(amber) Meaning / Cause

L/R ECU A FAIL

* A fault has occurred in the left / right engine ECU A (one

reset of minor faults is possible)

* ECU A is being tested during FADEC-test procedure

during the 'before take- off check.'

L/R ECU B FAIL

* A fault has occurred in the left / right engine ECU B (one

reset of minor faults is possible)

* ECU B is being tested during FADEC-test procedure

during the 'before take- off check.'

L/R FUEL LOW Left / Right engine main tank fuel quantity is low.

L/R ALTN FAIL Left / Right engine alternator has failed.

L/R VOLTS LOW Left / Right engine bus voltage is too low (< 25 volts).

L/R COOL LVL Left / Right engine coolant level is low.

PITOT FAIL Pitot heat has failed.

PITOT HT OFF Pitot heat is OFF.

STALL HT FAIL Stall warning heat has failed.

STALL HT OFF Stall warning heat is OFF.

STICK LIMIT Control stick limiting system (variable elevator stop) has

failed.

INTEG RAIM not

available RAIM (Receiver Autonomous Integrity Monitor) is not

available.

AHRS ALIGN:

Keep Wings

Level

The AHRS (Attitude and Heading Reference System) is

aligning.

L/R AUX FUEL E

Left / Right auxiliary fuel tank empty (if installed).

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 13

Color and significance of the advisory alerts on the G1000

advisory alerts

(white) Meaning / Cause

L/R GLOW ON Left / Right engine glow plug active.

L/R FUEL XFER Fuel transfer from auxiliary to main tank is in progress.

PFD FAN FAIL Cooling fan for the PFD is inoperative.

MFD FAN FAIL Cooling fan for the MFD is inoperative.

GIA FAN FAIL Cooling fan for the GIAs is inoperative.

2.6.2 OTHER WARNING ALERTS

Warning alerts on the instrument panel

GEAR UNSAFE

WARNING LIGHT

(red)

Illuminates if the landing gear is neither in the final up or

down & locked position.

Audible warning alerts

GEAR

RETRACTED

CHIME TONE

(repeating)

Resounds if the landing gear is retracted while the flaps

move into position LDG or when the throttle is placed in a

position below 25%.

Operating Limitations DA 42 AFM

Page 2 - 14 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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 1650 kg 3638 lb

Maximum landing mass (see NOTE below)

1700 kg 3748 lb

Max. load in nose baggage compartment

(in fuselage nose) 30 kg 66 lb

Max. load in cockpit baggage compartment

(behind rear seats) 45 kg 100 lb

Max. load in baggage extension

(behind cockpit baggage compartment) 18 kg 40 lb

Max. load, cockpit baggage compartment and baggage

extension together 45 kg 100 lb

WARNING

Exceeding the mass limits will lead to overstressing of the

airplane as well as to degradation of flight characteristics and

flight performance.

NOTE

In some countries the beginning of a flight is defined by

starting the powerplant. In those countries a ramp mass of

maximal MTOM + 8 kg (MTOM + 18 lb) is approved. At the

time of lift-off the maximum permitted take-off mass must not

be exceeded.

NOTE

If MÄM 42-088 is carried out, a landing with a mass between

1700 kg (3748 lb) and 1785 kg (3935 lb) is admissible. It

constitutes an abnormal operating procedure. A "Hard

Landing Check" is only required after a hard landing,

regardless of the actual landing mass.

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 2 - 15

2.8 CENTER OF GRAVITY

Datum Plane

The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and

in front of the airplane as seen from the direction of flight. The airplane’s longitudinal axis

is parallel with the floor of the nose baggage compartment. When the floor of the nose

baggage compartment is aligned horizontally, the Datum Plane is vertical. The Datum

Plane is located 2.196 meters (86.46 in) forward of the most forward point of the root rib

on the stub wing (refer to figure in Section 6.2).

Center of gravity limitations

The center of gravity (CG position) for flight conditions must be between the following

limits:

Most forward flight CG:

2.35 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. take-off mass (see Section 2.7)

linear variation in between

Most rearward flight CG:

2.42 m (95.28 in) aft of Datum Plane at 1250 kg (2756 lb)

2.49 m (98.03 in) aft of Datum Plane at 1600 kg (3527 lb)

2.49 m (98.03 in) aft of Datum Plane at max. take-off mass (see Section 2.7)

linear variation in between

Refer to Section 6.4.4 for a graphical illustration of the CG limitations.

WARNING

Exceeding the center of gravity limitations reduces the

controllability and stability of the airplane.

Operating Limitations DA 42 AFM

Page 2 - 16 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

2.9 APPROVED MANEUVERS

The airplane is certified in the Normal Category in accordance with JAR-23.

Approved maneuvers

1) all normal flight maneuvers;

2) stalling (with the exception of dynamic stalling); and

3) Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which

an angle of bank of not more than 60° is attained.

CAUTION

Aerobatics, spinning and flight maneuvers with more than 60°

of bank are not permitted in the Normal Category. Stalling

with asymmetric power or one engine inoperative is not

permitted.

DA 42 AFM Operating Limitations

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2.10 MANEUVERING LOAD FACTORS

at vAat vNE with flaps in APP

or LDG position

Positive 3.8 3.8 2.0

Negative -1.52 0

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.

load factor time limit

-0.2 5 seconds

-0.3 4 seconds

-0.4 3 seconds

-0.5 2 seconds

Operating Limitations DA 42 AFM

Page 2 - 18 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

2.11 OPERATING ALTITUDE

The maximum operating altitude is 18,000 ft (5,486 m) pressure altitude.

2.12 FLIGHT CREW

Minimum crew : 1 (one person)

Maximum number of occupants : 4 (four persons)

2.13 KINDS OF OPERATION

Provided that national operational requirements are met, the following kinds of operation

are approved:

• daytime flights according to Visual Flight Rules (VFR)

• with the appropriate equipment: night flights according to Visual Flight Rules (VFR)

• with the appropriate equipment: flights according to Instrument Flight Rules (IFR)

• take-off and landing on paved surfaces

• take-off and landing on grass surfaces

• If OÄM 42-054 is carried out: flight into known or forecast icing conditions. Refer

to Supplement S03, latest revision.

Flights into known thunderstorms are prohibited.

Minimum operational equipment (serviceable)

The following table lists the minimum serviceable equipment required by JAR-23. Additional

minimum equipment for the intended operation may be required by national operating

rules and also depends on the route to be flown.

NOTE

Many of the items of minimum equipment listed in the

following table are integrated in the G1000.

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 19

for daytime VFR

flights in addition

for night VFR flights in addition

for IFR flights

Flight &

naviga-

tion

instru-

ments

airspeed indicator

(on G1000 PFD or

backup)

altimeter (on G1000

PFD or backup)

magnetic compass

1 headset, used by

pilot in command

vertical speed

indicator (VSI)

attitude gyro

(artificial horizon; on

G1000 PFD or

backup)

turn & bank indicator

directional gyro

VHF radio (COM)

with speaker and

microphone

VOR receiver

transponder

(XPDR), mode A

and mode C

GPS receiver (part

of G1000)

second airspeed

indicator (both, on

G1000 PFD and

backup)

second altimeter

(both, on G1000

PFD and backup)

second attitude gyro

(both, on G1000

PFD and backup)

second VHF radio

(COM)

VOR-LOC-GP

receiver

second GPS

receiver (part of

G1000)

engine

instru-

ments

fuel qty. (2x)

oil press. (2x)

oil temp. (2x)

coolant temp. (2x)

coolant level

indicator (2x)

gearbox temp. (2x)

load (2x)

prop. RPM (2x)

fuel temp. left & right

tank

ammeter

voltmeter

Operating Limitations DA 42 AFM

for daytime VFR

flights in addition

for night VFR flights in addition

for IFR flights

Page 2 - 20 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

lighting *

position lights

strobe lights (anti

collision lights)

landing light

instrument lighting

flood light

flashlight

other

opera-

tional

mini-

mum

equip-

ment

stall warning system

variable elevator

stop

alternate means for

fuel quantity

indication (see

Section 7.9)

safety belts for each

occupied seat

Airplane Flight

Manual

Pitot heating system

alternate static valve

* emergency battery

(for backup attitude

gyro and flood light)

NOTE

A list of approved equipment can be found in Chapter 6.

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 2 - 21

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.

CAUTION

If the airplane is operated with Diesel fuel or a blend of Diesel

fuel with JET A-1, the use of the auxiliary tanks, if installed

(OÄM 42-056), is not permitted.

CAUTION

Additional temperature limitations must be observed if the

airplane is operated with Diesel fuel or blends of Diesel fuel

with Jet A-1. Refer to Section 2.16.1.

NOTE

Use only uncontaminated fuel from reliable sources.

Main Tanks Auxiliary Tanks

(if installed) Total

US gal liters US gal liters US gal liters

Total fuel quantity 2 x 26.0 2 x 98.4 2 x 13.7 2 x 52.0 2 x 39.7 2 x 150.4

Usable fuel 2 x 25.0 2 x 94.6 2 x 13.2 2 x 50.0 2 x 38.2 2 x 144.6

Max. permissible

difference LH/RH 5.0 18.9

Operating Limitations DA 42 AFM

Page 2 - 22 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

LANDING GEAR

vLE / vLOE = 194 KIAS

vLOR = 156 KIAS

EMERGENCY

Gear Extension

Max. 156 KIAS

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:

MÄM 42-088 or

OÄM 42-054 or

both

incorporated:

THIS AIRPLANE MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANE'FLIGHT MANUAL IN THE “NORMAL” CATEGORY. PROVIDED THAT NATIONAL'OPERATIONAL REQUIREMENTS ARE MET AND THE APPROPRIATE EQUIPMENT'IS INSTALLED AND OPERATIONAL, THIS AIRPLANE IS APPROVED FOR THE'FOLLOWING KINDS OF OPERATION: DAY VFR, NIGHT VFR AND IFR, AND FLIGHT'INTO KNOWN OR FORECAST ICING CONDITIONS. ALL AEROBATIC MANEUVERS'INCLUDING SPINNING ARE PROHIBITED. FOR FURTHER OPERATIONAL LIMITATIONS'REFER TO THE AIRPLANE FLIGHT MANUAL.'

MANEUVERING SPEED:'

VA = 126 KIAS (ABOVE 1542 KG / 3400 LB)'VA = 120 KIAS (UP TO 1542 KG / 3400 LB)'

neither

MÄM 42-088 nor

OÄM 42-054

incorporated:

THIS AIRPLANE MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANE

FLIGHT MANUAL. IT CAN BE OPERATED IN THE “NORMAL” CATEGORY IN NON-ICING

CONDITIONS. PROVIDED THAT NATIONAL OPERATIONAL REQUIREMENTS ARE MET

AND THE APPROPRIATE EQUIPMENT IS INSTALLED, THIS AIRPLANE IS APPROVED

FOR THE FOLLOWING KIND OF OPERATION: DAY VFR, NIGHT VFR AND IFR. ALL

AEROBATIC MANEUVERS INCLUDING SPINNING ARE PROHIBITED. FOR FURTHER

OPERATIONAL LIMITATIONS REFER TO THE AIRPLANE FLIGHT MANUAL.

MANEUVERING SPEED:

VA = 124 KIAS (ABOVE 1468 UP TO 1700 KG / ABOVE 3236 UP TO 3748 LB)

VA = 121 KIAS (1250 TO 1468 KG / 2756 TO 3236 LB)

On the Emergency Landing Gear Extension Lever:

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 2 - 23

Diesel Fuel or

Unknown Fuel Blend:

Below -5 /C:

No engine start permitted.

Below +5 /C:

No take-off permitted.

max. usable

fuel: 2 x 25 US gal

max. difference LH/RH

tank: 5 US gal

max. usable fuel

main tank:

2 x 25 US gal

auxiliary tank:

2 x 13 US gal

max. difference LH/RH

main tank: 5 US gal

WARNING

APPROVED FUEL

JET-A1

or see Airplane Flight Manual

On the instrument panel, next to the fuel quantity indication:

(a) Standard Tank: (b) Auxiliary Tank (if installed):

if MÄM 42-037 is carried out, on the Garmin G1000 MFD next to the fuel temperature

indication:'

(a) Next to each of the two fuel filler necks;

(b) in addition next to each of the two auxiliary fuel filler necks (if installed):

Operating Limitations DA 42 AFM

Page 2 - 24 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

OIL

Shell Helix Ultra

5W30 synth.

API SL/CF

or see AFM

Flaps

APP

137 KIAS

LDG

111 KIAS

In each cowling, on the door for the oil filler neck:

Next to the flap selector switch:

In the cockpit, on the left fuselage sidewall:

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 25

Next to the cockpit baggage compartment:

In the nose baggage compartment:

Beside the door locking device installed in the passengers' door:

On the right hand side of the instrument panel above the circuit breakers:

Max. Baggage:

30 kg [66 lb]

EMERGENCY EXIT:

The keylock must be

unlocked during flight

______ NO SMOKING ______

Operating Limitations DA 42 AFM

Page 2 - 26 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

Diesel fuel: engine starting fuel temperature ........... min. -5 °C (+23 °F)

take-off fuel temperature ................min. +5 °C (+41 °F)

maximum fuel temperature................ +75 °C (+167 °F)

Fuel blends or unknown fuel grade:

engine starting fuel temperature ........... min. -5 °C (+23 °F)

take-off fuel temperature ................min. +5 °C (+41 °F)

maximum fuel temperature................ +75 °C (+167 °F)

2.16.2 BATTERY CHARGE

Taking off for a Night VFR or IFR flight with an empty battery is not permitted.

The use of an external power supply for engine starting with an empty airplane battery

is also not permitted if the subsequent flight is intended to be a Night VFR or IFR flight.

In this case the airplane battery must first be charged.

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 2 - 27

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.

2.16.5 ELECTRONIC EQUIPMENT

The use and switching on of electronic equipment other than that which is part of the

equipment of the airplane is not permitted, as it could lead to interference with the

airplane’s avionics.

Examples of undesirable items of equipment are:

- Mobile phones

- Remote radio controls

- Video screens employing CRT's

- Minidisc recorders in record mode

This list is not exhaustive.

The use of laptop computers, including those with CD-ROM drives, CD and minidisc players

in the replay mode, cassette players and video cameras is permitted. All this equipment

however should be switched off for take-off and landing.

Operating Limitations DA 42 AFM

Page 2 - 28 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

Software Part Number Approved

Version Function

System

for approved version see DAI MSB 42-008, latest version

010-00370-( )

Manifest

006-B0093-( )

GPS1, GPS2

006-B0172-( )

GTX1-GIA1, GTX1-GIA2

006-B0190-( )

GIA1, GIA2

006-B0193-( )

GEA1-GIA1; GEA1-GIA2

006-B0203-( )

GMA1-GIA1, GMA1-GAI2

006-B0223-( )

GRS1-GIA1, GRS1-GIA2

006-B0224-( )

GMU1

006-B0319-( )

PFD1, MFD1

006-B0328-( )

006-B0329-( )

006-C0048-( )

GMU1 FPGA

006-C0049-( )

GRS1 FPGA

006-C0055-( )

GDC1 FPGA

006-D0159-( )

GRS1 MV DB

006-D0202-( )

006-B0261-( )

GDC1-GIA1

006-B0081-( )

COM1, COM2

006-B0083-( )

GS1, GS2

006-B0082-( )

NAV1, NAV2

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 29

NOTE

The database version is displayed on the MFD power-up page

immediately after system power-up and must be

acknowledged. The remaining system software versions can

be verified on the AUX group sub-page 5, "AUX - SYSTEM

STATUS".

3. IFR enroute, oceanic and terminal navigation predicated upon the G1000 GPS Receiver

is prohibited unless the pilot verifies the currency of the database or verifies each

selected waypoint for accuracy by reference to current approved data.

4. Instrument approach navigation predicated upon the G1000 GPS Receiver must be

accomplished in accordance with approved instrument approach procedures that are

retrieved from the GPS equipment database. The GPS equipment database must

incorporate the current update cycle.

NOTE

Not all published approaches are in the FMS database. The

pilot must ensure that the planned approach is in the

database.

(a) Instrument approaches utilizing the GPS receiver must be conducted in the

approach mode and Receiver Autonomous Integrity Monitoring (RAIM) must

be available at the Final Approach Fix.

Operating Limitations DA 42 AFM

Page 2 - 30 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

(b) Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of

approach not approved for GPS overlay with the G1000 GPS receiver is not

authorized.

require VOR/ILS navigation data to be present on the display.

(d) When an alternate airport is required by the applicable operating rules, it must

be served by an approach based on other than GPS or Loran-C navigation, the

airplane must have the operational equipment capable of using that navigation

aid, and the required navigation aid must be operational.

(e) VNAV information may be utilized for advisory information only. Use of VNAV

information for Instrument Approach Procedures does not guarantee step-down

fix altitude protection, or arrival at approach minimums in normal position to land.

(f) RNAV (GPS) approaches must be conducted utilizing the GPS sensor.

(g) RNP RNAV operations are not authorized, except as noted in Chapter 1 of this

AFM.

5. If not previously defined, the following default settings must be made in the "SYSTEM

SETUP" menu of the G1000 prior to operation (refer to Pilot's Guide for procedure if

necessary):

(a) DIS, SPD : nm, kt (sets navigation units to "nautical miles" and "knots")

(b) ALT, VS : ft, fpm (sets altitude units to "feet" and "feet per minute")

(d) POSITION : deg-min (sets navigation grid units to decimal minutes)

DA 42 AFM Operating Limitations

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 2 - 31

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.

6. Operation is prohibited north of 70° N and south of 70° S latitudes. In addition, operation

is prohibited in the following two regions:

(a) north of 65° N between 75° W and 120° W longitude, and

(b) south of 55° S between 120° E and 165° E longitude.

7. CDI sequencing of the ILS must be set to MANUAL for instrument approaches

conducted with the autopilot coupled. If the CDI source is changed when the autopilot

is engaged in NAV mode, the autopilot lateral mode will revert to ROLL ATTITUDE

mode and NAV mode must be manually reselected by the pilot.

8. The fuel quantity, fuel required, and fuel remaining functions on the Fuel Page

(displayed when pushing the FUEL button as shown in Section 7.13) of the FMS are

supplemental information only and must be verified by the flight crew.

9. The pilot's altimeter is the primary altitude reference during all operations using advisory

vertical navigation (VNAV) information.

Operating Limitations DA 42 AFM

Page 2 - 32 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 1

CHAPTER 3

EMERGENCY PROCEDURES

Page

3.1 INTRODUCTION .......................................3-4

3.1.1 GENERAL........................................3-4

3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES ..............3-5

3.1.3 SELECTING EMERGENCY FREQUENCY ..............3-5

3.2 AIRPLANE-RELATED G1000 WARNINGS ...................3-6

3.2.1 WARNINGS / GENERAL ............................3-6

3.2.2 L/R ENG TEMP....................................3-6

3.2.3 L/R OIL TEMP ....................................3-7

3.2.4 L/R OIL PRES.....................................3-7

3.2.5 L/R GBOX TEMP ..................................3-8

3.2.6 L/R FUEL TEMP ...................................3-8

3.2.7 L/R ALTN AMPS...................................3-9

3.2.8 L/R ENG FIRE ....................................3-9

3.2.9 L/R STARTER....................................3-10

3.2.10 DOOR OPEN....................................3-10

3.3 G1000 SYSTEM WARNINGS .............................3-11

3.3.1 RED X..........................................3-11

3.3.2 POSN ERROR ...................................3-11

3.3.3 ATTITUDE FAIL ..................................3-11

3.3.4 AIRSPEED FAIL ..................................3-11

3.3.5 ALTITUDE FAIL ..................................3-12

3.3.6 VERT SPEED FAIL ................................3-12

3.3.7 HDG ...........................................3-12

3.3.8 WARN..........................................3-12

Emergency

Procedures DA 42 AFM

Page 3 - 2 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

3.4 G1000 FAILURES ..................................... 3-13

3.4.1 NAVIGATION INFORMATION FAILURE .............. 3-13

3.4.2 PFD OR MFD DISPLAY FAILURE ................... 3-13

3.4.3 AHRS FAILURE ................................. 3-13

3.4.4 AIR DATA COMPUTER (ADC) FAILURE .............. 3-14

3.4.5 ERRONEOUS OR LOSS OF ENGINE

AND FUEL DISPLAYS ............................ 3-14

3.4.6 ERRONEOUS OR LOSS OF

WARNING/CAUTION ANNUNCIATORS .............. 3-15

3.5 ONE ENGINE INOPERATIVE PROCEDURES ............... 3-16

3.5.1 DETECTING THE INOPERATIVE ENGINE ............ 3-16

3.5.2 ENGINE TROUBLESHOOTING ..................... 3-17

3.5.3 ENGINE SECURING (FEATHERING) PROCEDURE .... 3-20

3.5.4 UNFEATHERING & RESTARTING

THE ENGINE IN FLIGHT .......................... 3-21

3.5.5 ENGINE FAILURE DURING TAKEOFF ............... 3-23

3.5.6 ENGINE FAILURES IN FLIGHT ..................... 3-26

3.5.7 LANDING WITH ONE ENGINE INOPERATIVE ......... 3-30

3.5.8 GO-AROUND / BALKED LANDING

WITH ONE ENGINE INOPERATIVE ................. 3-32

3.5.9 FLIGHT WITH ONE ENGINE INOPERATIVE........... 3-34

3.6 LANDING GEAR SYSTEM FAILURES ..................... 3-35

3.6.1 LANDING GEAR UNSAFE WARNING ................ 3-35

3.6.2 MANUAL EXTENSION OF THE LANDING GEAR ....... 3-37

3.6.3 LANDING WITH GEAR UP ......................... 3-39

3.6.4 LANDING WITH A DEFECTIVE TIRE

ON THE MAIN LANDING GEAR .................... 3-40

3.6.5 LANDING WITH DEFECTIVE BRAKES ............... 3-41

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 3

3.7 FAILURES IN THE ELECTRICAL SYSTEM ..................3-42

3.7.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . . 3-42

3.7.2 HIGH CURRENT .................................3-43

3.7.3 STARTER MALFUNCTION .........................3-43

3.8 SMOKE AND FIRE .....................................3-44

3.8.1 ENGINE FIRE ON GROUND ........................3-44

3.8.2 ENGINE FIRE DURING TAKE-OFF ...................3-44

3.8.3 ENGINE FIRE IN FLIGHT...........................3-45

3.8.4 ELECTRICAL FIRE ON GROUND ....................3-46

3.8.5 ELECTRICAL FIRE IN FLIGHT ......................3-47

3.9 OTHER EMERGENCIES ................................3-48

3.9.1 SUSPICION OF CARBON MONOXIDE

CONTAMINATION IN THE CABIN ...................3-48

3.9.2 UNLOCKED DOORS ..............................3-49

3.9.3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM . . 3-50

3.9.4 UNINTENTIONAL FLIGHT INTO ICING................3-52

3.9.5 FUEL SUPPLY FAILURE ...........................3-53

3.9.6 RECOVERY FROM AN UNINTENTIONAL SPIN .........3-54

3.9.7 EMERGENCY DESCENT...........................3-56

3.9.8 EMERGENCY EXIT ...............................3-56

NOTE

Procedures for uncritical system faults are given in Chapter

4B - ABNORMAL OPERATING PROCEDURES.

Emergency

Procedures DA 42 AFM

Page 3 - 4 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

3.1 INTRODUCTION

3.1.1 GENERAL

This chapter contains checklists as well as the description of recommended procedures

to be followed in the event of an emergency. Engine failure or other airplane-related

emergencies are most unlikely to occur if the prescribed procedures for pre-flight checks

and airplane maintenance are followed.

If, nonetheless, an emergency does arise, the guidelines given in this chapter should be

followed and applied in order to clear the problem.

As it is impossible to foresee all kinds of emergencies and cover them in this Airplane

Flight Manual, a thorough understanding of the airplane by the pilot is, in addition to his

knowledge and experience, an essential factor in the solution of any problems which may

arise.

WARNING

In each emergency, control over the flight attitude and the

preparation of a possible emergency landing have priority

over attempts to solve the current problem ("first fly the

aircraft"). Prior to the flight the pilot must consider the

suitability of the terrain for an emergency landing for each

phase of the flight. For a safe flight the pilot must constantly

keep a safe minimum flight altitude. Solutions for various

adverse scenarios should be thought over in advance. This

should prevent a situation where the pilot is faced with an

emergency he cannot handle calmly and with determination.

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 5

3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES

Event

One engine inoperative minimum

control speed (Air) vmCA 68 KIAS

One engine inoperative speed for

best rate of climb vYSE 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. If the display

is available, it will also show it in the "Active" frequency window.

Emergency

Procedures DA 42 AFM

Page 3 - 6 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

3.2 AIRPLANE-RELATED G1000 WARNINGS

3.2.1 WARNINGS / GENERAL

"Warning" means that the non-observation of the corresponding procedure leads to an

immediate or important degradation in flight safety. The warning text is displayed in red

color. A warning chime tone of 1.5 seconds duration will sound and repeat without delay

until the alarm is acknowledged by the crew.

3.2.2 L/R ENG TEMP

L/R ENG TEMP Left / Right engine coolant temperature is in the upper

red range (too high / above 105 °C)

Coolant temperatures above the limit value of 105 °C can lead to a total loss of power

due to engine failure.

Proceed according to:

4B.3.2 COOLANT TEMPERATURE

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 7

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.

Proceed according to:

4B.3.3 OIL TEMPERATURE

3.2.4 L/R OIL PRES

L/R OIL PRES Left / Right engine oil pressure is in the lower red

range (too low / below 1 bar).

Oil pressures below the limit value of 1 bar can lead to a total loss of power due to engine

failure.

Proceed according to:

4B.3.4 OIL PRESSURE

Emergency

Procedures DA 42 AFM

Page 3 - 8 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

3.2.5 L/R GBOX TEMP

L/R GBOX TEMP Left / Right engine gearbox temperature is in the

upper red range (too high / above 120 °C).

Gearbox temperatures above the limit value of 120 °C can lead to a total loss of power

due to engine failure.

Proceed according to:

4B.3.5 GEARBOX TEMPERATURE

3.2.6 L/R FUEL TEMP

L/R FUEL TEMP Left / Right fuel temperature is in the upper red range

(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.

Proceed according to:

4B.3.6 FUEL TEMPERATURE

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 9

3.2.7 L/R ALTN AMPS

L/R ALTN AMPS Left / Right engine alternator output is in the upper red

range (too high / above 60 amps).

Proceed according to:

3.7.2 HIGH CURRENT

3.2.8 L/R ENG FIRE

L/R ENG FIRE Left / Right engine fire detected

Engine fire can lead to a total loss of power due to engine failure as well as severe

structural damage:

Proceed according to the following procedures as applicable:

3.8.1 ENGINE FIRE ON GROUND

3.8.2 ENGINE FIRE DURING TAKE-OFF

3.8.3 ENGINE FIRE IN FLIGHT

Emergency

Procedures DA 42 AFM

Page 3 - 10 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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

DOOR OPEN Front and/or rear canopy and/or baggage door are/is

not closed and locked.

Proceed according to:

3.9.2 UNLOCKED DOORS

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 11

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

POSN ERROR The system will flag and no longer provide GPS based

navigational guidance.

Revert to the G1000 VOR/ILS receivers or an alternate means of navigation other than

the G1000 GPS receivers.

3.3.3 ATTITUDE FAIL

ATTITUDE FAIL The display system is not receiving attitude reference

information from the AHRS; accompanied by the

removal of sky/ground presentation and a red X over

the attitude area.

Revert to the standby attitude indicator.

3.3.4 AIRSPEED FAIL

AIRSPEED FAIL The display system is not receiving airspeed input

from the air data computer; accompanied by a red X

through the airspeed display.

Revert to the standby airspeed indicator.

Emergency

Procedures DA 42 AFM

Page 3 - 12 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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

VERT SPEED FAIL The display system is not receiving vertical speed

input from the air data computer; accompanied by a

red X through the vertical speed display.

Determine vertical speed based on the change of altitude information.

3.3.7 HDG

HDG The display system is not receiving valid heading input

from the AHRS; accompanied by a red X through the

digital heading display.

Revert to the emergency compass.

3.3.8 WARN

WARN RAIM position warning - nav deviation bar removed.

1. CDI softkey .......................... switch to VOR/LOC

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 13

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

NOTE

A failure of the Attitude and Heading Reference System

(AHRS) is indicated by a removal of the sky/ground

presentation and a red X and a yellow "AHRS FAILURE"

shown on the PFD. The digital heading presentation will be

replaced with a yellow "HDG" and the compass rose digits will

be removed. The course pointer will indicate straight up and

course may be set using the digital window.

1. Use standby attitude indicator, emergency compass and Navigation Map

2. Course ............................. set using digital window

Emergency

Procedures DA 42 AFM

Page 3 - 14 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

1. Use standby airspeed indicator and altimeter.

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.

Erroneous indications may be determined by comparing a

display with other displays and other system information.

1. Set power based on throttle lever position, engine noise and speed.

2. Monitor other indications to determine the health of the engine.

3. Use known power settings and Section 5.3.2 of AFM for approximate fuel flow

values.

4. Use other system information, such as annunciator messages, GPS fuel quantity

and flow, to safely complete the flight.

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 15

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.

1. If an annunciator appears, treat it as if the condition exists. Refer to Chapter 3 -

EMERGENCY PROCEDURES or Chapter 4B - ABNORMAL OPERATING PRO-

CEDURES.

2. If a display indicates an abnormal condition but no annunciator is present, use

other system information, such as engine displays, GPS fuel quantity and flow, to

determine if the condition exists. If it cannot be determined that the condition

does not exist, treat the situation as if the condition exists. Refer to Chapter 3 -

EMERGENCY PROCEDURES or Chapter 4B - ABNORMAL OPERATING PRO-

CEDURES.

Emergency

Procedures DA 42 AFM

Page 3 - 16 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

In any event the sudden application of power during one-

engine inoperative operation makes the control of the airplane

more difficult.

3.5.1 DETECTING THE INOPERATIVE ENGINE

NOTE

One engine inoperative means an asymmetric loss of thrust,

resulting in uncommanded yaw and roll in direction of the so-

called "dead" engine (with coordinated controls). To handle

this situation it is vital to maintain directional control by mainly

rudder and additional aileron input. The following mnemonic

can help to identify the failed engine:

"Dead foot - dead engine"

This means that, once directional control is re-established,

the pilot can feel the control force on the foot pushing the

rudder-pedal on the side of the operative engine, while the

foot on the side of the failed engine feels no force. Further,

the engine instruments can help to analyze the situation.

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 17

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.

Depending on the situation the following attempts can be made to restore engine power

prior to securing the engine:

CAUTION

Once the engine has been shut down for longer than 30

seconds, it can only be restarted below 6000 ft pressure

altitude. Proceed in accordance with 3.5.4 - UNFEATHERING

& RESTARTING THE ENGINE IN FLIGHT.

1. POWER lever ........................ IDLE

NOTE

If the loss of power was due to unintentional setting of the

power lever, you may adjust the friction lock and continue your

flight.

2. If in icing conditions ................... alternate air ON

CONTINUED

Emergency

Procedures DA 42 AFM

Page 3 - 18 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

4. Fuel selector ......................... check ON / CROSSFEED if

required

NOTE

If the loss of power was due to unintentional setting of the fuel

selector to the OFF position you may continue your flight but

have the proper function of the restrainer locks checked prior

to next flight.

5. ECU SWAP.......................... ECU B

NOTE

If the swap to ECU B has restored engine power land as soon

as possible. If selecting ECU B does not solve the problem,

switch back to AUTOMATIC in order to maintain the engine

control system redundancy.

6. Circuit breakers....................... check / reset if necessary

CONTINUED

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 19

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.

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 20 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. Inoperative engine ..................... identify & verify

2. ENGINE MASTER inoperative engine ..... OFF

CAUTION

Do not shut down an engine with the fuel selector valve. The

high pressure fuel pump can otherwise be damaged.

Securing the feathered engine:

3. Alternator inoperative engine ............ OFF

4. Fuel selector inoperative engine .......... OFF

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 its fuel selector in the CROSSFEED

position.

If one of the power levers is set to low settings the landing

gear warning horn is activated. Set the power lever of the

secured engine forward as required to mute the warning horn.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 21

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. POWER lever affected engine ........... IDLE

3. FUEL SELECTOR affected engine ........ check ON

4. ALTERNATE AIR ..................... as required

5. ENGINE MASTER affected engine ........ ON

CAUTION

The propeller starts windmilling at airspeeds of 80 KIAS and

above. To avoid propeller overspeeds shortly after

unfeathering and restarting maintain airspeeds below

120 KIAS.

6. Starter affected engine ................. engage / if propeller does

not start windmilling by itself

CAUTION

Do not engage the starter if the propeller is windmilling! This

might damage the starter.

CONTINUED

Emergency

Procedures DA 42 AFM

Page 3 - 22 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

7. Alternator ........................... ON / if engine power has been

restored

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 23

3.5.5 ENGINE FAILURE DURING TAKEOFF

a) Engine failure during ground roll

- abort takeoff

1. POWER lever ........................ IDLE / BOTH

2. Rudder ............................. maintain directional control

3. Brakes ............................. as required

CAUTION

If sufficient time is remaining, the risk of fire in the event of

a collision with obstacles can be reduced as follows:

4. ENGINE MASTER .................... both OFF

5. FUEL SELECTOR .................... both OFF

6. ELECT. MASTER ..................... OFF

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 24 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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:

- decide whether to abort or to continue the take-off

Continued takeoff:

WARNING

A continued take-off is not recommended if the steady rate

of climb according to Section 5.3.9 ONE ENGINE

INOPERATIVE CLIMB performance is less than 3.3 %. Under

certain combinations of ambient conditions, such as

turbulence, crosswinds and wind shear as well as pilot skill

the resulting climb performance may nevertheless be

insufficient to continue the take-off successfully. Therefore

a continued take-off with a failed engine has to be avoided

if at all possible.

1. Power lever .......................... MAX

2. Rudder ............................. maintain directional control

3. Airspeed ............................ vYSE 82 KIAS / as required

4. Landing Gear ........................ UP to achieve a positive ROC

5. FLAPS.............................. check UP

CONTINUED

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 25

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

land as soon as possible according to 3.5.7 - LANDING WITH ONE ENGINE

INOPERATIVE.

If the situation allows, you may climb to a safe altitude for troubleshooting (3.5.2 - ENGINE

TROUBLESHOOTING) in order to try to restore engine power.

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 26 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

3.5.6 ENGINE FAILURES IN FLIGHT

(a) Engine Failure during Initial Climb at Airspeeds below vmCA 68 KIAS

WARNING

As the climb is a flight condition which is associated with high

power settings, airspeeds lower than vmCA 68 KIAS should be

avoided as a sudden engine failure can lead to loss of control.

In this case it is very important to reduce the asymmetry in

thrust to regain directional control.

1. Rudder ............................. apply for directional control

2. Power levers ......................... retard as required to maintain

directional control

3. Airspeed ............................ vYSE 82 KIAS / above vmCA 68

KIAS as required

4. Operative engine ...................... increase power as required if

directional control has been

re-established

CONTINUED

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 27

Establish minimum / zero sideslip condition. (approx. half ball towards good engine;

3° to 5° bank)

5. 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 Section 3.5.7 - LANDING WITH ONE ENGINE

INOPERATIVE.

If the situation allows, you may climb to a safe altitude for troubleshooting (3.5.2 - ENGINE

TROUBLESHOOTING) in order to try to restore engine power.

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 28 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

(b) Engine Failure during Initial Climb at Airspeeds above vmCA 68 KIAS

1. Rudder ............................. maintain directional control

2. Airspeed ............................ v

YSE 82 KIAS/ above vmCA 68

KIAS as required

3. Operative engine ...................... increase power as required if

directional control has been

established

Establish minimum / zero sideslip condition. (approx. half ball towards good engine;

3° to 5° bank)

4. 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 Section 3.5.7 - LANDING WITH ONE ENGINE

INOPERATIVE.

If the situation allows, you may climb to a safe altitude for troubleshooting (3.5.2 - ENGINE

TROUBLESHOOTING) in order to try to restore engine power.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 29

1. Rudder ............................. maintain directional control

2. Airspeed ............................ as required /

above vmCA 68 KIAS

3. Operative engine ..................... increase power as required if

directional control has been

established

Establish minimum / zero sideslip condition. (approx. half ball towards good engine;

3° to 5° bank)

4. 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 Section 3.5.7 - LANDING WITH ONE ENGINE

INOPERATIVE.

If the situation allows, you may climb to a safe altitude for troubleshooting (3.5.2 - ENGINE

TROUBLESHOOTING) in order to try to restore engine power.

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 30 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

3.5.7 LANDING WITH ONE ENGINE INOPERATIVE

Preparation:

1. Safety harnesses ..................... check fastened & tightened

2. Landing light ......................... as required

3. Gear warning horn .................... check function

Operative engine:

4. Fuel Selector......................... check ON / CROSSFEED as

required

Inoperative engine:

5. Engine.............................. check secured (feathered)

according to 3.5.3 - ENGINE

SECURING & FEATHERING

PROCEDURE

not before being certain of "making the field“:

6. Airspeed ............................ reduce to operate landing

gear

7. Landing Gear ........................ DOWN, check 3 green

8. Trim................................ as required

9. Airspeed ............................ reduce as required

10.FLAPS.............................. as required

11. Final approach speed

at 1700 kg (3748 lb) ................... 85 KIAS (v

REF/FLAPS UP)

82 KIAS (vREF/FLAPS APP)

76 KIAS (vREF/FLAPS LDG)

CONTINUED

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 3 - 31

at 1785 kg (3935 lb) ................... 86 KIAS (v

REF/FLAPS UP)

82 KIAS (vREF/FLAPS APP)

78 KIAS (vREF/FLAPS LDG)

WARNING

One-engine inoperative approaches for landing with flap

settings of more than flaps UP are not recommended unless

a safe landing is assured („Making the field“). Higher flap

settings increase the loss of altitude during the transition to

a one engine inoperative go-around / balked landing.

12.POWER lever ........................ as required

13.Trim ............................... as required / directional trim to

neutral

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.

CONTINUED

Emergency

Procedures DA 42 AFM

Page 3 - 32 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

For performance data with one engine inoperative and flaps

and gear UP refer to 5.3.9 ONE ENGINE INOPERATIVE

CLIMB PERFORMANCE.

Under certain combinations of ambient conditions, such as

turbulence, cross wind and windshear, as well as pilot skill,

the resulting climb performance may nevertheless be

insufficient for a successful go-around / balked landing.

14.POWER lever ........................ MAX / as required

15. Rudder ............................. maintain directional control

16. Airspeed ............................ vYSE = 82 KIAS / as required

17. Landing Gear ........................ UP / retract

18.FLAPS.............................. UP

-Establish minimum sideslip and manoeuver for a new attempt to land. Repeat from

step 1 of this section.

CONTINUED

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 33

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.ENGINE MASTER .................... both OFF

20.FUEL SELECTOR .................... both OFF

21.ELECT. MASTER ..................... OFF

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 34 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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 vmCA 68 KIAS to

maintain directional control

2. Remaining engine ..................... monitor engine instruments

continuously

3. Fuel quantity ......................... monitor continuously

4. FUEL SELECTOR..................... Remaining engine / set

CROSSFEED or ON so as to

keep fuel quantity laterally

balanced

NOTE

If the Fuel Selector is set on CROSSFEED, the engine will

be supplied with fuel from the main tank on the opposite side.

This will extend range and helps to keep the wings laterally

balanced (see 2.14 FUEL).

Land as soon as possible according to Section 3.5.7 - LANDING WITH ONE ENGINE

INOPERATIVE.

If the situation allows, you may climb to a safe altitude for troubleshooting (3.5.2 - ENGINE

TROUBLESHOOTING) in order to try to restore engine power.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 35

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.

If the light remains on for longer than 20 seconds during landing gear retraction / extension:

1. Airspeed ............................ check below v

LOR 156 KIAS

2. Gear selector ........................ re-cycle if continued illumination

occurs

If the landing gear cannot be extended to the down & locked position or red light does

not extinguish:

- Continue with 3.6.2 MANUAL EXTENSION OF THE LANDING GEAR.

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.

Emergency

Procedures DA 42 AFM

Page 3 - 36 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

In cold ambient temperatures it may help to reduce the

airspeed below 110 KIAS for landing gear operation.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 37

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.

The following checks shall be completed before extending the landing gear manually:

1. Gear indicator lights ................... test / push test button

2. ELECT. MASTER .................... check ON

3. Bus voltage.......................... check in normal range

4. Circuit breaker ....................... check in / reset if necessary

CONTINUED

Emergency

Procedures DA 42 AFM

Page 3 - 38 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Manual landing gear extension procedure:

5. Gear selector ........................ select DOWN

6. Manual gear extension handle ........... pull out

NOTE

The landing gear should now extend by gravity and relief of

hydraulic pressure from the system. If one or more landing

gear indicator lights do not indicate the gear down & locked

after completion of the manual extension procedure steps 1 -

6 reduce airspeed below 110 KIAS and apply moderate yawing

and pitching to bring the landing gear into the locked position.

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.

If the landing gear cannot be extended to the down & locked position continue

according to 3.6.3 LANDING WITH GEAR UP.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 39

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. POWER lever ....................... IDLE / just before

touchdown

If the time / situation allows, the following steps can help to reduce the risk of fire:

3. ENGINE MASTER .................... both OFF

4. FUEL SELECTOR .................... both OFF

5. ELECT. MASTER ..................... OFF

Touchdown:

6. Touchdown ......................... Contact surface with minimum

airspeed

7. On ground .......................... Maintain directional control with

rudder as long as possible so as

to avoid collision with obstacles

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 40 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. Rapid and determined action is then

required.

1. Advise ATC.

2. Land the airplane at the edge of the runway that is located on the side of the intact

tire, so that changes in direction which must be expected during roll-out due to the

braking action of the defective tire can be corrected on the runway.

3. Land with one wing low. The wing on the side of the intact tire should be held low.

4. Direction should be maintained using the rudder. This should be supported by use

of the brake. It is possible that the brake must be applied strongly - if necessary

to the point where the wheel locks. The wide track of the landing gear will prevent

the airplane from tipping over a wide speed range. There is no pronounced tendency

to tip even when skidding.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 41

3.6.5 LANDING WITH DEFECTIVE BRAKES

Consider the greater rolling distance.

Safety harness ........................... check fastened and tightened

CAUTION

If sufficient time is remaining, the risk of fire in the event of

a collision can be reduced as follows after a safe touch-down:

ENGINE MASTER ............. both OFF

FUEL SELECTOR ............. both OFF

ELECT. MASTER .............. OFF

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 42 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. EMERGENCY SWITCH ................ ON

3. Flood light, if necessary ................ ON

4. POWER ............................ set based on lever positions

and engine noise

5. Prepare landing with flaps in the given position. Refer to 4B.5 - FAILURES IN

FLAP OPERATING SYSTEM.

6. Land on the nearest suitable airfield.

WARNING

Engine stoppage may occur, depending on the failure mode.

NOTE

The landing gear uplock is no longer ensured. The landing

gear may slowly extend.

The landing gear can be extended manually according to 3.6.2

MANUAL EXTENSION OF THE LANDING GEAR.

NOTE

The backup artificial horizon and the flood light will have

electrical power for at least 1.5 hours.

Make use of the stand-by airspeed indicator and altimeter. Engine power can be set via

visual reference of the power lever position.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 43

3.7.2 HIGH CURRENT

If high current is indicated on the G1000:

1. Circuit breakers ...................... check

2. Reduce electric load to minimum required for continued safe flight.

3. Land on the nearest suitable airfield.

END OF CHECKLIST

3.7.3 STARTER MALFUNCTION

If the starter does not disengage from the engine after starting (starter engaged warning

(STARTER ENGD) on the G1000 annunciator field remains illuminated after the engine

has started):

1. POWER lever affected engine ........... IDLE

2. ENGINE MASTER affected engine ........ OFF

3. ELECT. MASTER ..................... OFF

Terminate flight preparation!

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 44 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

3.8 SMOKE AND FIRE

3.8.1 ENGINE FIRE ON GROUND

1. ENGINE MASTER .................... both OFF

2. FUEL SELECTOR..................... both OFF

3. ELECT. MASTER ..................... OFF

after standstill:

4. Canopy ............................. open

5. Airplane............................. evacuate immediately

END OF CHECKLIST

3.8.2 ENGINE FIRE DURING TAKE-OFF

Proceed according to 3.5.5 - ENGINE FAILURES DURING TAKEOFF

1. Cabin heat & Defrost ................... OFF

CAUTION

In case of extreme smoke development, the front canopy may

be unlatched during flight. This allows it to partially open, in

order to improve ventilation. The canopy will remain open in

this position. Flight characteristics will not be affected

significantly.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 45

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.

CAUTION

In case of extreme smoke development, the front canopy may

be unlatched during flight. This allows it to partially open, in

order to improve ventilation. The canopy will remain open in

this position. Flight characteristics will not be affected

significantly.

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 46 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

3.8.4 ELECTRICAL FIRE ON GROUND

1. ELECT. MASTER ..................... OFF

if the engine is running:

2. POWER lever ........................ both IDLE

3. ENGINE MASTER .................... both OFF

4. FUEL SELECTOR..................... both OFF

when the engine has stopped / after standstill:

5. Canopy ............................. open

6. Airplane............................. evacuate immediately

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 47

3.8.5 ELECTRICAL FIRE IN FLIGHT

1. EMERGENCY SWITCH ................ ON, if installed

2. AVIONIC MASTER.................... OFF

3. ELECT. MASTER ..................... OFF

4. Cabin heat & Defrost .................. OFF

5. Emergency windows ................... open if required

6. Land at the next suitable airfield

CAUTION

Switching OFF the ELECTRIC MASTER will lead to total

failure of all electronic and electric equipment. The attitude

gyro (artificial horizon) and the directional gyro, if installed,

will also be affected.

However, by switching the EMERGENCY switch ON, the

emergency battery will supply power to the stand-by attitude

gyro (artificial horizon) and the flood light.

In case of extreme smoke development, the front canopy may

be unlatched during flight. This allows it to be partially opened,

in order to improve ventilation. The canopy will remain open

in this position. Flight characteristics will not be affected

significantly.

The maximum demonstrated airspeed for emergency opening

the front canopy in flight is 120 KIAS. Do not exceed 120

KIAS.

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 48 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. The occurrence of CO in the cabin is possible only due to a defect. If a smell similar

to exhaust gases is noticed in the cabin, the following measures should be taken:

1. Cabin heat & Defrost ................... OFF

2. Ventilation ........................... open

3. Emergency windows ................... open

4. Forward canopy ...................... unlatch, push up and lock in

"cooling-gap“ position

CAUTION

The maximum demonstrated airspeed for emergency opening

the front canopy in flight is 120 KIAS. Do not exceed 120

KIAS.

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 49

3.9.2 UNLOCKED DOORS

1. Airspeed ............................ reduce

2. Canopy ............................. check visually if closed

3. Rear passenger door .................. check visually if closed

4. Front baggage doors .................. check visually if closed

WARNING

Never unlock the rear passenger door during flight. It may

break away.

5. If it is not possible to lock the canopy or the rear passenger door, or if one or

both of the front baggage doors are open, land on the nearest suitable airfield.

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 50 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

WARNING

In case of a malfunction of the engine control unit it is possible

that the propeller blades will remain in the position of highest

pitch. In this case the reduced engine performance should be

taken into consideration.

(a) Oscillating RPM

1. POWER setting....................... change

if the problem does not clear:

2. ECU SWAP.......................... ECU B

NOTE

If the problem does not clear itself, switch back to AUTO and

land on the nearest suitable airfield.

CONTINUED

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 51

(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. ECU SWAP ......................... ECU B

CAUTION

If the problem does not clear itself, switch back to AUTO and

land on the nearest suitable airfield. Prepare for engine

malfunction according to 3.5.6 ENGINE FAILURES IN FLIGHT

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 52 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. Cabin heat & Defrost ................... ON

4. POWER lever ........................ increase power, in order to

prevent ice build-up on the

propeller blades, apply power

changes periodically.

5. ALTERNATE AIR ..................... OPEN

6. Emergency windows ................... open if required

CAUTION

Ice build-up increases the stalling speed.

7. ATC................................ advise if an emergency is

expected

CAUTION

If the Pitot heating fails:

Alternate static valve ............ OPEN

Emergency windows ............ close

END OF CHECKLIST

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 53

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.

2. Fuel quantity ......................... monitor

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 54 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

Single-engine stalling is not permitted.

CAUTION

Steps 1 to 4 must be carried out immediately and

simultaneously.

1. POWER lever ........................ IDLE

2. Rudder ............................. full deflection against

direction of spin

3. Elevator (control stick).................. fully forward

4. Ailerons ............................. neutral

5. FLAPS.............................. UP

CONTINUED

DA 42 AFM Emergency

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 3 - 55

when rotation has stopped:

6. Rudder ............................. neutral

7. Elevator (control stick) ................. pull carefully

8. Return the airplane from a descending into a normal flight attitude. Do not

exceed the 'never exceed speed', vNE = 194 KIAS.

END OF CHECKLIST

Emergency

Procedures DA 42 AFM

Page 3 - 56 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

3.9.7 EMERGENCY DESCENT

1. FLAPS.............................. UP

2. Gear ............................... DOWN

3. POWER lever ........................ IDLE

4. Airspeed ............................ as required

WARNING

Max. structural cruising speed ........v

NO = 155 KIAS.

Never exceed speed in smooth air ....v

NE = 194 KIAS.

END OF CHECKLIST

3.9.8 EMERGENCY EXIT

In case of a roll over of the airplane on ground, the rear side door can be used as exit.

For this purpose unlock the front hinge of the rear side door. The function is displayed

on a placard beside the hinge.

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 1

CHAPTER 4A

NORMAL OPERATING PROCEDURES

Page

4A.1 INTRODUCTION ..................................... 4A-3

4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES .... 4A-3

4A.3 ADVISORY ALERTS ON THE G1000 ..................... 4A-5

4A.3.1 ADVISORY / GENERAL.......................... 4A-5

4A.3.2 L/R GLOW ON ................................. 4A-5

4A.3.3 L/R FUEL XFER ................................ 4A-5

4A.3.4 PFD/MFD/GIA FAN FAIL ......................... 4A-5

4A.4 FLIGHT CHARACTERISTICS ........................... 4A-6

4A.5 DAILY CHECK ....................................... 4A-7

4A.6 CHECKLISTS FOR NORMAL OPERATING PROCEDURES . . . 4A-7

4A.6.1 PRE-FLIGHT INSPECTION ....................... 4A-7

4A.6.2 BEFORE STARTING ENGINE.................... 4A-19

4A.6.3 STARTING ENGINE............................ 4A-21

4A.6.4 BEFORE TAXIING ............................. 4A-23

4A.6.5 TAXIING ..................................... 4A-24

4A.6.6 BEFORE TAKE-OFF ........................... 4A-25

4A.6.7 TAKE-OFF ................................... 4A-30

4A.6.8 CLIMB ...................................... 4A-32

4A.6.9 CRUISE ..................................... 4A-33

4A.6.10 DESCENT .................................. 4A-34

4A.6.11 APPROACH & LANDING ....................... 4A-35

4A.6.12 GO-AROUND ................................ 4A-36

4A.6.13 AFTER LANDING............................. 4A-36

Normal Operating

Procedures DA 42 AFM

Page 4A - 2 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

4A.6.14 SHUT-DOWN ................................ 4A-37

4A.6.15 PARKING ................................... 4A-38

4A.6.16 EXIT AIRPLANE .............................. 4A-38

4A.6.17 POST FLIGHT INSPECTION .................... 4A-38

4A.6.18 FLIGHT IN RAIN.............................. 4A-38

4A.6.19 REFUELING ................................. 4A-39

4A.6.20 FLIGHT AT HIGH ALTITUDE .................... 4A-40

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 3

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

FLAPS

up to 1700 kg

above 1700 kg1

(above 3748 lb)

Airspeed for rotation (take-off run, vR)UP

min. 70 KIAS

min. 72 KIAS

Airspeed for take-off climb

(best rate-of-climb speed vY)UP

min. 77 KIAS

min. 79 KIAS

Airspeed for best angle of climb2

77 KIAS

79 KIAS

Airspeed for cruise climb UP

min. 85 KIAS

min. 86 KIAS

Reference landing approach speed UP

85 KIAS

86 KIAS

APP

min. 82 KIAS

82 KIAS

Final approach speed LDG

min. 76 KIAS

min. 78 KIAS

Minimum speed during go-around UP

min. 82 KIAS

Max. structural cruising speed

Do not exceed this speed except in

smooth air, and then only with

caution.

155 KIAS

1), 2) see NOTES on next page

Normal Operating

Procedures DA 42 AFM

Page 4A - 4 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. It

constitutes an abnormal operating procedure. A "Hard

Landing Check" is only required after a hard landing,

regardless of the actual landing mass.

NOTE

vx is always less than vy. For the DA 42 however, the actual

value of vx would be below the minimum safe speed. The

minimum airspeed for best angle of climb was therefore raised

to the value of vy.

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 5

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

CHARACTERISTICS White color coded text

4A.3.2 L/R GLOW ON

L/R GLOW ON Left / Right engine glow plug active

4A.3.3 L/R FUEL XFER

L/R FUEL XFER Fuel transfer from auxiliary to main tank is in progress (if

aux. tanks are installed)

4A.3.4 PFD/MFD/GIA FAN FAIL

PFD FAN FAIL Cooling Fan for the PFD is inoperative

MFD FAN FAIL Cooling Fan for the MFD is inoperative

GIA FAN FAIL Cooling Fan for the GIA is inoperative

The flight may be continued, but maintenance action is required after landing.

Normal Operating

Procedures DA 42 AFM

Page 4A - 6 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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

applied, the airplane 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.

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 7

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.

* On-condition check of the hinges for the canopy, the side door and the baggage

compartment doors.

* Visual inspection of the locking bolts for proper movement with no backlash.

* Tire inflation pressure check (main wheels: 4.5 bar/65 psi, nose wheel: 6.0 bar/87 psi).

* Visual inspection of both spinners and their attachment.

* If OÄM-42-077 (Removable Fuselage Nose Cone) is implemented: %

Check fuselage nose cone for improper fit and loose attachment screws.%

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 & Balance............. flight planning completed

c) Airplane documents ................... complete and up-to-date

d) Front canopy & rear door ............... clean, undamaged,

check locking mechanism

function

e) Baggage ............................ stowed and secured

f) Foreign objects ....................... check

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 8 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Center console:

a) FUEL SELECTOR..................... check ON

b) POWER Lever........................ check condition, freedom of

movement and full travel /

adjust friction, set IDLE

Below instrument panel in front of left seat:

a) ALTERNATE STATIC SOURCE .......... check CLOSED

b) MANUAL GEAR EXTENSION HANDLE . . . check pushed in

c) ALTERNATE AIR ..................... check CLOSED

On the instrument panel:

a) ALTERNATOR ....................... check ON

b) ECU SWAP.......................... check AUTOMATIC

c) PITOT HEAT......................... check OFF

d) ENGINE MASTER .................... check both OFF

e) START KEY ......................... check key is pulled out

f) ELECT. MASTER ..................... check OFF

g) AVIONIC MASTER .................... check OFF

h) GEAR SELECTOR .................... check DOWN

i) FLAP SELECTOR..................... check UP

j) Circuit breakers....................... set in (if one has been pulled,

check reason)

k) All electrical equipment ................. OFF

l) EMERGENCY SWITCH ................ check OFF & guarded

m) ELT ................................ armed

CONTINUED

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 9

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. Should the

pump continue to operate continuously or periodically,

terminate flight. There is a malfunction in the landing gear

system.

b) Fuel quantity ......................... check indication, verify using

alternate means (see Section

7.9.5)

c) Position lights, strobe lights (ACL) ........ check for correct function

CAUTION

Do not look directly into the anti collision lights.

d) Landing / Taxi light .................... check for correct function

e) Stall warning / stall heat / Pitot heat ....... check

f) Gear warning /

Fire detector TEST BUTTON ............ PUSH, check aural alert / fire

detection warning and aural alert

CAUTION

If the aural alert or the warning on the PFD does not appear,

terminate flight. Unscheduled maintenance is necessary.

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 10 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

g) Control stick ......................... pull fully aft / hold at backstop

h) FLAPS.............................. set LDG position

i) POWER Lever........................ set MAX

j) Variable elevator backstop .............. check function / control stick must

move slightly forward during

power lever forward movement

k) POWER Lever........................ set IDLE

l) Variable elevator backstop .............. check function / control stick must

regain full movement during

power lever retraction

m) FLAPS.............................. set UP position

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.

If the variable elevator backstop does not function properly,

terminate flight.

n) ELECT. MASTER ..................... OFF

o) Flight controls ........................ check free & correct movement

up to full deflection

p) Trims............................... check free & correct movement

up to full deflection

END OF CHECKLIST

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 11

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.

CAUTION

In low ambient temperatures the airplane must be completely

cleared of ice, snow and similar accumulations. For approved

de-icing fluids refer to Section 8.6 - DE-ICING.

CAUTION

Prior to flight, remove such items as control surfaces gust

lock, Pitot cover, tow bar, etc.

1. Left main landing gear:

a) Landing gear strut & lock ............... visual inspection, sufficient height

(typical visible length of bare

piston: at least 4 cm/1.6")

b) Down & Uplock switches (3x) ............ visual inspection

c) Wear, tread depth of tire ................ visual inspection

d) Tire, wheel, brake ..................... visual inspection

e) Brake line connection .................. check for leaks

f) Slip marks........................... visual inspection

g) Chocks ............................. remove

h) Landing gear door ..................... visual inspection

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 12 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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 ...................... check visually (inspection hole in

the lower cowling)

d) Cowling ............................. visual inspection

e) Gascolator / air inlet ................... drain off to check for water and

sediment (drain until no water

comes out) / clear

f) Venting pipe ......................... check for blockage

g) Exhaust ............................. visual inspection

WARNING

The exhaust can cause burns when hot.

h) Propeller ............................ visual inspection

WARNING

Never move the propeller by hand while the ENGINE

MASTER switch is ON! Also do not move the propeller by

hand while the ENGINE MASTER is OFF immediately after

operation (remaining pressure in the injection system rail).

Serious personal injury may result.

CONTINUED

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 13

i) Nacelle underside ..................... check for excessive

contamination particularly by oil,

fuel, and other fluids

j) Auxiliary tank vent outlet on lower surface . . visual inspection

k) Auxiliary tank drain .................... drain off to check for water and

sediment (drain until no water

comes out) / visual inspection

l) Auxiliary tank filler ..................... visual inspection, tank filler closed

3. Left wing:

a) Entire wing surface .................... visual inspection

b) Tank air outlet on lower surface .......... visual inspection

c) Tank drain / tank air inlet ............... drain off to check for water and

sediment (drain until no water

comes out) / visual inspection

d) Openings on lower surface .............. check for foreign objects and for

traces of fuel (if tank is full, fuel

may spill over through the tank

vent)

e) Stall warn device...................... visual inspection

f) Tank filler ........................... visual inspection, check closed

g) Pitot probe .......................... clean, orifices clear, cover

removed, no deformation

h) Wing tip............................. visual inspection

i) Static dischargers ..................... visual inspection

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 14 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

j) Position light, strobe light (ACL) .......... visual inspection

k) Tie-down ............................ check, clear

l) Aileron and linkage .................... visual inspection

m) Aileron hinges and safety pin ............ visual inspection

n) Foreign objects in aileron paddle ......... visual inspection

o) Flap and linkage ...................... visual inspection

p) Flap hinges and safety pin .............. visual inspection

q) Nacelle underside fuel cooler air in- & outlet . check clear

r) Step................................ visual inspection

4. Fuselage, left side, underside:

a) Canopy, left side ...................... visual inspection

b) Rear cabin door & window .............. visual inspection

c) Fuselage skin ........................ visual inspection

d) Antennas ............................ visual inspection

e) Fuselage ............................ check for contamination

(hydraulic fluid)

5. Empennage:

a) Stabilizers and control surfaces,

elevator tips.......................... visual inspection

b) Hinges .............................. visual inspection

c) Elevator trim tab ...................... visual inspection, check safetying

d) Rudder trim tab ....................... visual inspection, check safetying

e) Tie-down ............................ check, clear

f) Tail skid and lower fin .................. visual inspection

g) Static dischargers ..................... visual inspection

CONTINUED

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 15

6. Fuselage, right side:

a) Fuselage skin ........................ visual inspection

b) Rear window ......................... visual inspection

c) Canopy, right side ..................... visual inspection

7. Right Main Landing Gear:

a) Landing gear strut & lock ............... visual inspection, sufficient height

(typical visible length of bare

piston: at least 4 cm/1.6")

b) Down & Uplock switches (3x) ............ visual inspection

c) Wear, tread depth of tire ................ visual inspection

d) Tire, wheel, brake ..................... visual inspection

e) Brake line connection .................. check for leaks

f) Slip marks........................... visual inspection

g) Chocks ............................. remove

h) Landing gear door ..................... visual inspection

8. Right wing:

a) Entire wing surface .................... visual inspection

b) Tank air outlet on lower surface .......... visual inspection

c) Tank drain / tank air inlet ............... drain off to check for water and

sediment (drain until no water

comes out) / visual inspection

d) Openings on lower surface .............. check for foreign objects and for

traces of fuel (if tank is full, fuel

may spill over through the tank

vent)

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 16 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

e) Tank filler ........................... visual inspection, check closed

f) Pitot probe........................... clean, orifices clear, cover

removed, no deformation

g) Wing tip ............................. visual inspection

h) Static dischargers ..................... visual inspection

i) Position light, strobe light (ACL) .......... visual inspection

j) Tie-down ............................ check, clear

k) Aileron and linkage .................... visual inspection

l) Aileron hinges and safety pin ............ visual inspection

m) Foreign objects in aileron paddle ......... visual inspection

n) Flap and linkage ...................... visual inspection

o) Flap hinges and safety pin .............. visual inspection

p) Nacelle underside fuel cooler air in- & outlet . check clear

q) Step................................ visual inspection

r) Cabin vent air inlet .................... check clear

9. Right engine nacelle:

a) 3 air inlets / 2 air outlets ................ clear

b) Engine oil level ....................... check dipstick (inspection hole in

the upper cowling)

c) Gearbox oil level ...................... check visually (inspection hole in

the lower cowling)

d) Cowling ............................. visual inspection

CONTINUED

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 17

e) Gascolator / air inlet ................... drain off to check for water and

sediment (drain until no water

comes out) / clear

f) Venting pipe ......................... check for blockage

g) Exhaust ............................. visual inspection

WARNING

The exhaust can cause burns when hot.

h) Propeller ............................ visual inspection

WARNING

Never move the propeller by hand while the ENGINE

MASTER switch is ON! Also do not move the propeller by

hand while the ENGINE MASTER is OFF immediately after

operation (remaining pressure in the injection system rail).

Serious personal injury may result.

i) Nacelle underside ..................... check for excessive

contamination particularly by oil,

fuel, and other fluids

j) Auxiliary tank vent outlet on lower surface . . visual inspection

k) Auxiliary tank drain .................... drain off to check for water and

sediment (drain until no water

comes out) / visual inspection

l) Auxiliary tank filler ..................... visual inspection, tank filler closed

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 18 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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")

c) Down & Uplock switches................ visual inspection

d) Wear, tread depth of tire ................ check

e) Slip marks ........................... visual inspection

f) Gear door and linkage .................. visual inspection

g) Chocks ............................. remove

h) OAT sensor.......................... check

i) EPU connector ....................... check

j) Tow bar ............................. remove

END OF CHECKLIST

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 19

4A.6.2 BEFORE STARTING ENGINE

1. Pre-flight inspection ................... complete

2. Passengers ......................... instructed

NOTE

Ensure all the passengers have been fully briefed on the use

of the seat belts, doors and emergency exits and the ban on

smoking.

3. Rear door ........................... closed and locked

CAUTION

When operating the canopy, pilots/operators must ensure that

there are no obstructions between the canopy and the mating

frame, for example seat belts, clothing, etc. When operating

the locking handle do NOT apply undue force.

A slight downward pressure on the canopy may be required

to ease the handle operation.

4. Front canopy ......................... Position 1 or 2 (“cooling gap”)

5. Rudder pedals ....................... adjusted and locked

6. Safety harnesses ..................... all on and fastened

7. POWER lever ........................ check IDLE

8. Parking brake ........................ set

9. AVIONIC MASTER ................... check OFF

10. GEAR selector ....................... check DOWN

11.ECU SWAP ......................... check AUTOMATIC

12.ALTERNATORS ...................... check ON

13.ELECT. MASTER ..................... ON

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 20 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. There is a malfunction in the

landing gear system.

14. G1000 .............................. wait until power-up completed.

Press ENT on MFD to

acknowledge.

NOTE

The engine instruments are only available on the MFD after

item 14 has been completed.

15.Fuel temperature...................... check

WARNING

If Diesel fuel or a blend of Diesel fuel with Jet A-1 is used

(approved only if MÄM 42-037 is carried out), or if the fuel

grade is unknown, the engine must not be started if the fuel

temperature indication prior to operation is below -5 °C

(+23 °F).

Operation with a fuel temperature below -5 °C (+23 °F) is not

permitted, as safe operation of the engine under those

conditions cannot be ensured and the engine can stop.

NOTE

Make sure which fuel grade is being used (see Section 7.9.5).

If it is not possible to determine the fuel grade, the Diesel fuel

temperature limitations must be observed.

END OF CHECKLIST

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 21

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. If

required by operational reasons, the RH engine can also be

started first.

3. Annunciations ........................ check „L/R ENGINE GLOW“ ON

4. Annunciations / Engine / System Page ..... check OK / normal range

WARNING

Before starting the engine the pilot must ensure that the

propeller area is free, and no persons can be endangered.

After the L/R ENGINE GLOW indication is extinguished:

5. START KEY ......................... START L/R as required / release

when engine has started

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 22 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

If the „L/R STARTER“ annunciation does not extinguish after

the engine has started and the START KEY has been

released, set the ENGINE MASTER to OFF and investigate

the problem.

6. Annunciations / Engine / System Page ..... check OK / normal range

7. Annunciations / Starter ................. check OFF

8. Annunciations / Oil pressure ............. check OK

WARNING

If the oil pressure has not moved from the red range within

3 seconds after starting, set the ENGINE MASTER switch

to OFF and investigate problem. When starting the cold

engine, the oil pressure can be as high as 6.5 bar for a

maximum of 20 seconds.

7. Circuit breakers....................... check all in / as required

8. Idle RPM ............................ check, 900 ±20 RPM

Repeat with opposite engine.

9. Warm up ............................ IDLE for 2 minutes /

thereafter 1400 RPM

END OF CHECKLIST

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 23

4A.6.4 BEFORE TAXIING

1. AVIONIC MASTER.................... ON

2. Electrical equipment ................... ON as required

3. Flight instruments and avionics .......... set as required

4. Flood light ........................... ON, test function, as

required

5. Pitot and stall warn heating .............. ON, check annunciation

6. Pitot and stall warn heating .............. OFF

7. Strobe lights (ACL's) ................... check ON

8. Position lights, landing and taxi lights ...... as required

CAUTION

When taxiing at close range to other aircraft, or during night

flight in clouds, fog or haze, the strobe lights should be

switched OFF. The position lights must always be switched

ON during night flight.

END OF CHECKLIST

Normal Operating

Procedures DA 42 AFM

Page 4A - 24 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

4A.6.5 TAXIING

1. Parking brake ........................ release

2. Brakes.............................. test on moving off

3. Nose wheel steering ................... check for proper function

4. Flight instrumentation and avionics ........ check for correct indications

5. FUEL SELECTOR..................... CROSSFEED (LH/RH)

CAUTION

The fuel crossfeed function can be tested simultaneously with

both engines. Proper function can be tested by running the

engines for approx. 30 seconds with crossfeed selected. The

operation of both engines with both fuel selectors in crossfeed

position, other than for this test, is prohibited.

6. FUEL SELECTOR .................... ON (LH/RH)

CAUTION

When taxiing on a poor surface select the lowest possible

RPM to avoid damage to the propeller from stones or similar

items.

END OF CHECKLIST

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 25

4A.6.6 BEFORE TAKE-OFF

1. Position airplane into wind if possible.

2. Parking brake ........................ set

3. Safety harnesses ..................... on and fastened

4. Rear door ........................... check closed and locked

CAUTION

When operating the canopy, pilots/operators must ensure that

there are no obstructions between the canopy and the mating

frame, for example seat belts, clothing, etc. When operating

the locking handle do NOT apply undue force.

A slight downward pressure on the canopy may be required

to ease the handle operation.

5. Front canopy ......................... closed and locked

6. Front baggage doors .................. closed (visual check)

7. Door warning (DOOR) ................. check no indication

8. Annunciations / Engine / System Page ..... check OK / normal range

(except pressure may be in the

yellow range with a warm engine

and power lever at IDLE)

9. Circuit breakers ...................... check pressed in

10. Longitudinal Trim ..................... set T/O

11.FUEL SELECTOR .................... check ON (LH/RH)

12. Directional Trim ....................... neutral

13.FLAPS ............................. check function & indicator /

set UP

14.Flight controls ........................ unrestricted free movement,

correct sense

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 26 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. Terminate flight preparation.

The whole test procedure must be completed without any

error. In case of an error terminate flight preparation, even

when the engine seems to run smoothly after the test

procedure.

1. Power lever .......................... IDLE

2. ECU TEST BUTTON................... press and hold

CONTINUED

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 27

Annunciations in the following sequence:

3. ECU A/B FAIL LIGHTS................. ON

4. Propeller RPM ....................... increase

5. ECU A/B FAIL LIGHTS ................ OFF

6. ECU B FAIL LIGHT.................... ON

7. Propeller RPM ....................... decrease / increase

8. ECU B FAIL LIGHT.................... OFF

9. ECU A FAIL LIGHT.................... ON

10. Propeller RPM ....................... decrease / increase

11. ECU A FAIL LIGHT ................... OFF

12. Propeller RPM ....................... decrease to idle

Test sequence completed.

CAUTION

When switching from one ECU to the other a slight shake of

the engine may occur. In case of longer dropouts of the

engine, or if the engine stops during the test, terminate flight

preparation.

13.ECU TEST BUTTON .................. release

14.ECU SWAP ......................... ECU B

15.Engine ............................. check running without a change

16.ECU SWAP ......................... AUTOMATIC

NOTE

When switching from one ECU to the other a slight shake of

the engine may occur.

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 28 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

17. Pitot heating ......................... ON, if required

18. Landing light ......................... ON, if required

Available power check:

1. POWER lever ........................ MAX for 10 seconds

2. Annunciations ........................ check OK / normal range

3. Instruments .......................... check within normal range

3. RPM ............................... stabilizes at 2240 to 2300 RPM

4. LOAD indication ...................... stabilizes at 90 to 100 %

5. POWER lever ........................ IDLE

CAUTION

Under high temperature and high altitude conditions, load

indications below 90 % are possible. If the engine does not

stabilize at the target RPM of 2240 to 2300 RPM terminate

flight preparation.

6. Engine instruments .................... check in green range (except oil

pressure may be in yellow range

with a warm engine and power

lever at IDLE, and fuel temp may

be in the low yellow range if the

airplane is operated with JET A-1)

CONTINUED

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 29

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.

END OF CHECKLIST

Normal Operating

Procedures DA 42 AFM

Page 4A - 30 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

4A.6.7 TAKE-OFF

1. Transponder ......................... as required

2. POWER lever ........................ MAX

NOTE

The proper and symmetric performance of the engines at

MAX should be checked early during the take-off run, so that

the take-off can be aborted if necessary.

3. Elevator............................. neutral

4. Rudder ............................. maintain direction

NOTE

In strong crosswinds steering can be augmented by use of

the toe brakes. It should be noted, however, that this method

increases the take-off roll, and should not generally be used.

5. Nose wheel lift-off:

up to 1700 kg (3748 lb) ............... v

R minimum 70 KIAS

above 1700 kg (3748 lb) .............. v

R minimum 72 KIAS

6. Airspeed for initial climb:

up to 1700 kg (3748 lb) ............... Minimum 77 KIAS, recommended

82 KIAS (vySE) when clear of

obstacles.

above 1700 kg (3748 lb) .............. Minimum 79 KIAS, recommended

82 KIAS (vySE) when clear of

obstacles.

CONTINUED

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 31

when safe climb is established:

7. LANDING GEAR...................... apply brakes; UP,

check unsafe light off

NOTE

To avoid damage and excessive wear of the main landing

gear wheels, firmly apply brakes before selecting gear up.

END OF CHECKLIST

Normal Operating

Procedures DA 42 AFM

Page 4A - 32 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

4A.6.8 CLIMB

Initial climb check

1. Landing light ......................... OFF / as required

2. Landing Gear ........................ check UP

3. FLAPS.............................. check UP

4. Airspeed:

up to 1700 kg (3748 lb) ............... 77 KIAS (best rate-of-climb)

85 KIAS / as required for en-route

(cruise) climb

above 1700 kg (3748 lb) .............. 79 KIAS (best rate-of-climb)

86 KIAS / as required for en-route

(cruise) climb

5. POWER lever ........................ MAX

6. Trim................................ as required (ball centered)

7. Annunciations / Engine / System Page ..... monitor

CAUTION

If the oil temperature and/or coolant temperature reaches the

yellow range during climb, flight should be continued with the

airspeed increased by 10 kts and power reduced by 10 %

(reduced climb rate) for better engine cooling.

END OF CHECKLIST

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 33

4A.6.9 CRUISE

1. POWER lever ........................ performance as required

NOTE

The engine manufacturer recommends a cruise power setting

of 70 %.

2. Trim ............................... as required

3. Annunciations / Engine / System Page ..... monitor

END OF CHECKLIST

Use of the Auxiliary fuel tanks (if installed)

The auxiliary fuel tanks are optional equipment (OÄM 42-056).

CAUTION

When operating the FUEL TRANSFER LH/RH switch, make

sure not to exceed the fuel imbalance limitations given in

Section 2.14.

To avoid additional imbalance in the auxiliary tanks both

FUEL TRANSFER switches must be operated simultaneously.

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.

Monitor the fuel quantity indicator to verify that fuel is transferred properly. (approx.

1 US gal per minute). If no fuel is transferred, proceed according to Section 4B.4.10

L/R FUEL XFER FAIL.

CONTINUED

Normal Operating

Procedures DA 42 AFM

Page 4A - 34 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

END OF CHECKLIST

4A.6.10 DESCENT

1. POWER lever ........................ as required

2. Airspeed ............................ as required

3. Trim................................ as required

4. Annunciations / Engine / System Page ..... monitor

END OF CHECKLIST

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 35

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. Controls ............................ no interference by foreign objects

3. Landing light ......................... as required

4. Gear warning horn .................... check function

5. Fuel Selector ........................ check ON

6. LANDING GEAR...................... DOWN, check 3 green

7. Parking brake ........................ check released

8. Trim ............................... as required, directional trim

neutral

Before landing:

9. Airspeed ............................ min. 82 KIAS with FLAPS APP

min. 85 KIAS with FLAPS UP

10.FLAPS ............................. as required

11.POWER lever ........................ as required

12.Trim ............................... as required, directional trim

neutral

13. Final Approach speed .................. min. 76 KIAS with FLAPS LDG

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.

END OF CHECKLIST

Normal Operating

Procedures DA 42 AFM

Page 4A - 36 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

4A.6.12 GO-AROUND

1. POWER lever ........................ MAX

2. Airspeed ............................ min. 82 KIAS

3. FLAPS.............................. position APP

when a positive rate of climb is established:

4. Landing Gear ........................ UP, check unsafe light off

5. FLAPS.............................. retract, position UP

END OF CHECKLIST

4A.6.13 AFTER LANDING

1. POWER lever ....................... IDLE

2. Brakes ............................. as required

3. Transponder ........................ OFF / STBY

4. Pitot heating ......................... OFF

5. Avionics ............................ as required

6. Lights .............................. as required

7. FLAPS ............................. UP

END OF CHECKLIST

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 37

4A.6.14 SHUT-DOWN

1. Parking brake ........................ set

2. POWER lever ........................ IDLE for 2 minutes

3. Engine / System Page ................. check

4. ELT................................ check not transmitting on

121.5 MHz

5. AVIONIC MASTER.................... OFF

6. Electrical consumers................... OFF

7. ENGINE MASTER .................... OFF

8. Anti-collision lights (ACL) ............... OFF

9. ELECT. MASTER ..................... OFF

CAUTION

Before shut-down the engine must run for at least 2 minutes

with the power lever at IDLE to avoid heat damage of the

turbo charger.

CAUTION

Do not shut down an engine with the fuel selector valve. The

high pressure fuel pump can otherwise be damaged.

END OF CHECKLIST

Normal Operating

Procedures DA 42 AFM

Page 4A - 38 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

4A.6.15 PARKING

1. Parking brake ........................ release, use chocks

2. Airplane............................. moor, if unsupervised for

extended period

3. PITOT probe ......................... cover

END OF CHECKLIST

4A.6.16 EXIT AIRPLANE

Exit the airplane to the aft on designated areas on the inner wing section LH or RH.

4A.6.17 POST FLIGHT INSPECTION

1. Record any problem found in flight and during the post-flight check in the log

book.

2. Park the airplane.

3. If necessary, moor the airplane.

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.

DA 42 AFM Normal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4A - 39

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

(refer to Section 2.16.1) must be observed.

If JET A-1 is used, make sure that no Diesel fuel is remaining

in the tanks, neither in the left nor in the right tank (see fuel

grade, Section 7.9.5). Otherwise the temperature limitations

for Diesel fuel operation must be observed.

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.

If the auxiliary tanks are not in use, make sure that they are

empty (refer to Section 6.4).

CAUTION

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), the use of the auxiliary tanks is not permitted.

Normal Operating

Procedures DA 42 AFM

Page 4A - 40 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 1

CHAPTER 4B

ABNORMAL OPERATING PROCEDURES

Page

4B.1 PRECAUTIONARY LANDING ........................... 4B-3

4B.2 CANOPY IN COOLING GAP POSITION ................... 4B-5

4B.3 ENGINE INSTRUMENT INDICATIONS OUTSIDE

OF GREEN RANGE ON THE G1000 ...................... 4B-5

4B.3.1 RPM ......................................... 4B-5

4B.3.2 COOLANT TEMPERATURE ...................... 4B-6

4B.3.3 OIL TEMPERATURE ............................ 4B-8

4B.3.4 OIL PRESSURE............................... 4B-10

4B.3.5 GEARBOX TEMPERATURE ..................... 4B-12

4B.3.6 FUEL TEMPERATURE ......................... 4B-13

4B.3.7 VOLTAGE ................................... 4B-14

4B.4 CAUTION-ALERTS ON THE G1000 ..................... 4B-15

4B.4.1 CAUTIONS / GENERAL......................... 4B-15

4B.4.2 L/R ECU A FAIL ............................... 4B-16

4B.4.3 L/R ECU B FAIL ............................... 4B-17

4B.4.4 L/R FUEL LOW................................ 4B-18

4B.4.5 LOW VOLTAGE CAUTION (LOW VOLTS) .......... 4B-19

4B.4.6 L/R ALTN FAIL ................................ 4B-20

4B.4.7 L/R COOL LVL ................................ 4B-21

4B.4.8 PITOT FAIL / HT OFF .......................... 4B-22

4B.4.9 STALL HT FAIL / OFF .......................... 4B-23

4B.4.10 L/R FUEL TRANSFER FAIL

(IF AUX. TANKS ARE INSTALLED) .............. 4B-24

4B.4.11 L/R AUXILIARY FUEL TANK EMPTY

(IF AUX. TANKS INSTALLED)................... 4B-24

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 2 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

4B.4.12 STICK LIMIT ................................. 4B-25

4B.4.13 RAIM UNAVAIL ............................... 4B-26

4B.4.14 AHRS ALIGNING - KEEP WINGS LEVEL .......... 4B-26

4B.5 FAILURES IN FLAP OPERATING SYSTEM ............... 4B-27

4B.6 FAILURES IN HYDRAULIC SYSTEM ..................... 4B-28

4B.6.1 CONTINUOUS HYDRAULIC PUMP OPERATION..... 4B-28

4B.6.2 HYDRAULIC PUMP FAILURE .................... 4B-28

4B.7 STARTING ENGINE WITH EXTERNAL POWER............ 4B-29

4B.7.1 BEFORE STARTING ENGINE .................... 4B-29

4B.7.2 STARTING ENGINE ............................ 4B-31

4B.8 LANDING WITH HIGH LANDING MASS .................. 4B-33'

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 3

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. The pilot is required to decide

whether or not a controlled landing in a field represents a

lower risk than the attempt to reach the target airfield under

all circumstances.

NOTE

If no level landing area is available, a landing on an upward

slope should be sought.

1. Select appropriate landing area.

2. Consider wind.

3. Approach:

If possible, the landing area should be overflown at a suitable height in order to

recognize obstacles. The degree of offset at each part of the circuit will allow the

wind speed and direction to be assessed.

4. ATC ............................... advise

Perform procedures according to Normal Procedures 4A.6.11

APPROACH & LANDING.

5. Touchdown .......................... with the lowest possible airspeed

CONTINUED

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 4 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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 ........... both OFF

- ELECT. MASTER ............ OFF

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 5

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.

4B.3 ENGINE INSTRUMENT INDICATIONS OUTSIDE OF GREEN

RANGE ON THE G1000

4B.3.1 RPM

High RPM

1. Reduce power of affected engine.

2. Keep RPM within the green range using the power lever.

If the above mentioned measures do not solve the problem, refer to 3.9.3 DEFECTIVE

PROPELLER RPM REGULATING SYSTEM

3. Land at the nearest suitable airfield.

END OF CHECKLIST

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 6 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

- Increase airspeed by 10 KIAS or more as required.

- If the coolant temperature does not reach the green range within 60 seconds,

reduce power on affected engine as far as possible and increase airspeed.

during cruise:

- Reduce power on affected engine.

- Increase airspeed.

- Check coolant temperature in green range.

CAUTION

If high coolant temperature is indicated and the L/R COOL

LVL caution message is not displayed, it can be assumed that

there is no technical defect in the cooling system and that the

above mentioned procedure can decrease the temperature(s).

This might not be the case if the coolant temperature does

not return to the green range. In this case perform a

precautionary landing on the nearest suitable airfield. Prepare

for an engine failure in accordance with 3.5.6 - ENGINE

FAILURES IN FLIGHT.

CONTINUED

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 7

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.

(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. In this case

an increase in power and a decrease in airspeed can help.

L/R COOL LVL caution message displayed:

- Reduce power on affected engine.

- Expect loss of coolant.

WARNING

A further decrease in coolant temperature must be expected.

Prepare for an engine failure in accordance with 3.5.6 -

ENGINE FAILURES IN FLIGHT.

END OF CHECKLIST

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 8 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

Prepare for an engine failure in accordance with 3.5.6 -

ENGINE FAILURES IN FLIGHT.

if the oil pressure is within the green range:

- Reduce power on affected engine.

- Increase airspeed.

CAUTION

If high oil temperature is announced and the oil pressure

indication is within the green range, it can be assumed that

there is no technical defect in the engine oil system and that

the above mentioned procedure can decrease the

temperature(s). This might not be the case if the oil

temperature does not return to the green range. In this case

perform a precautionary landing on the nearest suitable

airfield. Prepare for an engine failure in accordance with 3.5.6

- ENGINE FAILURES IN FLIGHT.

CONTINUED

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 9

(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.

END OF CHECKLIST

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 10 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

WARNING

Land at the nearest suitable airfield. Prepare for an engine

failure in accordance with 3.5.6 - ENGINE FAILURES IN

FLIGHT.

CAUTION

When starting a cold engine, the oil pressure can be as high

as 6.5 bar for a maximum of 20 seconds.

CONTINUED

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 11

(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.

END OF CHECKLIST

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 12 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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). This

might not be the case if the gearbox temperature does not

return to the green range. In this case perform a precaution-

ary landing on the nearest suitable airfield. Prepare for an

engine failure in accordance with 3.5.6 - ENGINE FAILURES

IN FLIGHT.

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4B - 13

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). If the fuel temperature does not

return to the green range, perform a precautionary landing

on the nearest suitable airfield.

NOTE

Increased fuel temperature can occur when the fuel quantity

in the main tank is low. If the auxiliary tank is installed the fuel

temperature can be decreased by transferring fuel from the

auxiliary to the main tank.

(b) Low fuel temperature

- Increase power on affected engine.

- Reduce airspeed.

CAUTION

At low ambient temperature conditions and / or at high

airspeeds with low power settings, it can be assumed that

the above mentioned procedure will increase the tempera-

ture(s). If the fuel temperature does not return to the green

range perform a precautionary landing on the nearest suitable

airfield. Prepare for an engine failure in accordance with

3.5.6 - ENGINE FAILURES IN FLIGHT.

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 14 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

4B.3.7 VOLTAGE

(a) Low voltage indication on the ground

1. Circuit breakers....................... check

2. POWER lever ........................ increase RPM

if LOW VOLTAGE CAUTION (LOW VOLTS / 4B.4.5) is still indicated on the G1000:

terminate flight preparation.

(b) Low voltage during flight

1. Circuit breakers....................... check

2. Electrical equipment ................... OFF if not needed

if LOW VOLTAGE CAUTION (LOW VOLTS / 4B.4.5) is still indicated on the G1000:

follow procedure in 4B.4.6 - L/R ALTN FAIL

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 15

4B.4 CAUTION-ALERTS ON THE G1000

The G1000 provides the following CAUTION-alerts on the PFD in the ALERT area.

4B.4.1 CAUTIONS / GENERAL

CHARACTERISTICS * amber color coded text

* Single warning chime tone of 1.5 seconds duration

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 16 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

4B.4.2 L/R ECU A FAIL

L/R ECU A FAIL * Left / Right engine ECU A has failed

* is being tested during FADEC test procedure before

take-off check.

(a) 'ECU A' caution on the ground

- Terminate flight preparation.

(b) 'ECU A' caution during flight

NOTE

In case of a failure in the electronic ECU (Engine Control Unit)

'A' the system automatically switches to ECU 'B'.

1. Press the ECU TEST button for more than 2 seconds to reset the caution

message.

If the ECU A caution message re-appears, or cannot be reset:

2. Land on the nearest suitable airfield.

3. The engine must be serviced after landing.

If the ECU A caution message can be reset:

2. Continue flight.

3. The engine must be serviced after landing.

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 17

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.

(b) 'ECU B' caution during flight

1. Press the ECU TEST button for more than 2 seconds to reset the caution

message.

If the ECU B caution message re-appears, or cannot be reset:

2. Land on the nearest suitable airfield.

3. The engine must be serviced after landing.

If the ECU B caution message can be reset:

2. Continue flight.

3. The engine must be serviced after landing.

END OF CHECKLIST

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 18 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

4B.4.4 L/R FUEL LOW

L/R FUEL LOW

Left / Right engine main tank fuel quantity is low.

1. Fuel quantity ......................... check

CAUTION

As soon as the amount of usable fuel in the main tank is low,

a caution message is displayed. The indication is calibrated

for straight and level flight. The caution message may be

triggered during turns which are flown with slip, or while

taxiing in curves.

if fuel quantities of LH & RH engines show remarkable different fuel quantities in flight:

- Expect loss of fuel on side with lower indication.

- Use crossfeed function to ensure fuel supply.

2. FUEL SELECTOR..................... crossfeed (engine with LOW

FUEL indication)

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 19

4B.4.5 LOW VOLTAGE CAUTION (LOW VOLTS)

L/R VOLTS LOW Left / Right engine bus voltage is too low (less than

25 volts)

Possible reasons are:

- A fault in the power supply.

- RPM too low.

Continue with 4B.3.7 VOLTAGE.

CAUTION

If both Low Voltage indications are ON, expect failure of both

Alternators and follow 4B.4.6 L/R ALTN FAIL.

END OF CHECKLIST

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 20 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. Bus voltage .......................... monitor

3. Electrical consumers................... reduce as practicable

END OF CHECKLIST

(b) Both alternators failed

WARNING

If both alternators fail at the same time, reduce all electrical

equipment to a minimum. Expect battery power to last 30

minutes and land the airplane as soon as possible. Expect

engine stoppage after this period of time.

1. Avionics Master....................... OFF

2. LH/RH Alternator...................... OFF

3. XPDR .............................. STBY

4. LANDING GEAR...................... down, when down and locked pull

Emergency Release

5. Stall/Pitot heat ........................ OFF

6. All lights............................. OFF

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 21

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.

1. Annunciations / Engine instruments ....... monitor

See 4B.3.2 COOLANT TEMPERATURE.

NOTE

The indication is calibrated for straight and level flight. The

caution message may be triggered during turns which are

flown with slip, or while taxiing in curves.

END OF CHECKLIST

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 22 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

4B.4.8 PITOT FAIL / HT OFF

PITOT FAIL Pitot heating system has failed.

PITOT HT OFF Pitot heating system is OFF.

1. PITOT HEAT......................... check ON / as required

NOTE

The Pitot heating caution message is displayed when the Pitot

heating is switched OFF, or when there is a failure of the Pitot

heating system. Prolonged operation of the Pitot heating on

the ground can also cause the Pitot heating caution message

to be displayed. In this case it indicates the activation of the

thermal switch, which prevents overheating of the Pitot

heating system on the ground. This is a normal function of

the system. After a cooling period, the heating system will be

switched on again automatically.

if in icing conditions:

2. Expect loss of static instruments.

3. Open Alternate Static.

4. Leave icing zone / refer to 3.9.4 - UNINTENTIONAL FLIGHT INTO ICING

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 23

4B.4.9 STALL HT FAIL / OFF

STALL HT FAIL Stall warning heat has failed.

STALL HT OFF Stall warning heat is OFF.

1. PITOT HEAT ........................ check ON / as required

NOTE

The STALL HT OFF caution message is displayed when the

Pitot heating is switched OFF, or STALL HT FAIL when there

is a failure of the stall warning heating system. Prolonged

operation of the stall warning heating on the ground can also

cause the stall warning heating failed caution message to be

displayed. In this case it indicates the activation of the thermal

switch, which prevents overheating of the stall warning

heating system on the ground. This is a normal function of

the system. After a cooling period, the heating system will be

switched on again automatically.

if in icing conditions:

2. Expect loss of acoustic stall warning.

3. Leave icing zone / See 3.9.4 UNINTENTIONAL FLIGHT INTO ICING

END OF CHECKLIST

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 24 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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).

2. Check fuel imbalance in the main tanks; use crossfeed function to keep the LH

and RH main tank imbalance within the permissible limit of 1 US gal (3.8 liters).

3. Switch the remaining fuel pump ON.

4. Use crossfeed function to keep the LH and RH main tank imbalance within the

permissible limit of 1 US gal (3.8 liters).

END OF CHECKLIST

4B.4.11 L/R AUXILIARY FUEL TANK EMPTY (IF AUX. TANKS INSTALLED)

L/R AUX FUEL E Left / Right auxiliary fuel tank empty (displayed only

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.

1. L/R auxiliary fuel pump ................. OFF

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4B - 25

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

be identified as follows:

(a) Both power levers are in a position for a power setting of more than approximately

20 % LOAD, and the FLAP selector switch is in LDG position:

CAUTION

The variable elevator backstop is inoperative. In case of

stalling with "power-on" the handling qualities and stall-

characteristics are degraded significantly.

Do not stall the airplane in any configuration.

(b) At least one power lever is in a position for a power setting of less than approximately

20 % LOAD, or the FLAP selector switch is not in LDG position:

CAUTION

The variable elevator backstop is active all the time, reducing

the maximum elevator "pull"-deflection. This results in

reduced elevator capacity. In this case it is important to

maintain the required minimum vREF during the approach for

landing, especially at loading conditions with forward locations

of the center of gravity.

up to 1700 kg (3748 lb) .......... v

REF = 76 KIAS

above 1700 kg (3748 lb) ......... v

REF = 78 KIAS

(see Section 4B.8)

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 26 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

4B.4.13 RAIM UNAVAIL

INTEG

RAIM not available RAIM (Receiver Autonomous Integrity Monitor) is 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

initial approach phase of flight, continue to navigate using the GPS equipment or revert

to an alternate means of navigation other than the G1000 GPS receiver appropriate to

the route and phase of flight. When continuing to use GPS navigation, position must be

verified every 15 minutes using the G1000 VOR/ILS receiver or another IFR-approved

navigation system.

(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. Missed approach course guidance may still be available with

1 nautical mile CDI sensitivity and integrity by executing the missed approach.

4B.4.14 AHRS ALIGNING - KEEP WINGS LEVEL

AHRS ALIGN:

Keep Wings

Level

The AHRS (Attitude and Heading Reference System) is

aligning.

Keep wings level using standby attitude indicator.

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4B - 27

4B.5 FAILURES IN FLAP OPERATING SYSTEM

Failure in position indication or function

1. FLAPS position ....................... check visually

2. Airspeed ............................ keep in white sector

(max. 111 KIAS)

3. FLAPS switch ........................ re-check all positions

Modified approach procedure depending on the available flap setting

(a) Only UP available:

Airspeed

up to 1700 kg (3748 lb) ............... min. 85 KIAS

above 1700 kg (3748 lb) .............. min. 86 KIAS (see Section 4B.8)

Land at a flat approach angle, use power lever to control airplane speed and

rate of descent.

(b) Only APP available:

Airspeed ............................ min. 82 KIAS

Land at a flat approach angle, use power lever to control airplane speed and

rate of descent.

Perform normal landing.

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 28 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

NOTE

The landing gear might extend as the hydraulic system

pressure decreases. Consider for higher aerodynamic drag,

resulting in degraded flight performance, increased fuel

consumption and decreased range.

Unscheduled maintenance action is required after landing.

4B.6.2 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.

NOTE

The landing gear might extend as the hydraulic system

pressure decreases. Consider for higher aerodynamic drag,

resulting in degraded flight performance, increased fuel

consumption and decreased range.

Unscheduled maintenance action is required after landing.

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 4B - 29

4B.7 STARTING ENGINE WITH EXTERNAL POWER

4B.7.1 BEFORE STARTING ENGINE

1. Pre-flight inspection ................... complete

2. Passengers ......................... instructed

NOTE

Ensure all the passengers have been fully briefed on the use

of the seat belts, doors and emergency exits and the ban on

smoking.

3. Rear door ........................... closed and locked

4. Front canopy ......................... Position 1 or 2 (“cooling gap”)

5. Rudder pedals ....................... adjusted and locked

6. Safety harnesses ..................... all on and fastened

7. POWER lever ........................ check IDLE

8. Parking brake ........................ set

9. AVIONIC MASTER ................... check OFF

10. GEAR selector ....................... check DOWN

11.ECU SWAP ......................... check AUTOMATIC

12.ALTERNATORS ...................... check ON

13.ELECT. MASTER ..................... check OFF

14.ENGINE MASTER .................... check OFF

15.PROPELLER ........................ check clear

16.External power ....................... connect

CONTINUED

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 30 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. There is a malfunction in the landing gear

system.

NOTE

When switching the External Power Unit ON, all electrical

equipment, connected to the LH and RH main busses is

powered.

17. G1000 .............................. wait until power-up completed.

Press ENT on MFD to

acknowledge.

NOTE

The engine instruments are only available on the MFD after

item 17 has been completed.

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4B - 31

4B.7.2 STARTING ENGINE

1. Strobe lights (ACL) .................... ON

2. ELECT. MASTER ..................... ON

3. ENGINE MASTER .................... ON (L / R)

NOTE

It is recommended to start the LH engine (pilot side). If

required by operational reasons, the RH engine can also be

started.

4. Annunciations ........................ check „L/R ENGINE GLOW“ ON

5. Annunciations / Engine / System Page ..... check OK / normal range

WARNING

Before starting the engine the pilot must ensure that the

propeller area is free, and no persons can be endangered.

After the L/R ENGINE GLOW indication is extinguished:

6. START KEY ......................... START L/R as required / release

when engine has started

CONTINUED

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 32 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

If the „L/R STARTER“ annunciation does not extinguish after

the engine has started and the START KEY has been

released, set the ENGINE MASTER to OFF and investigate

the problem.

7. Annunciations / Engine / System Page ..... check OK / normal range

8. Annunciations / Starter ................. check OFF

9. Annunciations / Oil pressure ............. check OK

WARNING

If the oil pressure has not moved from the red range within

3 seconds after starting, set the ENGINE MASTER switch

to OFF and investigate problem. When starting the cold

engine, the oil pressure can be as high as 6.5 bar for a

maximum of 20 seconds.

10.Circuit breakers....................... check all in / as required

11.Idle RPM ............................ check, 900 ±20 RPM

12.External Power ....................... disconnect

13. Opposite engine ...................... Start with normal procedure

14.Warm up ............................ IDLE for 2 minutes /

thereafter 1400 RPM

END OF CHECKLIST

DA 42 AFM Abnormal Operating

Procedures

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 4B - 33

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. It

constitutes an abnormal operating procedure. A "Hard

Landing Check" is only required after a hard landing,

regardless of the actual landing mass. Refer to Section

4A.6.11 for landings with a mass up to 1700 kg (3748 lb).

Perform landing approach according to Section 4A.6.11, but maintain an increased

airspeed during final landing approach.

Approach speed .......................... min. 82 KIAS with FLAPS APP

min. 86 KIAS with FLAPS UP

Final approach speed ...................... min. 78 KIAS with FLAPS LDG

Minimum speed on go-around ............... 82 KIAS

Abnormal Operating

Procedures DA 42 AFM

Page 4B - 34 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Intentionally left blank.

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 1

CHAPTER 5

PERFORMANCE

Page

5.1 INTRODUCTION .......................................5-2

5.2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS ......5-2

5.3 PERFORMANCE TABLES AND DIAGRAMS..................5-3

5.3.1 AIRSPEED CALIBRATION ...........................5-3

5.3.2 FUEL FLOW DIAGRAM .............................5-6

5.3.3 INTERNATIONAL STANDARD ATMOSPHERE...........5-7

5.3.4 STALLING SPEEDS ................................5-8

5.3.5 WIND COMPONENTS ..............................5-9

5.3.6 TAKE-OFF DISTANCE .............................5-10

5.3.7 CLIMB PERFORMANCE - TAKE-OFF CLIMB ...........5-16

5.3.8 CLIMB PERFORMANCE - CRUISE CLIMB .............5-19

5.3.9 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE . . . 5-22

5.3.10 CRUISING (TRUE AIRSPEED TAS) .................5-25

5.3.11 LANDING DISTANCE.............................5-27

5.3.12 GRADIENT OF CLIMB ON GO-AROUND .............5-33

5.3.13 APPROVED NOISE DATA .........................5-34

Performance DA 42 AFM

Page 5 - 2 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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

in the tables and the diagrams were obtained in the framework of the flight trials using

an airplane and power-plant in good condition, and corrected to the conditions of the

International Standard Atmosphere (ISA = 15 EC / 59 °F and 1013.25 hPa / 29.92 inHg

at sea level).

The performance diagrams do not take into account variations in pilot experience or a

poorly maintained airplane. The performances given can be attained if the procedures

quoted in this manual are applied, and the airplane has been well maintained.

5.2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS

In order to illustrate the influence of a number of different variables, the performance data

is reproduced in the form of tables or diagrams. These contain sufficiently detailed

information so that conservative values can be selected and used for the determination

of adequate performance data for the planned flight.

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 3

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.

Performance DA 42 AFM

Page 5 - 4 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 5

Performance DA 42 AFM

Page 5 - 6 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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

values shown are numbers which are calculated from the last

fuel quantity update done by the pilot and actual fuel flow

data. Therefore, the endurance and range data is for

information only, and must not be used for flight planning.

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 7

5.3.3 INTERNATIONAL STANDARD ATMOSPHERE

Performance DA 42 AFM

Page 5 - 8 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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)

Bank Angle

Gear Flaps 0° 30° 45° 60°

UP UP 56

DOWN APP 53

DOWN LDG 49

1700 kg (3748 lb) Bank Angle

Gear Flaps 0° 30° 45° 60°

UP UP 62

67 76

DOWN APP 59

DOWN LDG 55

60 68 84

if MÄM 42-088 is carried out:

1785 kg (3935 lb)

Bank Angle

Gear

Flaps

0°

30°

45°

60°

DOWN

APP

DOWN

LDG

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 9

5.3.5 WIND COMPONENTS

Example: Flight direction : 360°

Wind : 32°/30 kts

Result: Crosswind component : 16 kts

Max. demonstrated crosswind component : 20 kts

Performance DA 42 AFM

Page 5 - 10 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

5.3.6 TAKE-OFF DISTANCE

Conditions:

- Power lever ......................... both MAX @ 2300 RPM

- Flaps .............................. UP

- Nose wheel lift-off

up to 1700 kg (3748 lb) .............. @ v

R = 70 KIAS

above 1700 kg (3748 lb) ............. @ v

R = 72 KIAS

- Airspeed for initial climb

up to 1700 kg (3748 lb) ............. 77 KIAS

above 1700 kg (3748 lb) ............. 79 KIAS

- Runway ............................ level, hard paved surface

(concrete, asphalt, etc.)

values for ISA and MSL, at 1700 kg (3748 lb)

Take-off distance over a 50 ft (15 m) obstacle 530 m (1739 ft)

Take-off ground roll 348 m (1142 ft)

if MÄM 42-088 is carried out:

values for ISA and MSL, at 1785 kg (3935 lb)

Take-off distance over a 50 ft (15 m) obstacle

691 m (2267 ft)

Take-off ground roll

427 m (1401 ft)

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.

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 11

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. In any

case the pilot must allow for the condition of the runway to

ensure a safe take-off.

NOTE

For take-off from dry, short-cut grass covered runways, the

following corrections must be taken into account, compared

to paved runways (typical values, see CAUTION above):

- grass up to 5 cm (2 in) long: 10 % increase in take-off roll.

- grass 5 to 10 cm (2 to 4 in) long: 15 % increase in take-

off roll.

- grass longer than 10 cm (4 in): at least 25 % increase

in take-off roll.

- on grass longer than 25 cm (10 in), a take-off should

not be attempted.

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 %. The effect on the take-off roll can be greater.

Performance DA 42 AFM

Page 5 - 12 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Conditions: Flaps: UP, Power: both MAX @ 2300 RPM, vR: 70 KIAS, Airspeed: 77 KIAS, Runway: hard, paved

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 13

Conditions: Flaps: UP, Power: both MAX @ 2300 RPM, vR: 72 KIAS, Airspeed: 79 KIAS, Runway: hard, paved

Performance DA 42 AFM

Page 5 - 14 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Conditions: Flaps: UP, Power: both MAX @ 2300 RPM, vR: 70 KIAS, Airspeed: 77 KIAS, Runway: hard, paved

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 15

Conditions: Flaps: UP, Power: both MAX @ 2300 RPM, vR: 72 KIAS, Airspeed: 79 KIAS, Runway: hard, paved

Performance DA 42 AFM

Page 5 - 16 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Gradient ROC fpm

TAS KTAS

[%] []

[]

=⋅

095

Gradient ROC m s

TAS KTAS

[%] [/]

[]

=⋅

190

5.3.7 CLIMB PERFORMANCE - TAKE-OFF CLIMB

Conditions:

- Power lever ......................... both MAX @ 2300 RPM

- Flaps .............................. UP

- Landing Gear ........................ retracted

- Airspeed

up to 1700 kg (3748 lb) .............. 77 KIAS

above 1700 kg (3748 lb) ............. 79 KIAS

NOTE

The charts on the following pages show the rate of climb. The

gradient of climb cannot easily be determined with a chart,

but it can be calculated using the following formulae:

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 17

Conditions: Flaps: UP, Power: both MAX @ 2300 RPM, Landing gear: retracted, Airspeed: 77 KIAS

Performance DA 42 AFM

Page 5 - 18 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Conditions: Flaps: UP, Power: both MAX @ 2300 RPM, Landing gear: retracted, Airspeed: 79 KIAS

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 19

Gradient ROC m s

TAS KTAS

[%] [/]

[]

=⋅

190

Gradient ROC fpm

TAS KTAS

[%] []

[]

=⋅

095

5.3.8 CLIMB PERFORMANCE - CRUISE CLIMB

Conditions:

- Power lever ......................... both MAX @ 2300 RPM

- Flaps .............................. UP

- Airspeed

up to 1700 kg (3748 lb) .............. 85 KIAS

above 1700 kg (3748 lb) ............. 86 KIAS

NOTE

The graphs on the following pages show the rate of climb.

The gradient of climb cannot easily be determined with a

graph, but it can be calculated using the following formulae:

Performance DA 42 AFM

Page 5 - 20 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Conditions: Flaps: UP, Power: both MAX @ 2300 RPM, Airspeed: 85 KIAS

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 21

Conditions: Flaps: UP, Power: both MAX @ 2300 RPM, Airspeed: 86 KIAS

Performance DA 42 AFM

Page 5 - 22 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Gradient ROC fpm

TAS KTAS

[%] []

[]

=⋅

095

Gradient ROC m s

TAS KTAS

[%] [/]

[]

=⋅

190

5.3.9 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE

Conditions:

- Remaining Engine (RH) ................ MAX @ 2300 RPM

- Dead Engine ........................ feathered and secured

- Flaps .............................. UP

- Airspeed ............................ 82 KIAS

- Landing Gear ........................ retracted

- Zero Sideslip ........................ established

NOTE

With respect to handling and performance, the left hand

engine (pilots view) is considered the "critical" engine.

NOTE

The graphs on the following pages show the rate of climb.

The gradient of climb cannot easily be determined with a

graph, but it can be calculated using the following formulae:

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 23

Conditions: Flaps: UP, Power: remaining engine MAX @ 2300 RPM / Dead engine: feathered+secured, Airspeed: 82 KIAS

Performance DA 42 AFM

Page 5 - 24 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Conditions: Flaps: UP, Power: remaining engine MAX @ 2300 RPM / Dead engine: feathered+secured, Airspeed: 82 KIAS

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 25

5.3.10 CRUISING (TRUE AIRSPEED TAS)

Conditions:

- Engines ............................ all operating

- Power lever ......................... as required to adjust selected

displayed LOAD [%]

- Flaps .............................. UP

- Landing Gear ....................... retracted

Performance DA 42 AFM

Page 5 - 26 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Conditions: Engines: all operating, Power: as required to adjust selected LOAD [%], Flaps: UP, Landing Gear: retracted

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 27

5.3.11 LANDING DISTANCE

Conditions: - Power lever ............... both IDLE

- Flaps .................... LDG

- Runway .................. level, asphalt surface, dry

values for ISA and MSL, at 1700 kg (3748 lb), approach speed 76 KIAS

Landing distance over a 50 ft (15 m) obstacle 572 m (1877 ft)

Ground roll 323 m (1060 ft)

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. It

constitutes an abnormal operating procedure.

values for ISA and MSL, at 1785 kg (3935 lb), approach speed 78 KIAS

Landing distance over a 50 ft (15 m) obstacle

710 m (2329 ft)

Ground roll

397 m (1302 ft)

WARNING

For a safe landing the available runway length must be at

least equal to the landing distance over a 50 ft (15 m)

obstacle.

Performance DA 42 AFM

Page 5 - 28 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

In any case the pilot must allow for the condition of the runway

to ensure a safe landing.

NOTE

For landings on dry, short-cut grass covered runways, the

following corrections must be taken into account, compared

to paved runways (typical values, see CAUTION above):

- grass up to 5 cm (2 in) long: 5 % increase in landing roll.

- grass 5 to 10 cm (2 to 4 in) long: 15 % increase in landing

roll.

- grass longer than 10 cm (4 in): at least 25 % increase in

landing roll.

NOTE

For wet grass, an additional 10 % increase in landing roll must

be expected.

NOTE

A downhill slope of 2 % (2 m per 100 m or 2 ft per 100 ft)

results in an increase in the landing distance of approximately

10 %. The effect on the landing roll can be greater.

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 29

Conditions: Flaps: LDG, Power: both IDLE, Runway: level and hard, dry surface, Approach Speed: 76 KIAS

Performance DA 42 AFM

Page 5 - 30 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Conditions: Flaps: LDG, Power : both IDLE, Runway: level and hard, dry surface, Approach Speed: 78 KIAS

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 31

Conditions: Flaps: LDG, Power: both IDLE, Runway: level and hard, dry surface, Approach Speed: 76 KIAS

Performance DA 42 AFM

Page 5 - 32 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Conditions: Flaps: LDG, Power: both IDLE, Runway: level and hard, dry surface, Approach Speed: 78 KIAS

DA 42 AFM Performance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 5 - 33

5.3.12 GRADIENT OF CLIMB ON GO-AROUND

Conditions:

- Power lever ......................... both MAX @ 2300 RPM

- Flaps .............................. LDG

- Landing gear ........................ extended

- Airspeed:

up to 1700 kg (3748 lb) .............. 76 KIAS

above 1700 kg (3748 lb) ............. 78 KIAS

value for ISA and MSL, at 1700 kg (3748 lb)

constant gradient of climb

5.25 % (equals 3.0° climb angle) or 400 ft/min

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. It

constitutes an abnormal operating procedure.

value for ISA and MSL, at 1785 kg (3935 lb)

constant gradient of climb

4.30 % (equals 2.5° climb angle) or 340 ft/min

Performance DA 42 AFM

Page 5 - 34 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. flight mass 1785 kg (3935 lb), if MÄM 42-088 is carried out

ICAO Annex 16 Chapter X, App. 6 ............ 76.8 dB(A)

JAR-36 Subpart C ......................... 76.8 dB(A)

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 6 - 1

CHAPTER 6

MASS AND BALANCE

Page

6.1 INTRODUCTION .......................................6-2

6.2 DATUM PLANE ........................................6-3

6.3 MASS AND BALANCE REPORT ...........................6-4

6.4 FLIGHT MASS AND CENTER OF GRAVITY ..................6-6

6.4.1 MOMENT ARMS...................................6-8

6.4.2 LOADING DIAGRAM ...............................6-9

6.4.3 CALCULATION OF LOADING CONDITION.............6-10

6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE .........6-12

6.4.5 PERMISSIBLE MOMENT RANGE ....................6-14

6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY ...........6-15

Mass and Balance DA 42 AFM

Page 6 - 2 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

The pilot is responsible for adhering to the permissible values for loading and center of

gravity (CG). In this, he should note the movement of the CG due to fuel consumption.

The permissible CG range during flight is given in Chapter 2.

The procedure for determining the flight mass CG position is described in this chapter.

Additionally a comprehensive list of the equipment approved for this airplane exists

(Equipment List) with a list of the equipment installed when the airplane was weighed

(Equipment Inventory).

Before the airplane is delivered, the empty mass and the corresponding CG position are

determined and entered in Section 6.3 MASS AND BALANCE REPORT.

NOTE

Following equipment changes the new empty mass and the

corresponding CG position must be determined by calculation

or by weighing.

Following repairs or repainting the new empty mass and the

corresponding CG position must be determined by weighing.

Empty mass, empty mass CG position, and the empty mass

moment must be certified in the Mass and Balance Report

by authorized personnel.

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 6 - 3

2196 mm

floor of

nose baggage

compartment

horizontal

(86.46 in)

Datum

Plane

Root Rib

on Stub Wing

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. The airplane’s longitudinal axis

is parallel with the floor of the nose baggage compartment. When the floor of the nose

baggage compartment is aligned horizontally, the Datum Plane is vertical. The Datum

Plane is located 2.196 meters (86.46 in) forward of the most forward point of the root rib

on the stub wing.

Mass and Balance DA 42 AFM

Page 6 - 4 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

For the calculation of flight mass and corresponding CG position (or moment), the current

empty mass and the corresponding CG position (or moment) in accordance with the Mass

and Balance Report must always be used.

Condition of the airplane for establishing the empty mass:

- Equipment as per Equipment Inventory (see Section 6.5)

- Including the following operating fluids:

brake fluid

hydraulic fluid (for the retractable gear)

engine oil (2 x 6.0 liters = 2 x 6.3 qts)

coolant (2 x 6.0 liters = 2 x 6.3 qts)

gearbox oil (2 x 0.9 liters = 2 x 0.95 qts)

unusable fuel in main fuel tanks (2 x 1.0 US gal = 2 x 3.8 liters)

unusable fuel in auxiliary fuel tanks (if installed, 2 x 0.5 US gal = 2 x 1.9 liters)

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 6 - 5

MASS AND BALANCE REPORT

Page No.:

Current empty

mass

Mo-

ment

''''''''

'''''

Mo-

ment

Arm

''''''''

'''''

Mass

''''''''

'''''

Registration:

Changes in mass

Subtraction (-)

Mo-

ment

''''''''

'''''

'''

Mo-

ment

Arm

''''''''

'''''

Mass

''''''''

'''''

Serial No.:

Addition (+)

Mo-

ment

''''''''

'''''

'''

Mo-

ment

Arm

''''''''

'''''

Mass

''''''''

'''''

DA 42

Description

of part or

Modification

Upon delivery

'''''''

'''''

Entry No.:

OUT

''''''''

'''''

''''''''

'''''

Date

''''''''

'''''

Mass and Balance DA 42 AFM

Page 6 - 6 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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

6.4.2 LOADING DIAGRAM

6.4.3 CALCULATION OF LOADING CONDITION

6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE

6.4.5 PERMISSIBLE MOMENT RANGE

The diagrams should be used as follows:

1. Take the empty mass and the empty mass moment of your airplane from the Mass

and Balance Report, and enter the figures in the appropriate boxes under the column

marked ‘Your DA 42' in Table 6.4.3 - 'CALCULATION OF LOADING CONDITION'.

2. Read the fuel quantity indicators to determine the fuel quantity in the main fuel tanks.

3. Determine the fuel quantity in the auxiliary fuel tanks (if installed).

To verify an empty auxiliary fuel tank, set the ELECT. MASTER switch and the FUEL

TRANSFER switch to ON and check the PFD for the L/R AUX FUEL E caution

message.

To verify a full auxiliary fuel tank open the auxiliary fuel tank filler and check fuel level.

If the auxiliary fuel tank quantity is in between empty and full, the exact quantity cannot

be determined. If possible transfer all fuel to the main fuel tank by setting the ELECT.

MASTER switch and the FUEL TRANSFER switch to ON until the L/R AUX FUEL E

caution message appears on the PFD. During this procedure ground power must be

used or at least one engine must be running. The fuel transfer will take a maximum

of 10 minutes.

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 6 - 7

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.

4. Multiply the individual masses by the moment arms quoted to obtain the moment for

every item of loading and enter these moments in the appropriate boxes in Table

6.4.3 - 'CALCULATION OF LOADING CONDITION'.

5. Add up the masses and moments in the respective columns. The CG position is

calculated by dividing the total moment by the total mass (using row 8 for the condition

with empty fuel tanks, and row 11 for the pre take-off condition). The resulting CG

position must be inside the limits.

As an illustration the total mass and the CG position are entered on Diagram 6.4.4 -

'PERMISSIBLE CENTER OF GRAVITY RANGE'. This checks graphically that the

current configuration of the airplane is within the permissible range.

6. Graphical method:

Diagram 6.4.2 - 'LOADING DIAGRAM' is used to determine the moments. The masses

and moments for the individual items of loading are added. Then Diagram 6.4.5 -

'PERMISSIBLE MOMENT RANGE' is used to check whether the total moment

associated with the total mass is in the permissible range.

The result found with the graphical method is however inaccurate. In doubtful cases

the result must be verified using the exact method given above.

Mass and Balance DA 42 AFM

Page 6 - 8 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

6.4.1 MOMENT ARMS

The most important lever arms aft of the Datum Plane:

Item Lever Arm

[m] [in]

Occupants on front seats 2.30 90.6

Occupants on rear seats 3.25 128.0

Fuel in main tanks 2.63 103.5

in auxiliary tanks 3.20 126.0

De-Icing Fluid (if equipment installed,

OÄM 42-053 or OÄM 42-054)

1.00

39.4

Baggage in

Compartments

nose 0.60 23.6

cockpit 3.89 153.1

extension 4.54 178.7

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 6 - 9

6.4.2 LOADING DIAGRAM

Mass and Balance DA 42 AFM

Page 6 - 10 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. Depending on the fuel flow and de-icing

fluid flow, the overall movement of the CG can be a forward

or a rearward movement. In order to cover all possible cases,

the following table must be completed twice: with (as shown

in the example) and without considering the on-board de-icing

fluid. All four CG positions (fuel tank full/empty, de-icing fluid

tank full/empty) must fall into the permitted area.

1. Complete the form on the next page.

2. Divide the total moments from rows 8 and 11 by the related total mass to obtain the

CG positions.

In our example: empty tanks: 3625.1 kgm / 1527.5 kg = 2.373 m

314,656 in.lb / 3368 lb = 93.43 in

full tanks: 4312.1 kgm / 1770.5 kg = 2.436 m

374,295 in.lb / 3904 lb = 95.87 in

3. Locate the values in the diagram in Section 6.4.4 'PERMISSIBLE CENTER OF

GRAVITY RANGE'. If the CG positions and related masses fall into the permitted area,

the loading condition is allowable.

Our example shows allowable loading conditions (for 1785 kg take-off mass, i.e., MÄM

42-088 carried out).

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 6 - 11

CALCULATION OF

LOADING CONDITION

DA 42 (Example) Your DA 42

Mass

[kg]

[lb]

Moment

[kgm]

[in.lb]

Mass

[kg]

[lb]

Moment

[kgm]

[in.lb]

1. Empty mass (from Mass and

Balance Report) 1250

2756

2937.5

254,965

2. Front seats

Lever arm: 2.30 m (90.6 in) 160

353 368.0

31,982

3. Rear seats

Lever arm: 3.25 m (128.0 in) 70

154 227.5

19,712

4. Nose baggage compt.

Lever arm: 0.60 m (23.6 in) 5

11 3.0

260

5. Cockpit baggage compt.

Lever arm: 3.89 m (153.1 in) 10

22 38.9

3,368

6. Baggage extension

Lever arm: 4.54 m (178.7 in) 5

11 22.7

1,966

7. De-icing fluid (if installed; see

NOTE on previous page)

(1.1 kg/liter) (9.2 lb/US gal)

Lever arm: 1.00 m (39.4 in)

27.5

2,403

8. Total mass & total moment

with empty fuel tanks

(Total of 1.-7.)

1527.5

3368

3625.1

314,656

9. Usable fuel, main tanks

(0.84 kg/liter) (7.01 lb/US gal)

Lever arm: 2.63 m (103.5 in)

159

351 418.2

36,329

10. Usable fuel, auxiliary tanks (if

installed; OÄM 42-056)

(0.84 kg/liter) (7.01 lb/US gal)

Lever arm: 3.20 m (126.0 in)

185 268.8

23,310

11. Total mass & total moment

with fuel & de-icing fluid

(Total of 8. through 10.)

1770.5

3904

4312.1

374,295

Mass and Balance DA 42 AFM

Page 6 - 12 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Flight Mass [kg]

1250

1300

1350

1400

1450

1500

1550

1600

1650

1700

1750

1800

Center of Gravity Position [m]

2.35 2.40 2.45 2.50

Flight

Mass

[lb]

Center of Gravity Position [in]

9695949392 97 98

shaded area only for 1785 kg (3935 lb)

max. take-off mass (MÄM 42-088 carried out)

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

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 6 - 13

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. take-off mass (see Section 2.7)

linear variation in between

Most rearward flight CG:

2.42 m (95.28 in) aft of Datum Plane at 1250 kg (2756 lb)

2.49 m (98.03 in) aft of Datum Plane at 1600 kg (3527 lb)

2.49 m (98.03 in) aft of Datum Plane at max. take-off mass (see Section 2.7)

linear variation in between

Mass and Balance DA 42 AFM

Page 6 - 14 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

1250

1300

1350

1400

1450

1500

1550

1600

1650

1700

1750

1800

2800

3000

3200

3400

3600

3800

4000

4300

4400

4500

4200

4100

4000

3900

3800

3700

3600

3500

3400

3300

3200

3100

3000

2900

Flight Mass [kg]

Flight Mass [lb]

Flight Mass Moment [kg m]

Flight Mass Moment [in lb]

260,000

280,000

300,000

320,000

340,000

360,000

380,000

shaded area only for 1785 kg (3935 lb)

max. take-off mass (MÄM 42-088 carried out)

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.

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 6 - 15

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. The airplane manufacturer must be

contacted before removing or installing equipment, with the

exception of replacing a unit by an identical unit.

The items of equipment installed in your particular airplane are indicated in the appropriate

column. The set of items marked as 'installed' constitutes the Equipment Inventory.

Airplane Serial No.: Registration: Date:

Description Type Part No. Manufacturer S/N inst‘d

AVIONICS COOLING

Avionics Cooling Fan SAFE 328 305 467-00 Sandia Aerospace

PFD Cooling Fan SAFE 128 305 468-00 Sandia Aerospace

MFD Cooling Fan SAFE 128 305 468-00 Sandia Aerospace

AUTOPILOT SYSTEM KAP 140

Flight Computer KC 140 065-00176-7904 Bendix/King

Pitch servo KS 270 C 065-00178-2500 Bendix/King

Pitch servo mount KM 275 065-00030-0000 Bendix/King

Roll servo KS 271 C 065-00179-0500

Bendix/King

Roll servo mount KM 275 065-00030-0000 Bendix/King

Trim servo KS 272 C 065-00180-3500 Bendix/King

Trim servo mount KM 277 065-00041-0000 Bendix/King

Configuration module KCM 100 071-00073-5000 Bendix/King

Sonalert SC 628 Mallory

Control stick DA4-2213-12-90 Diamond Aircraft

CWS switch 031-00514-0000 Bendix/King

AP-Disc switch 031-00428-0000 Bendix/King

Trim switch assy 200-09187-0000 Bendix/King

ELECTRICAL POWER

Main Battery G-243 (CB24-11M) Gill (Concorde)

Excitation Battery (2 pcs.) LC-R121R3PU Panasonic

Mass and Balance DA 42 AFM

Airplane Serial No.: Registration: Date:

Description Type Part No. Manufacturer S/N inst‘d

Page 6 - 16 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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 Thielert

RH Alternator Regulator 02-7150-55112R2 Thielert

EQUIPMENT

Safety belt, pilot 5-01-1C5710-LH 918 Schroth

Safety belt, copilot 5-01-1C0710-RH 918 Schroth

Safety belt, LH pax 5-01-1B5710 918 Schroth

Safety belt, RH pax 5-01-1B0710 918 Schroth

ELT unit C406-1 453-5002- Artex

ELT unit

ME406

453-6603-

Artex

ELT remote switch 345-6196-04 Artex

ELT ant+enna 110-338 Artex

Buzzer 130-4004 Artex

SAFETY EQUIPMENT

Fire extinguisher HAL 1 AIR Total

First aid kit

FLIGHT CONTROLS

Flaps actuator assy 43055 Krutz

Lift detector C-99701-1 Safe Flight Instr.

Stall warning buzzer SC Series SC 628 ND Mallory

Variable elevator stop D60-2733-12-00 Diamond Aircraft

HYDRAULIC

Motor pump unit X11-0001-00- Hydraulik Mayer

Hydraulic fluid tank X11-0002-00- Hydraulik Mayer

Hydraulic control unit X11-0003-00- Hydraulik Mayer

High pressure filter X11-0004-00- Hydraulik Mayer

Hydraulic pressure accumulator X11-0005-00- Hydraulik Mayer

MLG hydraulic cylinder X11-0006-00- Hydraulik Mayer

NLG hydraulic cylinder X11-0006-00- Hydraulik Mayer

Brake master cylinder 2x 10-54A Cleveland

Parking valve 60-5B Cleveland

Brake assembly 30-239A Cleveland

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 6 - 17

Airplane Serial No.: Registration: Date:

Description Type Part No. Manufacturer S/N 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 D60-3217-11-00 Diamond Aircraft

Main landing gear RH D60-3217-12-00 Diamond Aircraft

Nose landing gear D60-3223-10-00 Diamond Aircraft

LDG Gear Warning SC Series SC 628 NDP Mallory

LIGHTS

Map/Reading light assy crew W1461.0.010 Rivoret

Cabin Light W1461.0.010 Rivoret

Strobe/Pos. light assy LH A600-PR-D-28 01-0790006-05 Whelen

Strobe/Pos. light assy RH A600-PG-D-28 01-0790006-07 Whelen

Strobe light power supply LH/RH A490ATS-CF-14/28 01-0770062-05 Whelen

Taxi light Xenon D1S Aero Vision Int.

Taxi light power supply XV1-28 Aero Vision Int.

Landing light Xenon D1S Aero Vision Int.

Landing light power supply XV1-28 Aero Vision Int.

Glareshield lamp assy DA4-3311-10-02 Diamond Aircraft

Glareshield light inverter APVL328-4-1-L-5QF Quantaflex

Placards inverter APVL328-4-1-L-15QF Quantaflex

Mass and Balance DA 42 AFM

Page 6 - 18 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

Airplane Serial No.: Registration: Date:

Description Type Part No. Manufacturer S/N inst‘d

COMMUNICATION / NAVIGATION

COMM #1 antenna DMC63-1/A DM

COMM #2 antenna DMC63-2 DM

Audio Panel / Marker / ICS GMA 1347 011-00809-00 Rev. 3 Garmin

Headset, pilot Echelon 100 Telex

Headset, copilot Echelon 100 Telex

Headset, LH pax Echelon 100 Telex

Headset, RH pax Echelon 100 Telex

Speaker FRS8 / 4 Ohms Visaton

Handmic 100 TRA 62800-001 Telex

Pitot/Static probe, heated

DAI-9034-57-00

Diamond Aircraft

Pitot/Static probe, heated

AN5814-2

PST-305

Aeroinstruments

'''

Alternate static valve DA4-3111-51-00 Diamond Aircraft

Backup Altimeter 5934PD-3 Untied Instruments

Backup airspeed indicator 8030 8030-B.864 United Instruments

Backup artificial horizon 4300 4300-206 Mid Continent Instr.

Magnetic compass PG2C-28V SIRS Navigation

Turn & Bank indicator 1394T100-(12RZ) Mid Continent Instr.

Turn & Bank indicator 1394T100-(12RA) Mid Continent Instr.

OAT probe GTP 59

011-00978-00

Garmin

Digital Air Data System GDC 74A 011-00882-00 Rev. 6 Garmin

Integrated Avionics #1 GIA 63 011-00781-01 Garmin

Integrated Avionics #2 GIA 63 011-00781-01 Garmin

Transponder GTX 33 011-00779-00 Rev. C Garmin

Attitude / Heading Reference System GRS 77 011-00868-00 Rev. 4 Garmin

Attitude / Heading Reference System

GRS 77

011-00868-10

Garmin

Magnetometer GMU 44 011-00870-00 Rev. 4 Garmin

VOR/LOC/GS antenna CI 157P Comant

dual VOR / dual GS duplexer CI 1125 Comant

Transponder antenna KA 60 071-01591-0001 Bendix/King

Marker antenna CI 102 Comant

GPS #1 antenna GA 56 010-10040-01 Garmin

GPS #2 antenna GA 56 010-10040-01 Garmin

DME KN 63 066-1070-01 Bendix/King

DME antenna KA 60 071-01591-0001 Bendix/King

ADF receiver

RA 3502-(01)

0505.757-912

Becker

ADF / RMI converter

AC 3504-(01)

0856.010-912

Becker

ADF antenna

AN 3500

0832.601-912

Becker

Stormscope

WX-500

805-11500-001

L-3(Goodrich)

Stormscope antenna

NY-163

805-10930-001

L-3 (Goodrich)

DA 42 AFM Mass and Balance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 6 - 19

Airplane Serial No.: Registration: Date:

Description Type Part No. Manufacturer S/N 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 ECU 02-7610-55003R(*) Thielert

ECU Firmware 02-7610-55101R( )* Thielert

ECU Mapping 50-7610-55107R( )* Thielert

RH ENGINE CONTROL UNIT ECU 02-7610-55003R(*) Thielert

ECU Firmware 02-7610-55101R( )* Thielert

ECU Mapping 50-7610-55107R( )* Thielert

ENGINE STARTING

Glow Power Control Unit LH/RH 02-7150-55005R1 Thielert

Starter LH/RH 02-8010-13210R1 Thielert

ENGINE FIRE WARNING

LH overheat detector X 2003-2 Control Products, Inc.

RH overheat detector X 2003-2 Control Products, Inc.

ENGINE INDICATING

Engine / Airframe Unit GEA 71 011-00831-00 Rev. 6 Garmin

PROPELLER

Propeller LH MTV-6-A-C-F/CF187-129 mt-propeller

Propeller RH MTV-6-A-C-F/CF187-129 mt-propeller

Unfeathering accumulator X11-0007-00-00 Hydraulik Mayer

AIRPLANE FLIGHT MANUAL Doc. No. 7.01.05-E Diamond Aircraft

FUEL TANK SYSTEM

Fuel probe assy., LH inboard D60-2817-13-00 Diamond Aircraft

Fuel probe assy., RH inboard D60-2817-13-00 Diamond Aircraft

Fuel probe assy., LH outboard D60-2817-14-00 Diamond Aircraft

Fuel probe assy., RH outboard D60-2817-14-00 Diamond Aircraft

Alternate means for fuel qty. D60-2817-90-00 Diamond Aircraft

AUX FUEL SYSTEM

''''''

LH auxiliary fuel pump

5100-09

Dukes

'''

LH auxiliary fuel pump

5100-09

Dukes

'''

Mass and Balance DA 42 AFM

Airplane Serial No.: Registration: Date:

Description Type Part No. Manufacturer S/N inst‘d

Page 6 - 20 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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 12102-23 CAV Aerospace

porous panel, center wing, RH 12102-24 CAV Aerospace

porous panel, horizontal tail, LH 12102-25 CAV Aerospace

porous panel, horizontal tail, RH 12102-26 CAV Aerospace

porous panel, vertical tail 12102-27 CAV Aerospace

inlet strainer 12121-02 CAV Aerospace

spray bar 12124-10 CAV Aerospace

metering pump 1 9513A-386 CAV Aerospace

metering pump 2 9513A-386 CAV Aerospace

de-icing fluid tank D60-3013-24-50 Diamond Aircraft

filter F908 CAV Aerospace

solenoid valve FV158H-28V CAV Aerospace

high pressure switch P041ED850 CAV Aerospace

proportioning unit, nacelle, LH PU300DW142 CAV Aerospace

proportioning unit, nacelle, RH PU300DW142 CAV Aerospace

tail bracket assembly 12132-03 CAV Aerospace

windshield pump 1 WP209A CAV Aerospace

windshield pump 2 WP209A CAV Aerospace

de-ice control box DAI-9030-00-01 Diamond Aircraft

* Refer to Service Information SI 42.003 for approved ECU firmware and mapping.

Place:____________ Date: ____________ Signature: ____________

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 1

CHAPTER 7

DESCRIPTION OF THE AIRPLANE

AND ITS SYSTEMS

Page

7.1 INTRODUCTION .......................................7-3

7.2 AIRFRAME ............................................7-3

7.3 FLIGHT CONTROLS ....................................7-4

7.4 INSTRUMENT PANEL ..................................7-10

7.5 LANDING GEAR.......................................7-13

7.6 SEATS AND SAFETY HARNESSES .......................7-19

7.7 BAGGAGE COMPARTMENT.............................7-19

7.8 CANOPY, REAR DOOR, AND CABIN INTERIOR .............7-20

7.9 POWER PLANT .......................................7-22

7.9.1 ENGINES, GENERAL..............................7-22

7.9.2 PROPELLER ....................................7-23

7.9.3 OPERATING CONTROLS ..........................7-26

7.9.4 ENGINE INSTRUMENTS ...........................7-30

7.9.5 FUEL SYSTEM ...................................7-32

7.9.6 COOLING SYSTEM ...............................7-43

7.9.7 OIL SYSTEMS ...................................7-44

7.9.8 TURBO-CHARGER SYSTEM ........................7-45

7.9.9 FIRE DETECTION SYSTEM ........................7-46

7.10 ELECTRICAL SYSTEM .................................7-47

7.10.1 GENERAL......................................7-48

7.10.2 ENGINE CONTROL UNIT / ECU ....................7-53

7.10.3 WARNING, CAUTION AND ADVISORY MESSAGES ....7-55

Airplane Description DA 42 AFM

Page 7 - 2 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

7.11 PITOT-STATIC SYSTEM ............................... 7-61

7.12 STALL WARNING SYSTEM ............................. 7-61

7.13 GARMIN G1000 INTEGRATED AVIONICS SYSTEM ......... 7-62

7.13.1 GENERAL ..................................... 7-62

7.13.2 PRIMARY FLIGHT DISPLAY (PFD) ................. 7-63

7.13.3 MULTI-FUNCTION DISPLAY (MFD) ................. 7-65

7.13.4 AUDIO PANEL ................................. 7-66

7.13.5 ATTITUDE AND HEADING

REFERENCE SYSTEM (AHRS) .................... 7-66

7.13.6 AIR DATA COMPUTER (ADC) ..................... 7-66

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 3

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. The two main spars and both nacelles are part of the

center wing. The two main spars are CFRP items. The engine compartment in each nacelle

is separated from the other structure with a firewall. The fire protection on the firewall is

of a special fire-resistant matting, which is covered on the engine side by stainless steel

cladding.

Wings

The wings have a front and rear spar; each wing has a top shell and a bottom shell; The

whole wing is ‘fail-safe‘ design. The wings, as well as the ailerons and flaps, are made

of GFRP/CFRP, and are principally of sandwich construction. An aluminum fuel tank is

installed in each of the wings.

Empennage

The airplane has a ‘T’ tail of GFRP/CFRP semi monocoque construction. Both the

stabilizers have twin spars. Rudder and elevator are of sandwich construction.

Airplane Description DA 42 AFM

Page 7 - 4 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

Ailerons

Construction: GFRP/CFRP composite sandwich.

Hinges: There are 4 hinges, which are hinge pins mounted in an aluminum

bracket. They are secured in position by a roll pin. The absence of this

roll pin can lead to the loss of the hinge pin and a consequent loss of flight

safety.

Operation: A rod-end bearing is screwed into a steel push rod and locked by means

of a jam nut which has locking varnish applied to it. Damage to this

varnish can indicate a twisting and thus a change to the adjustment. The

connection between the rod-end bearing and the control horn is a bolt,

the nut of which is likewise sealed with locking varnish.

The aluminum control horn is attached to the aileron with 3 screws.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 5

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.

Construction: GFRP/CFRP composite sandwich.

Hinges: There are 6 hinges at the outer part and 4 hinges at the inner part of the

flap. These hinges are hinge pins mounted in an aluminum bracket. They

are secured in position by a roll pin. The absence of this roll pin can lead

to the loss of the hinge pin and a consequent loss of flight safety.

Operation: Each part is connected with a flap control horn to the push rods of the

flap control system. A rod-end bearing is screwed into a steel push rod

and locked by means of a jam nut which has locking varnish applied to

it. Damage to this varnish can indicate a twisting and thus a change to

the adjustment. The connection between the rod-end bearing and the

control horn is a bolt, the nut of which is likewise sealed with locking

varnish.

Each flap control horn is attached to the flap part with 3 screws.

The flaps are driven by an electric motor and have 3 settings:

- Cruise (UP), totally retracted

- Approach (APP), and

- Landing (LDG).

Airplane Description DA 42 AFM

Page 7 - 6 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

The UP and LDG positions are additionally protected by a limit switch to guard against

over-running the end positions.

The electrical flap drive has an automatic circuit breaker which can also be operated

manually.

Flap position indicator:

The current flap position is indicated by means of three lights beside the flap selector

switch.

When the upper light (green) is illuminated, the flaps are in the Cruise position (UP);

when the center light (white) is illuminated, the flaps are in Approach position (APP);

when the lower light (white) is illuminated, the flaps are in Landing position (LDG).

When two lights are illuminated simultaneously, the flaps are between the two indicated

positions. This is the case only when the flaps are in transition.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 7

Elevator

Construction: GFRP sandwich.

Hinges: 5 hinges.

Operation: Steel push-rods;

Two of the bellcrank bearings are accessible for visual inspection next

to the lower hinge of the rudder. The elevator horn and its bearing, as

well as the connection to the push-rod, can be visually inspected at the

upper end of the rudder.

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° full deflection.

The linear actuator acts as a movable stop and is controlled by three switches, one for

each power lever and one for the flap selector. When the power of one engine is reduced

below approximately 20 %, or the flap selector is not in the LDG position, full elevator

deflection is regained.

An amber annunciation (CAUTION) on the G1000 display is provided to inform the pilot

in case a malfunction occurs. The annunciation illuminates when the variable stop should

be in place and is actually not activated (power on condition) or should be retracted and

actually limits the elevator travel (power off condition).

Airplane Description DA 42 AFM

Page 7 - 8 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

Operation: Steel cables, the eyes of which are connected to the bolts on the bracket.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 9

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.

Turn wheel to the front = nose down

Turn wheel to the rear = nose up

Rudder Trim

The trim control is a black wheel in the center console below the instrument panel. A mark

on the wheel shows the center position and the direction of movement.

Turn wheel to the right = right turn

Turn wheel to the left = left turn

Pedal Adjustment

NOTE

The pedals may only be adjusted on the ground!

The pedals are unlocked by pulling the black handle which is located behind the rear

attachment.

Forward adjustment:

Whilst keeping the handle pulled, push the pedals forward with your feet. Release the

handle and allow the pedals to lock into place.

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.

Airplane Description DA 42 AFM

Page 7 - 10 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

7.4 INSTRUMENT PANEL

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 11

Major instruments and controls

1 Electric Master switch 16 Ventilation nozzles

2 Avionic Master switch 17 Circuit breakers*

3 Engine Master switches 18 Backup airspeed indicator

4 Start switch 19 Backup artificial horizon

5 Pitot-/Stall Warning-Heat switch 20 Backup altimeter

6 Alternator switches 21 Emergency compass

7 ECU Test buttons 22 ELT control unit

8 ECU Swap switches 23 Primary Flight Display (PFD)

9 Rotary buttons for instrument

lighting and flood light 24 Audio amplifier / Intercom / Marker

beacon receiver

10 Light switches 25 Multi Function Display (MFD)

11 Emergency switch 26 Oxygen system control unit

12 Flap selector switch 27 Autopilot control unit

13 Landing gear switch 28 Alt air lever

14 Alternate static valve 29 Landing gear emergency

extension lever

15 Microphone socket

*) 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).

Airplane Description DA 42 AFM

Page 7 - 12 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

The spherical nozzles are opened and closed by twisting.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 13

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. Electrically actuated hydraulic valves, which are operated with the gear selector

switch, provide the required hydraulic pressure for the movement of the landing gear.

The gear selector switch is located on the instrument panel. The switch must be pulled

out before it is moved to “UP” or “DOWN” position. Gear extension normally takes 6-10

seconds.

When the landing gear is retracted, the main wheels retract inboard into the center wing

and the nose wheel retracts forward into the nose section. Hydraulic pressure on the

actuators keeps the landing gear in the retracted position. A pressurized gas container

acts as an accumulator which keeps the system pressure constant by replacing the volume

lost due to the normal actuator leakages. This prevents a permanent starting of the

hydraulic pump in flight.

Springs assist the hydraulic system in gear extension and locking the gear in the down

position. After the gears are down and the downlock hooks engage, springs maintain force

on each hook to keep it locked until it is released by hydraulic pressure.

When the gears are fully extended or retracted and the gear selector switch is in the

corresponding position, electrical limit switches stop the operation. The three green lights

directly above the landing gear operating switch illuminate to indicate that each gear is

in the correct position and locked. If the gear is in neither the full up nor the full down

position, a red warning light on the instrument panel illuminates.

Should one throttle be placed in a position below 25% while the landing gear is retracted,

a warning horn sounds to alert the pilot that the gear is retracted. The same warning

appears if the flaps move into position LDG (fully extended) while the gear is retracted.

Airplane Description DA 42 AFM

Page 7 - 14 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

To prevent inadvertent gear retraction on ground, an electric squat switch prevents the

hydraulic valve from switching if the master switch is on and the gear extension switch

is placed in the “UP” position.

After takeoff, the gear should be retracted before an airspeed of 156 KIAS is exceeded.

The landing gear may be extended at any speed up to194 KIAS.

The landing gear is designed to be manually operated in the event of failure. Since the

gear is held in the retracted position by hydraulic pressure, gravity will allow the gear to

extend if the system fails for any reason. To extend and lock the gears in the event of

failure, it is only necessary to relieve the hydraulic pressure by means of the emergency

gear extension lever, which is located under the instrument panel to the left of the center

console. Pulling this lever releases the hydraulic pressure and allows the gear to fall free.

Before pulling the emergency gear extension lever, place the gear selector switch in the

“DOWN” position.

NOTE

If the emergency gear extension has been pulled due to an

emergency, the system has to be checked before pushing

the lever in again.

The nose gear is steerable by the use of full rudder pedal travel. A gear damping element,

incorporated in the nose gear steering system, prevents shimmy tendencies. When the

gear is retracted, the nose wheel centers as it enters the wheel well, and the steering

linkage disengages to reduce pedal loads in flight.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 15

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.

The figure below shows the system status when the landing gear is extended. All hydraulic

cylinders are under high pressure.

Airplane Description DA 42 AFM

Page 7 - 16 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

While the landing gear is retracted both valves are energized and excessive hydraulic

fluid on one side is drained into the tank. This configuration of the system is shown in the

following figure.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 17

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.

Airplane Description DA 42 AFM

Page 7 - 18 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

brake pedals,

pilot brake pedals,

co-pilot

parking brake

valve

brake cylinder, LH brake cylinder, RH

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. To operate the parking brake, pull the lever

downwards until it catches. Brake pressure is built up by multiple operation of the toe brake

pedals, and is maintained until the parking brake is released. To release, the lever is

pushed upwards.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 19

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.

The seats have removable furnishings and are equipped with energy-absorbing foam

elements.

The seats are fitted with three-part safety harnesses. The harnesses are fastened by

inserting the end of the belts in the belt lock, and are opened by pressing the red release

on the belt lock.

The backs of the rear seats can be laid forward after pulling upwards on the locking bolt

knob.

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.

Airplane Description DA 42 AFM

Page 7 - 20 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

“Cooling Gap” position: A second setting allows the bolts to lock in, leaving a gap under

the forward canopy.

The canopy can be blocked by a locking device on the left side near the canopy opening

lever by turning the key clockwise. The closed and blocked canopy can be opened from

inside by pulling the lever inside the opening handle.

WARNING

The airplane may be operated with the front canopy in the

“cooling gap” position on the ground only. Before take-off the

front canopy must be completely closed and locked.

Do not block the front canopy with the locking key before flight

in order to assure emergency evacuation from outside.

A window on the left and right hand side of the canopy can be opened for additional

ventilation or as an emergency window.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 21

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. The rear door is protected against unintentional opening

by an additional lever.

The door can be blocked by a locking device on the left side near the door opening lever

by turning the key clockwise. The closed and blocked door can be opened from inside

by pulling the lever inside the opening handle.

WARNING

Do not block the door with the locking key before flight in

order to assure emergency access from outside.

Heating and ventilation

Heating and ventilation are operated using two levers located on the small center console

under the instrument panel.

Right lever: up = HEATING ON (Seats, Floor)

down = HEATING OFF

Center lever : up = DEFROST ON (Airflow to canopy)

down = DEFROST OFF

The heat of the RH engine is used for the front seats and floor, the heat of the LH engine

is used to defrost the canopy.

The Air inlet for the Ventilation System is placed on the underside of the RH wing, inboard

of the engine nacelle. The air is distributed within the cabin via 6 nozzles (2 on the

instrument panel LH/RH side, 2 on the overhead panel and 2 on the LH/RH side of the

passenger compartment). The jet direction of each cone can be changed easily and

the jet intensity can be regulated by rotation of the nozzle.

Airplane Description DA 42 AFM

Page 7 - 22 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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

- Digital Engine Control with Integrated Propeller Governor (separate oil system)

- Turbo-charger with Intercooler

Displacement: 1689 cm3 (103 in³)

Max. power: 99 kW (135 DIN-HP) at 2300 RPM at sea level and ISA

Max. continuous power: 99 kW (135 DIN-HP) at 2300 RPM at sea level and ISA

The indications for monitoring important engine-parameters during operation are integrated

within the Garmin G1000 display. Each engine can only be operated with the ENGINE

MASTER switch ON. Each engine has an own ECU (Engine Control Unit) which receives

its electrical power from the generator when at least one engine is running. When both

engines are at standstill, the ECU receives its electrical power from the battery.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 23

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.

Propeller control

The propeller pitch control system is integrated into the engine. The pitch is controlled

automatically by the ECU. To change the blade pitch angle gearbox oil is pumped into

the propeller hub. The oil pressure is regulated by an electrically operated valve, the

governor valve, which is controlled by the ECU. Increasing the oil pressure leads to a

decrease of pitch and a higher RPM. Decreasing the pressure leads to higher pitch and

a lower RPM.

Depending on the power setting the propeller pitch is adjusted such that the required RPM

will be obtained as shown in the following diagram.

Airplane Description DA 42 AFM

Page 7 - 24 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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).

During engine operation the accumulator makes sure that enough oil pressure is available

even if the oil feed by the gearbox oil pump is decreasing due to negative acceleration.

The hydraulic pressure keeps the propeller pitch angle below the start lock position, or

moves the propeller blades beyond the start lock position.

Feathering:

To feather the propeller the engine must be shut down with the appropriate engine master

switch. This will open the electric governor valve. All oil will flow back from the propeller

hub, allowing the blades to move into the feathered pitch position. At the same time the

electric valve at the pressure accumulator closes, and the oil pressure is restored in the

accumulator.

Feathering is only possible at propeller speeds above 1300 RPM.

CAUTION

If the engine is shut down below an RPM of 1300 the propeller

pitch remains below the start lock position. In this case the

speed must be increased to increase the propeller RPM.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 25

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.

Ground operation:

CAUTION

Operation on the ground at high RPM should be avoided as

far as possible, as the blades could suffer stone damage. For

this reason a suitable site for engine runs should be selected,

where there are no loose stones or similar items.

WARNING

Never move the propeller by hand.

Airplane Description DA 42 AFM

Page 7 - 26 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

Each power lever is used to set the desired engine power LOAD (%)

Lever forward (MAX) = Full power

Lever to rear (IDLE) = Idle

A separate ECU for each engine controls manifold pressure, injected fuel quantity and

propeller speed according to the desired engine power preselected with the power lever.

If the power lever is in a low power position - as for a landing approach - while the landing

gear is retracted, an aural warning alerts the pilot to the retracted landing gear.

A propeller governor, which is controlled by the ECU, is flanged onto the front of each

engine. The propeller governor oil circuit is supplied with oil by the gearbox oil pump (also

see Section 7.9.2 - PROPELLER). A loss of oil pressure leads to a feathering of the

propeller blades, thus allowing continuation of the flight according to 3.7.3 - DEFECTIVE

PROPELLER RPM REGULATING SYSTEM.

CAUTION

Following governor failure the RPM should be adjusted using

the power lever. Every effort should be made not to exceed

2300 RPM.

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.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 27

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.

ELECT. MASTER

The electric master switch has two positions:

OFF

disconnecting battery power

connecting battery power to the power distribution system

ENGINE MASTER

Each engine can only be cranked with its ENGINE MASTER switched to ON. When

activated, the ENGINE MASTER provides the power supply for the preheat system, the

unfeathering accumulator valve and the engine itself. To shut down the engine the

appropriate ENGINE MASTER is switched to OFF.

START

Turning START key switch to the left starts the LH engine. Turning it to the right side starts

the RH engine.

Airplane Description DA 42 AFM

Page 7 - 28 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. If the automatic switch-over fails, switch-over can be done

manually by switching to ECU B. This procedure should only be applied in an emergency.

ECU TEST

There are two ECU TEST buttons, one for each engine. Depending on the position of

the power lever and the engine speed, the ECU TEST button has two different functions.

Power lever at IDLE and RPM below approximately 900:

By pushing and holding the button until the end of the procedure, the self-test of each

engine control unit is started. The procedure is possible on the ground as well as during

flight, but only if the power lever is in the IDLE position. Otherwise the test will not start.

During the procedure the ECU performs a switch from ECU A to ECU B with the

propeller cycling. The propeller RPM is monitored automatically by the ECU. When

switching from one ECU to the other, a slight shake of the engine may occur. Finally

the ECU switches back from ECU B to ECU A. After that both caution lights must

extinguish and the engine must run without a change.

Power lever above IDLE, or RPM above approximately 900:

If an ECU A or ECU B caution message is displayed, the ECU TEST button can be

pressed for more than 2 seconds to reset the message. The reset is possible only once,

and only in case of system faults of minor criticality.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 29

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. To open the alternate air source the lever is pulled to

the rear. Normally, the alternate air source is closed with the lever in the forward position.

Placard on the lever, forward position:

ALTERNATE AIR

Placard on the lever, visible when lever is in the rearward position:

ALTERNATE AIR

Airplane Description DA 42 AFM

Page 7 - 30 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

Default page Display when pushing Display when pushing

Engine the SYSTEM button the FUEL button

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 31

NOTE

The figure on previous page is a general demonstration of

a typical 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. The values shown are

numbers which are calculated from the last fuel quantity

update done by the pilot and actual fuel flow data. Therefore,

the endurance and range data is for information only, and

must not be used for flight planning.

Designation Indication Unit

LOAD Available power %

RPM Propeller RPM 1/min

VOLT Volts V

GENERATOR Ampères A

CT Coolant temperature °C

GT Gearbox temperature °C

OT Engine oil temperature °C

OP Oil pressure bar

FUEL Fuel quantity US gal

FUEL FLOW Fuel flow US gal/hr

FUEL TEMP. °C

Airplane Description DA 42 AFM

Page 7 - 32 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

TAE 125

ENGINE

firewall TAE Diesel filter

sediment bowl

drain

fuel selector valves

fuel level switch

fuel supply

return line

FUSELAGE

fuel system is symmetric

with respect to fuselage

cross-

feed

lines

fuel cooler aux. fuel pump

relief valve

check valve

aux. fuel

tank (op-

tional)

fuel temp.

sensor

low fuel

sensor

finger filter drain

drain

RH WING

inboard chamber

fuel

probe fuel

probe

fuel level

switch

middle

chamber

outboard

chamber

fuel filler

aux. fuel filler

pressure

relief valve

fuel

tank

vent

check valve

with capillary

optional

(OÄM 40-056)

vent line

check valve

with capillary

7.9.5 FUEL SYSTEM

General

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 33

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.

On each engine fuel is injected with high pressure directly into the cylinders. The injection

nozzles (one per cylinder) are supplied with fuel by the common rail. Pressure inside the

rail is generated by a high pressure pump which receives fuel from a low pressure pump.

Depending on the power setting the rail pressure is controlled by the ECU through an

electric valve. Both pumps are powered mechanically by the engine. Fuel that is not

injected is fed back into the appropriate wing tank.

Both sides of the fuel system are interconnected by crossfeed lines.

Airplane Description DA 42 AFM

Page 7 - 34 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. When X-Feed is selected, the engine will draw fuel from

the tank on the opposite side in order to extend range and keep fuel weight balanced

during single engine operation. With the fuel selector valve both the feeding and the return

line are switched.

The desired position is reached by pulling the lever back. To reach the OFF position a

safety guard must be twisted. This is to ensure that this selection is not made

unintentionally.

NOTE

When one engine is inoperative the fuel selector valve for this

engine must be in the OFF position.

CAUTION

Do not operate with both fuel selector valves in X-Feed

Position. Do not take off with a fuel selector valve in X-Feed

Position.

CAUTION

Do not shut down an engine with the fuel selector valve. The

high pressure fuel pump can otherwise be damaged.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 35

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):

figure 1:

normal

operation

figure 2:

cross-feed

operation

figure 3

shut-off

position

Airplane Description DA 42 AFM

Page 7 - 36 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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).

figure 4... fuel selector valve RH normal operation

position, fuel selector valve LH cross feed

position

figure 5... fuel selector RH valve shut-off position, fuel

selector valve LH cross feed position

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 37

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

wing is usable.

There are two tank vents. One includes a check valve with a capillary and one includes

a relief pressure valve, which operates at 150 mbar (2 psi) and allows fuel and air to flow

to the outside with higher internal pressure. The relief pressure valve protects the tank

against high pressure, if the tank was overfilled in case of an auxiliary fuel transfer failure.

The check valve with capillary allows air to enter the tank but prevents flow of fuel to the

outside. The capillary equalizes the air pressure during climb. The hose terminals are

located on the underside of the wing, approximately 2 meters (7 ft) from the wing tip.

In each tank a coarse filter (finger filter) is fitted before the outlet. To allow draining of

the tank, there is an outlet valve at its lowest point.

At the lowest point in each side of the fuel system a fuel filter with a drain valve is installed.

This drain valve can be used to remove water and sediment which has collected in the

fuel system. The drain valves are fitted in each nacelle behind the firewall, approximately

15 cm (0.56 ft) backward of the wing leading edge.

Fuel quantity indication

Two capacity probes measure the fuel quantity in each main tank. The indication is

provided by the G1000 flight display. Information about fuel consumption can be found

in Chapter 5 - PERFORMANCE.

Airplane Description DA 42 AFM

Page 7 - 38 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. The additional fuel capacity is 13.7 US gallons (52 liters) per side. The total

fuel capacity (main fuel tanks and auxiliary fuel tanks) is 39.7 US gallons (150.4 liters)

per side.

The fuel supply connection attaches to a finger filter mounted at the rear of the auxiliary

fuel tank. Each auxiliary fuel tank has a fuel transfer pump which pumps fuel into the

related main fuel tank.

The vent line for the auxiliary fuel tank has a check valve with capillary. It allows air to

enter the tank but prevents flow of fuel to the outside. The capillary equalizes the air

pressure during climb. A fuel drain valve is located at the rear of each auxiliary tank.

Operation

Two FUEL TRANSFER switches in the cockpit are used to activate the fuel transfer pumps.

The switches are located behind the elevator trim wheel on the center console. Both

swithes are intended to be used simultaneously to prevent the airplane from additional

lateral imbalance. The fuel transfer pump pumps the fuel from the auxiliary fuel tank into

the related main fuel tank. Fuel level switches shut this pump off automatically when the

auxiliary fuel tank is empty or when the main fuel tank is full. During operation of the pumps

an advisory alert on the Garmin G1000 indicates that the fuel transfer is in progress.

If the auxiliary fuel tank is empty, a caution alert appears on the Garmin G1000. In this

case the fuel pumps must be switched OFF.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 7 - 39

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.

The fuel transfer pumps are electrically connected to the LH Main Bus and protected by

a 5A circuit breaker, if no Ice Protection System (OÄM 42-053) is installed.

If the Ice Protection System is installed, both Systems are protected by a 10 A circuit

breaker and an additional 5A fuse for the fuel transfer pumps. The circuit breaker is

labeled XFER PUMP/DE ICE.

Airplane Description DA 42 AFM

Page 7 - 40 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

The fuel quantity measuring device has

a recess which fits the airfoil of the wing

in front of the fuel tank drain, which lies

approximately 10 cm (4 in) outboard of

the engine nacelle. The metal connector

is pressed against the drain of the tank.

The amount of fuel in the tank can now

be read off from the vertical ascending

pipe.

For an exact indication the airplane must

stand on level ground and the measuring

device must be held vertically.

The designated location for the fuel

quantity measuring device is a bag on the

rear side of the pilot seat.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 41

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.

The lower yellow bar indicates that the airplane is not ready for take-off if Diesel fuel or

a blend of Diesel fuel with JET A-1 is used (approved only if MÄM 42-037 is carried out).

If the fuel grade is uncertain, take-off is not allowed in this temperature range either.

In the temperature range below -5 °C (23 °F) the engine must not be started if Diesel fuel

or a blend of Diesel fuel with JET A-1 is used. If the fuel blend is uncertain, the engine

must not be started in this temperature range either.

If the airplane is being operated with JET A-1, operation in the yellow temperature range

is permissible.

Airplane Description DA 42 AFM

Page 7 - 42 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

If the airplane is operated in a cold environment, it must be changed from Diesel fuel

operation to JET A-1 operation. To ensure that no blend of JET A-1 with Diesel fuel is

in one of the tanks, each tank must be refilled at least twice with more than 17.2 US gal

(65 liters) of JET A-1. Otherwise both tanks must be drained before refueling with JET A-1.

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 A-1 the use of the auxiliary tanks, if installed

(OÄM 42-056), is not permitted.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 43

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. Additionally a coolant

to air heat exchanger is provided for the cabin heat system. The flow through the heat

exchanger is independent of the coolant temperature. An expansion tank helps to adjust

the pressure in the system. The system is protected against overpressure by means of

a pressure relief valve.

Airplane Description DA 42 AFM

Page 7 - 44 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

A dip-stick is provided to check the oil quantity through an inspection hole in the upper

cowling. If required, oil can also be filled in there (for approved oil grades refer to Section

2.4 - POWER-PLANT LIMITATIONS).

Gearbox and propeller governor system

The second oil circuit lubricates the gearbox and serves the governor system and the

regulation of the propeller.

The gearbox oil quantity can be checked with the help of an inspection glass which can

be reached through an inspection hole on the front side of the lower cowling.

CAUTION

If the gearbox oil quantity is too low, an unscheduled

maintenance is necessary (for approved oil grades refer to

Section 2.4 - POWER-PLANT LIMITATIONS).

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 45

engine

air inlet

filter box

air filter

alternate air inlet

charger

turbine

exhaust

waste gate

engine

intercooler

alternate air valve

7.9.8 TURBO-CHARGER SYSTEM

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. Behind the turbine

the exhaust gases are guided through the lower cowling to the exterior of the airplane.

Excess exhaust gases bypass the turbine. The bypass is controlled by the ECU through

the waste gate valve. A manifold pressure sensor behind the compressor allows the ECU

to calculate the correct position of the waste gate valve. This prevents excessive manifold

pressures at low density altitudes. The intake air is compressed in the compressor which

is driven by the turbine, and is subsequently cooled down in the intercooler to increase

power. Cooling the air increases efficiency through the higher density of the cooler air.

Airplane Description DA 42 AFM

Page 7 - 46 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

To test the fire detectors (refer to Section 4A.5.1 - PRE-FLIGHT INSPECTION) push

the test button located next to the gear selector switch. An aural alert and the fire warning

message for the LH and RH engine should appear in the annunciation window of the

G1000 PFD.

CAUTION

If the aural alert or the warning does not appear, an

unscheduled maintenance is necessary.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 47

7.10 ELECTRICAL SYSTEM

Airplane Description DA 42 AFM

Page 7 - 48 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. The alternators are driven by a flat-belt.

The power output line of the left-hand alternator is connected to the 'LH main bus' via

the LH alternator relay and a 70 ampère circuit breaker. The power output line of the right-

hand alternator is connected to the 'RH main bus' via the RH alternator relay and a 70

ampère circuit breaker. Both 'main busses' are connected to the 'battery bus' via a 90

ampère circuit breaker.

Both generator power output lines also run through a current sensor for each alternator,

which provides an indication of the power being supplied to the electrical system by an

alternator including the current for battery charging on the G1000. In the event of a main

battery failure the field of each alternator is energized by two 12 V, 1.3 Ah sealed-lead-acid

batteries ('excitation'-battery) connected in series, which are installed in the nose baggage

compartment. The 'ENGINE MASTER LH (RH)'-switches connect the 'excitation'-battery

to the alternator field via a 5 A fuse.

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.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 49

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.

Load Balancing: The alternator control unit supports load balancing across the two

alternators via the internal alternator temperature. The temperature is measured and

the alternator control unit slightly decreases alternator voltage output at higher internal

alternator temperatures. Thus the load is partly shifted to the alternator with the lower

internal temperature. This system is able to balance the actual load within a few amps

between the two alternators installed.

Storage

'Main'-battery power is stored in a 24 V, 10 Ah lead-acid battery mounted on the right-aft

side of the front baggage compartment. The 'main' battery is connected to the 'hot battery

bus' via a 20 A fuse and to the 'battery bus' via the 'battery'-relay which is installed in

the relay junction box on the center-aft side of the front baggage compartment.

The 'battery'-relay is controlled with the 'ELECTRIC MASTER'-switch which is located

on the left-hand side of the instrument panel.

In addition, a non-rechargeable dry battery is installed as a further source of power for

the attitude gyro (artificial horizon) and the flood light. When the EMERGENCY switch

is set to ON, these two systems are supplied with power for at least 1.5 hours,

independent of all other electrical consumers. During each 100 hour inspection, this

battery is checked for proper functioning. Every 2 years or after use (broken seal on the

switch) the battery package must be replaced.

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'.

Airplane Description DA 42 AFM

Page 7 - 50 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

Battery bus:

The 'battery bus' is connected to the 'main'-battery via the 'battery'-relay which can be

controlled by the 'ELECTRIC MASTER'-switch. The 'battery bus' provides power to the

' LH (RH) main bus' and heavy duty power to both starters.

ECU bus:

The 'LH (RH) ECU bus' is connected to the 'LH (RH) main bus' via a diode and connected

to the power output line of the alternator via a 30 ampère circuit breaker and provides

power for the ECU A and ECU B via the 'LH (RH ECU A (B)'-Relays which are controlled

by the 'LH (RH) ENGINE MASTER'-switch. The 'LH (RH) ENGINE MASTER'-switch must

be set to 'ON' to connect the ECU A and ECU B to the 'ECU bus'.

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.

The 'AVIONIC MASTER'-switch must be set to 'ON' to connect the 'RH main bus' to the

'avionic bus'.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 51

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.

Voltmeter

The voltmeter displays the voltage of the electrical system. Under normal operating

conditions the alternator voltage is shown, otherwise it displays the 'main'-battery voltage.

Ammeter

The ammeter displays the intensity of current which is supplied to the electrical system

by the LH (RH) alternator.

Landing and taxi lights

Landing and taxi lights are built into the wing center section, and are each operated by

means of a switch (LANDING, TAXI) located on the row of switches on the instrument

panel.

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.

Flood light

A two-dimensional light emitter is mounted above the instrument panel. It illuminates the

instrument panel as well as all levers, switches, etc. The flood light is switched on and

its brightness is adjusted by means of a rotary button (FLOOD) in the left-hand section

of the instrument panel.

Airplane Description DA 42 AFM

Page 7 - 52 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Instrument lighting

With a rotary button (INSTRUMENT) in the left-hand section of the instrument panel the

internal lighting of the instruments is switched on and its brightness is adjusted.

Pitot heating

The Pitot probe, which provides measurement for the Pitot-static system, is electrically

heated. The heating is activated with a switch (PITOT HEAT) located on the row of

switches on the instrument panel. The temperature is automatically kept constant by

means of a thermal switch on the Pitot probe, and as an additional safety measure a

thermal fuse is built in. If this thermal fuse is activated, the Pitot heating can no longer

be switched on, and the Pitot heating caution will be displayed. In this case the system

should be serviced. The Pitot heat caution light is also on if the Pitot heating is switched

off.

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.

The socket itself has three pins:

• a large negative pin

• a large positive pin

• a small positive pin

A diode protects the system from reverse polarity.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 53

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

- Coolant temperature / COOLANT TEMP

- Gearbox temperature / GEARBOX

- Camshaft RPM (twice)

- Crankshaft RPM (twice)

- Fuel pressure in the common rail

- Manifold pressure

- Manifold air temperature

- Ambient air pressure

- Propeller governor / oil pressure

- Power lever position (twice)

- Voltage

- Starter switch signal

- Fuel pressure

- 'ECU Swap'-switch signal

- 'ECU Test'-switch signal

Airplane Description DA 42 AFM

Page 7 - 54 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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

- Signal for the rail-pressure regulation valve

- Signal for each of the 4 injection nozzles

- Activation of the glow plugs

- Signal for the waste gate valve

The following alerts are displayed on PFD of the G1000:

- Glow sparks active

- Status ECU A

- Status ECU B

Normally each engine is controlled and regulated by the appropriate ECU A. The ECU

B is a backup system to ensure redundancy. In case of an internal error during operation

or the loss of a sensor signal the system automatically switches to ECU B. If the loss

of the sensor signal was the cause for the error, the system automatically switches back

to ECU A.

A fault in one of the ECU's is indicated by a caution message on the PFD (L/R ECU A/B

FAIL). In case of minor faults, the annunciation can be reset once by pressing the ECU

TEST button for more than 2 seconds. However, the annunciation will re-appear upon

the next attempt to start the engine. After the indication of the L/R ECU A/B FAIL caution

message, the engine must be serviced, even if the caution message could be reset.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 55

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:

WARNING

CAUTION

ADVISORY

Crew alerts will appear in the Alerts Window on the PFD. In this window Warnings will

appear at the top, followed by Cautions and Advisories, respectively. Within the criticality

levels, messages will appear from newest (top) to oldest (bottom).

At the low right corner of the display there is a MSG (Message) soft key. The MSG key

provides two functions in the CAS:

1. Pressing the MSG key acknowledges a new master warning / caution / advisory

indication.

2. An additional MSG key press with no master alert indication active will open a

pop-up Auxiliary Flight Display (AFD) page that contains information for all active alerts.

This structure allows the crew to scroll through all system alerts if the Alerts Window

overflows. This approach displays the most critical alerts close to the pilot´s primary field

of view at all times, with the option of allowing lower criticality alerts to overflow and be

accessible from the pop-up AFD page/window.

Airplane Description DA 42 AFM

Page 7 - 56 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

Alert levels

Level Text Color Importance Audible Tone

Warning Red May require

immediate

corrective action

Warning chime tone

which repeats

without delay until

acknowledged by

the crew

Caution Amber May require future

corrective action Single warning

chime tone

Annunciation

Advisory White None

Message Advisory White None

Safe Operation

Annunciation Green Lowest None

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 57

Warning alerts on the G1000

Warning alerts Meaning / Cause

L/R ENG TEMP The annunciation is active when the engine coolant temperature

is greater than 105 °C.

L/R OIL TEMP The annunciation is active when the engine oil temperature is

greater than 140 °C.

L/R OIL PRES The annunciation is active when the engine oil pressure is

less than 1 bar.

L/R FUEL TEMP The annunciation is active when the fuel temperature is

greater than 75 °C.

L/R GBOX TEMP The annunciation is active when the gearbox oil temperature is

greater than 120 °C.

L/R ALTN AMPS The annunciation is active when the alternator load is greater than

60 amps.

L/R ENG FIRE The annunciation is active when an engine fire is detected.

L/R STARTER This annunciation is used to indicate to the pilot that the starter

is engaged when it should not be.

DOOR OPEN The annunciation is used to indicate to the pilot if the baggage-,

canopy- or rear door is open.

POSN ERROR The annunciation is active when the G1000 will no longer

provide GPS based navigational guidance.

ATTITUDE FAIL The annunciation is active when the display system is not

receiving attitude reference information from the AHRS.

AIRSPEED FAIL The annunciation is active when the display system is not

receiving airspeed input from the air data computer.

ALTITUDE FAIL The annunciation is active when the display system is not

receiving altitude input from the air data computer.

VERT SPEED

FAIL The annunciation is active when the display system is not

receiving vertical speed input from the air data computer.

HDG The annunciation is active when the display system is not

receiving valid heading input from the AHRS.

Airplane Description DA 42 AFM

Warning alerts Meaning / Cause

Page 7 - 58 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

WARN This annunciation constitutes a RAIM position warning. The

nav deviation bar is removed.

Audible warning alerts

Warning alerts Meaning / Cause

landing gear

retracted

A warning chime tone which repeats without delay is active

when the landing gear is retracted while the flaps move into

the LDG position or when the POWER lever is placed in a

position below 25 %.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 59

Caution alerts on the G1000

Caution-alerts Meaning / Cause

L/R ECU A FAIL

L/R ECU B FAIL

The annunciation is active when a fault in ECU A or ECU B

has occurred.

In case of minor faults, the annunciation can be reset once by

pressing the ECU TEST button for more than 2 seconds.

However, the annunciation will re-appear upon the next

attempt to start the engine.

L/R FUEL LOW The annunciation is active when the fuel quantity is below

4 ± 1 gal usable fuel.

L/R VOLTS LOW The annunciation is active when bus voltage is less than

25 volts.

L/R ALTN FAIL The annunciation is active when the alternator has failed.

L/R COOL LVL The annunciation is active when engine coolant level is low.

PITOT FAIL The annunciation is active when the Pitot heater is failed.

PITOT HT OFF The annunciation is active when the Pitot heat is off.

STALL HT FAIL The annunciation is active when the stall heater is failed.

STALL HT OFF The annunciation is active when the stall heater is off.

STICK LIMIT Control stick limiting system (variable elevator stop) has

failed.

L/R AUX FUEL E

This annunciation can only occur when the auxiliary fuel tank

system (optional) is installed.

The annunciation is active when the L/R auxiliary fuel tank is

empty and the FUEL TRANSFER pump is ON.

INTEG

RAIM not

available

The annunciation is active when RAIM (Receiver

Autonomous Integrity Monitor) is not available.

AHRS ALIGN:

Keep Wings Level The annunciation is active when the AHRS (Attitude and

Heading Reference System) is aligning.

Airplane Description DA 42 AFM

Page 7 - 60 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

Message advisory alerts on the G1000

Advisory alerts Meaning / Cause

PFD FAN FAIL The annunciation is active when the PFD fan is inoperative.

MFD FAN FAIL The annunciation is active when the MFD fan is inoperative.

GIA FAN FAIL The annunciation is active when the GIA fan is inoperative.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 61

7.11 PITOT-STATIC SYSTEM

Total pressure is measured at the leading edge of a Pitot probe under the left wing. Static

pressure is measured at two orifices at the lower and rear edges of the same probe. To

protect against dirt and condensation there are filters in the system, which are accessible

from the wing root. The Pitot probe is electrically heated.

With the alternate static valve, the static pressure in the cabin can be used as static

pressure source in the event of a failure of the 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. The stall status is announced to the pilot by a continuous sound in the

cockpit.

The lift detector vane, the mounting plate and the complete housing are heated to prevent

icing. Heating is engaged together with the Pitot heating.

Airplane Description DA 42 AFM

Page 7 - 62 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. The system

contains dual GPS receivers, dual VOR/ILS receivers, dual VHF communications

transceivers, a transponder, and an integrated annunciation system to alert the pilot of

certain abnormal conditions.

A remote avionic box is located behind the aft baggage compartment frame. A push-to-talk

(PTT) button for the COM portion of the G1000 is mounted on the end of each control

stick. There are connection facilities for up to 4 headsets between the front seats.

Refer to the Garmin G1000 Cockpit Reference Guide, Garmin P/N 190-00406-00, dated

September, 2004, and Pilot's Guide, P/N K00-00138-00, dated September, 2004, for

complete descriptions of the G1000 system and operating procedures.

NOTE

Near the DME ground station, it can happen under certain

adverse conditions that the Bendix/King KN 63 DME loses

the direct signal from the ground station and locks onto an

"echo". This will result in an inaccurate indication of the

distance.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 63

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. Rate of turn information is shown on the scale above the compass rose; full scale

deflection is equal to a standard rate turn. The following controls are available on the

PFD (clockwise from top right):

* Communications frequency volume and squelch knob

* Communications frequency set knobs

* Communications frequency transfer button

* Altimeter setting knob (baro set)

* Course knob

* Map range knob and cursor control

* FMS control buttons and knob

* PFD softkey buttons, including master warning/caution acknowledgment

* Altitude reference set knob

* Heading bug control

* Navigation frequency transfer button

* Navigation frequency set knobs

* Navigation frequency volume and Identifier knob

Airplane Description DA 42 AFM

Page 7 - 64 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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. Acknowledging the alert will cancel the flashing and provide

a text description of the message. Refer to Chapter 3 - EMERGENCY PROCEDURES,

Chapter 4B - ABNORMAL OPERATING PROCEDURES, and Section 7.10.3 - WARNING,

CAUTION AND ADVISORY LIGHTS.

DA 42 AFM Airplane Description

Doc. No. 7.01.05-E Rev. 4 30-Nov-2005 Page 7 - 65

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).

Trend vectors are shown on the airspeed and altimeter displays as a magenta line

predicting 6 seconds at the current rate. The turn rate indicator also functions as a trend

indicator on the compass scale.

The PFD can be displayed in a composite format for emergency use by pressing the

DISPLAY BACKUP button on the audio panel. In the composite mode, the full crew

alerting function remains, but no map functions are available.

7.13.3 MULTI-FUNCTION DISPLAY (MFD)

The Multi-Function Display (MFD) typically displays engine data, maps, terrain, traffic

and topography displays, and flight planning and progress information. The display unit

is identical to the PFD and contains the same controls as previously listed.

Engine instruments are displayed on the MFD. Discrete engine sensor information is

processed by the Garmin Engine Airframe (GEA) sub-system. When an engine sensor

indicates a value outside the normal operating range, the legend will turn yellow for caution

range, and turn red and flash for warning range.

Also refer to Section 7.9.4 - ENGINE INSTRUMENTS.

Airplane Description DA 42 AFM

Page 7 - 66 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

Lights above the selections indicate what selections are active. Pressing the red DISPLAY

BACKUP button on the audio panel causes both the PFD and MFD to display a composite

mode.

7.13.5 ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS)

The Attitude and Heading Reference System (AHRS) uses GPS, rate sensors, air data,

and magnetic variation to determine pitch and roll attitude, sideslip and heading. Operation

is possible in a degraded mode if the system loses any of these inputs. Status messages

alert the crew of the loss of any of these inputs. The AHRS will align while the airplane

is in motion, but will align quicker if the wings are kept level during the alignment process.

7.13.6 AIR DATA COMPUTER (ADC)

The Air Data Computer (ADC) provides airspeed, altitude, vertical speed, and air

temperature to the display system. In addition to the primary displays, this information

is used by the FMS and TIS systems.

DA 42 AFM Handling, Care,

Maintenance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 8 - 1

CHAPTER 8

AIRPLANE HANDLING, CARE AND MAINTENANCE

Page

8.1 INTRODUCTION .......................................8-2

8.2 AIRPLANE INSPECTION INTERVALS ......................8-2

8.3 AIRPLANE ALTERATIONS OR REPAIRS ....................8-3

8.4 SERVICING ...........................................8-3

8.4.1 REFUELING ......................................8-3

8.4.2 ENGINE OIL LEVEL CHECK .........................8-4

8.4.3 GEARBOX OIL LEVEL CHECK .......................8-4

8.4.4 TIRE INFLATION PRESSURE CHECK .................8-5

8.5 GROUND HANDLING / ROAD TRANSPORT .................8-6

8.5.1 GROUND HANDLING ..............................8-6

8.5.2 PARKING ........................................8-7

8.5.3 MOORING .......................................8-9

8.5.4 JACKING ........................................8-9

8.6 CLEANING AND CARE .................................8-10

8.6.1 PAINTED SURFACES .............................8-10

8.6.2 CANOPY AND REAR DOOR ........................8-11

8.6.3 PROPELLER ....................................8-11

8.6.4 ENGINE ........................................8-11

8.6.5 INTERIOR SURFACES ............................8-11

8.7 GROUND DE-ICING ....................................8-12

Handling, Care,

Maintenance DA 42 AFM

Page 8 - 2 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

8.2 AIRPLANE INSPECTION INTERVALS

Inspections are scheduled every 50, 100, 200, 1000 and 2000 hours. Independent of the

flight hours an annual inspection must be performed every year. A non-recurring engine

inspection must be performed on new engines after 3 to 6 hours. The respective inspection

checklists are prescribed in the Airplane Maintenance Manual, Chapter 05.

For maintenance work on engine and propeller, the currently effective Operator's Manuals,

Service Instructions, Service Letters and Service Bulletins of TAE and mt-Propeller must

be followed. For airframe inspections, the currently effective checklists/manuals, Service

Bulletins and Service Instructions of the manufacturer must be followed.

CAUTION

Unscheduled maintenance checks are required after:

- hard landings

- propeller strike

- engine fire

- lightning strike

- occurrence of other malfunctions and damage

Unscheduled maintenance checks are described in the

Airplane Maintenance Manual (Doc. No. 7.02.01; Section

05-50).

DA 42 AFM Handling, Care,

Maintenance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 8 - 3

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. Fuel burns violently

and can cause injury to persons and damage to the airplane.

WARNING

Do not get fuel on your skin. Fuel can cause skin disease.

WARNING

Connect the airplane and the fuel supply vehicle to electrical

ground before refueling. If you do not ground the airplane,

static electricity can cause fire during refueling.

WARNING

Make sure that a suitable fire extinguisher is available at all

times during refueling.

WARNING

Turn off all ground equipment in the refueling area.

WARNING

Do not operate electrical switches in the airplane during

refueling.

Handling, Care,

Maintenance DA 42 AFM

Page 8 - 4 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

3. Refuel the airplane.

4. Install the fuel filler cap.

5. Repeat steps 2 to 4 for the other wing.

6. Remove the ground cable from the airplane and the fuel supply vehicle.

8.4.2 ENGINE OIL LEVEL CHECK

1. Open the inspection door on top of the upper left cowling.

2. Remove the filler cap.

3. Clean the oil dip-stick.

4. Install the filler cap.

5. Remove the filler cap again.

6. Read the oil level from the dip-stick.

7. If necessary, add engine oil and repeat steps 3 to 6.

8. Install the filler cap.

9. Close the inspection door.

10. Repeat steps 1 to 9 for the other engine.

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.

DA 42 AFM Handling, Care,

Maintenance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 8 - 5

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).

5. Install dust cap on valve stem by turning clockwise.

6. Install the wheel cover (main wheels only).

Handling, Care,

Maintenance DA 42 AFM

Page 8 - 6 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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.

Tow bar

WARNING

The tow bar must be removed before starting the engine.

CAUTION

The tow bar may only be used for moving the airplane on the

ground by hand. After moving the airplane, the tow bar must

be removed.

DA 42 AFM Handling, Care,

Maintenance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 8 - 7

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. Parking in a hangar is recommended.

Control surfaces gust lock

The manufacturer offers a control surfaces gust lock which can be used to block the

primary controls. It is recommended that the control surfaces gust lock be used when

parking outdoors, because otherwise the control surfaces can hit the stops in strong tail

wind. This can lead to excessive wear or damage.

WARNING

The control surfaces gust lock must be removed before flight.

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.

4. Attach the locks and tighten the straps.

For removal reverse the sequence.

Handling, Care,

Maintenance DA 42 AFM

Page 8 - 8 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

DA 42 AFM Handling, Care,

Maintenance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 8 - 9

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.

8.5.4 JACKING

The airplane can be jacked at the two jackpoints located on the lower side of the center

wing's LH and RH root ribs as well as at the tail fin.

Handling, Care,

Maintenance DA 42 AFM

Page 8 - 10 Rev. 3 15-Oct-2005 Doc. No. 7.01.05-E

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. Nevertheless, it is recommended to protect the airplane against moisture and

dampness. It is also recommended not to store the airplane outside for long periods of

time.

Dirt, insects, etc. can be removed with water alone and if necessary with a mild detergent.

An automotive paint cleaner can be used for stubborn spots. For best results, clean the

airplane after the day's flying is ended, so that the dirt will not become ingrained.

Oil stains, exhaust stains, etc. on the lower fuselage skin can be removed with a cold

detergent. Before starting, ensure that the detergent does not affect the surface finish.

Use commercial automotive preservatives without silicone additives to conserve the paint

finish.

DA 42 AFM Handling, Care,

Maintenance

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 8 - 11

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.

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.

The penetration of moisture into the wooden core must be avoided by all means. Should

doubts arise, an appropriately rated inspector must be consulted.

8.6.4 ENGINE

Engine cleaning is part of the scheduled inspections.

8.6.5 INTERIOR SURFACES

The interior should be cleaned using a vacuum cleaner. All loose items (pens, bags etc.)

should be removed or properly stored and secured.

All instruments can be cleaned using a soft dry cloth. Plastic surfaces should be wiped

clean using a damp cloth without any cleaning agents.

The leather interior should be treated with leather sealer within 3 months since new, and

then at intervals of 3 to 6 months. Clean the leather interior with an appropriate mild leather

cleaning agent and a soft cleaning brush for leather.

Note that the acrylic glass windows transmit the ultraviolet radiation from the sun.

Handling, Care,

Maintenance DA 42 AFM

Page 8 - 12 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

3. Use a soft piece of cloth to wipe the airplane dry.

DA 42 AFM Supplements

Doc. No. 7.01.05-E Rev. 3 15-Oct-2005 Page 9 - 1

CHAPTER 9

SUPPLEMENTS

Page

9.1 INTRODUCTION .......................................9-2

9.2 LIST OF SUPPLEMENTS.................................9-2

Supplements DA 42 AFM

Page 9 - 2 Rev. 4 30-Nov-2005 Doc. No. 7.01.05-E

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.

All approved supplements are listed in the List of Supplements in this Chapter.

The Airplane Flight Manual contains exactly those Supplements which correspond to the

installed equipment according to the Equipment Inventory of Section 6.5.

9.2 LIST OF SUPPLEMENTS

Airplane S/N: Registration: Date:

Sup.

No. Title Rev.

No. Date applicable

YES NO

A13 Autopilot System,

Bendix/King KAP 140 0 01-Dec-2004 99

S02 Ice Protection System 1

06-Dec-2005

S03

Ice Protection System

(Known Icing)

12-Jan-2006

DA 42 AFM Rev. 4 DA42_Diamond Twin_Flight Manual DA42 Diamond Twin Flight

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