Diamond Aircraft DA 42 Technical specifications

.. Diamond
v AIRCRAFT
AIRPLANE FLIGHT MANUAL
DA42
Airworthiness Category
Requirement
Seriai Number
Registration
Doc. No.
Date
of Issue
Signature
ACG Project Manager
Stamp
Date ofapproval
:Normal
: JAR-23
: lLz r; Z-- 5
: Ht)- L'1k
: 7.01.05-E
25. Ct !. 2005
This Flight Manual has been verlfied for EASA by the Austrlan Civil Aviation Authority
Austro Control (ACG) as Primary Certification Authority (PCA) ln accordance wlth the
valld Certification Procedures and approved by EASA with approval no..200'i -4'to3 .
This Airpiane Flight Manuel
is FAA approved for U.S. registered alrcraft ln accordance
wlth
the provisionsof 14 CFRSection 21 . 29, and lsrequlred by FAA TypeCertificate Data
Sheet no.: A57CE
DIAMOND AIRCRAFT INDUSTRIES GMBH
N.A. OTTO·STR. 5
A-2700
WIENER NEUSTADT
AU STRIA Page
0- o. Rev .3

Introduction
lâDiamond
~ AIRCRAFT
NOTE
This airplane flight manual is valid for DA42 airplanes with
a KAP 140
or no autopilot system installed.
Refer to the airplane flight manual "DA42 with Garmin
GFC 700 (OAM 42-102)", Doc. No. 7.01.06-E for airplanes
with a Garmin Autopilot system installed.
DA42AFM
Page 0- Oa Rev. 5 15 Nov 2007 Doc. # 7.01.05-E

DA42AFM
~ADi a mond
..., w AIRCRAFT Introduction
FOREWORD
We congratulate you on the acquisition ofyour new DIAMOND DA 42.
Skillful operation of an airplane increases both safety and the enjoyment of flying.
Please lake the
ti me therefore, to familiarize yourself with your new DIAMOND DA 42.
This airplane may only be operated
in accordance with the procedures and operating
limitations ofthis Airplane Flight
Ma nuai.
Before this airplane is operated for the first
ti me, the pilot must familiarize himselfwith
the complete contents ofthis Airplane Flight
Ma nuai.
ln the event thal you have obtained your DIAMOND DA 42 second-ha nd , please let us
know your address, so
th at we can supply you with the publications necessary for the
safe operation ofyour airplane.
This document
is protected by copyright. Ali 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.
Copyright© by: DIAMOND AIRCRAFT INDUSTRIES GMBH
N
.A. Otto-Strasse 5
A-2700 Wiener Neustadt, Austria
Phone [phone]
Fa x [phone]
E-Mail [e-mail]
Doc.
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DA42AFM
66Diamond
'Y AIRCRAFT Introduction
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 1EQUIPMENT 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
Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page
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1 DA42AFM
~Diamond
Tq AIRCRAFT
CHAPTER 1
GENERAL
Page
1.1 INTRODUCTION . .. ..... .. .. ... . ... ... .. . . .... . ........ 1-2
1.2 CERTIFICATION BASIS ..... ... ... . ..... •.. .. . ....... .... 1-6
1.3 WARNINGS, CAUTIONS AND NOTES . .
.. . . .. . ....... .... .. 1-6
1.4 DIMENSIONS ... . .................... . . ............ . . .. 1-7
1.5 DEFINITIONS AND ABBREVIATIONS .
.. ........ .. ....... . .. 1-9
1.6 UNITS
OF MEASUREMENT . . .. ..... . ... . . ......... .. ... 1-17
1.6.1 CONVERSION FACTORS .
.... .......... .... . ...... 1-17
1.6.2 CONVERSION CHART LITERS 1
US GALLONS ......... 1-19
1.7 THREE-VIEW DRAWING .
....... ... ........... . . .... . ... 1-20
1.8 G1000 AVIONICS SYSTEM .............. .. ............. . 1-21
1.9 SOURCE DOCUMENTATION . . ........ ........... . . .... . 1-24
1.9.1 ENGINE ...
.. ...... .... .............. . ......... . 1-24
1.9.2 PROPELLER
......... . .. . ... . .. . ....... .. ....... 1-25
1.9.3 AVIONICS SYSTEM
.. ........ . ... . ...... ... . . .. . . . 1-25
Doc.
No. 7.01 .05-E
Rev.8
15-Dec-2017 Page 1 - 1

lâ Diamond
~ A/RCRAFT
DA42AFM 1
1.1 INTRODUCTION
This Airplane Flight Ma nuai has been prepared in arderto provide pilots and instructors
with ali the information required for the safe and efficient operation
of the airplane.
TheAirplane FlightManual includes ali the datawhich mustbe madeavailableto thepilot
according to the JAR-23 requirement. Beyond this, itcontains furtherdata and operating
instructions which,
in the manufacturer's opinion, cou Id be of value to the pilot.
__- This Airplane Flight Manual is valid for ali seriai numberswith a KAP 140 orno autopilot
system installed. Equipment and modification level (design details}
of the airplane may
vary from seriai numberto seriai number. Therefore, some
of the information contained
in this manual isapplicabledepending on the respective equipmentand modification lev el.
The exact equipment of your seriai number is recorded in the Equipment lnventory in
Section 6. 5. The modification level is recorded in the following table (as faras necessary
for this manual}.
Modification Source lnstalled
Use of Diesel Fuel MAM 42-037 o yes o no
lncreased Take-Off Mass MAM 42-088 o yes o no
New Engine Instrument Markings MAM 42-101 o yes o no
Autopilot Static Source MAM 42-186 o yes o no
TAE 125-02-99 Engine MAM 42-198 o yes o no
ECU Backup Battery MAM 42-240 o yes o no
Firmware 2.7, MAM 42-284 o yes o no
Mapping 028V273DA42
Firmware 2.91 , MAM 42-304 o yes o no
Mapping 028V291DA42
ECU Firmware TAE-125 m2.
91 , MAM 42-310 o yes o no
ECU Mapping R28V291 DIA
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1-2 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E

1 DA42AFM
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AIRCRAFT
Genemll
Modification Source lnstalled
Firmware 2.91, MAM 42-529 o yes o no
Mapping 028V294DA42
lee Protection System OAM 42-053 o yes o no
lee Protection System OAM 42-054 o yes o no
(Known lcing)
Oxygen System OAM 42-055 o yes o no
Auxiliary Fuel Tanks OAM 42-056 o yes o no
Front Seats with Adjustable OAM 42-067 o yes o no
Backrest
Electrical Rudder Pedal OAM 42-070
Adjustment o yes o no
Mission Power Supply System OAM 42-074/a o yes o no
Removable Fuselage Nose Cone OAM 42-077 o yes o no
Operator Desk OAM 42-111 o yes o no
(Full CFRP Version)
Operator Desk (CFRP Version OAM 42-111/a o yes o no
with Aluminum Joint)
Garmin GWX 68 Weather Radar OAM42-119 o yes o
no
ECU Backup Battery OAM 42-129 o yes o no
Exhaust End Pipe OAM 42-130 o yes o no
DA 42 M -IFR OAM 42-141 o yes o no
Operator Desk OAM 42-158 o yes o no
(Full Aluminum Version)
lncrease of Maximum OAM 42-188
Zero Fuel Mass o yes o
no
Maximum Landing Mass 1785 kg OAM 42-195 o yes o no
Emergency Axe OAM 42-205 o yes o no
Doc. No. 7.
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17 Page 1 - 3

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Modification Source lnstalled
TAE 125-02-114 Engine OAM 42-252/b o yes
Front Seats with Adjustable OAM 42-259 o yes
Backrest -Hydrolok
Emergency Egress Hammer OAM 40-304 o yes
NOTE
The use of ECU Mapping 028V273DA42, ECU
Mapping 028V291DA42 and ECU Mapping 028V294DA42
is limited to TAE 125-02-99 engines (MAM 42-198, latest
revisi
on carri ed out ).
NOTE
The use of ECU Mappi ng R2 8V 291 DIA is limited to
TAE 125-01 engines.
o
no
o no
o no
ThisAirplane Flight Manual must be kept
on board the airplaneatali times.ltsdesignated
place
is the side bag oftheforward leftseat. The designated placeforthe Garmin G1000
Cockpit Reference Guide
is the bag on the rear side ofthe forward left seat.
Page 1 - 4
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1 DA42AFM
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AIRCRAFT
CAUTION
The DA 42 is a twin engine airplane. When the operating
limitationsand 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
recommended for flights
du ring the night, on top, under IMC,
or above terrain which is unsuitable for a landing,
to select
flighttimes and flight routes
su ch that reduced performance
in case of single engine operation does not constitute a risk.
Doc.
No . 7.01.05-E Rev. 8 15-Dec-2017
Geoernll
Page 1 - 5

1 Ge"ernl
~ Diamon d
~~ A/RCRAFT
DA42AFM 1
1.2 CERTIFICATION BASIS
The certification basis is JAR-23, published on 11-Mar-1994, including Am dt. 1, and
additional requirements as laid down
in CRI A-01.
1.3 WARNINGS. CAUTIONS AND NOTES
Special statements in the Airplane Flight Ma nuai concerning the safety or operation of
the airplane are highlighted
by being pr efi x ed by one of the following terms:
Page
1-6
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 notdirectly related to
safety but which
is important or unusual.
Rev.8 15-Dec-2017 Doc. No. 7. 01 .05-E

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A/RCRAFT
Ge"ernll
1.4 DIMENSIONS
NOTE
Ali dimensions shown below are approximate.
Overall Dimensions
Span 13.42 m 44.0
ft
13.55 m 44.5 ft including ACL
Length 8.
56 m 28 ft 1 in
Height 2.49 m 8
ft 2 in
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
Leading edge sweep
Area (total, left + right) 0.66 m• 7.1 sq.ft.
Doc.
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1 Ge"ern l
Winq Flaps
Area (total, left + righi}
Horizontal Tail
Area
Elevator area
Angle of incidence
Vertical Tail
A
rea
Rudder area
Landing Gear
Track
Wheelbase
/ Nose wheel
Main wheel
Page 1 - 8 Rev. 8
MâDiamond
'V 4" AIRCRAFT
2.18 m2
2.35 m2
0.66 m2
23.4 sq . ft .
25.3
sq .ft.
7.1 sq.ft.
-1.1 o relative to longitudinal axis ofairplane
2.43 m2 26.2
sq . ft .
0.78 m2 8.4 sq.ft.
2.
95 m 9 ft 8 in
1.735 m 5 ft 8 in
5.00-5*
15x6.0-6*
• for details refer to the Airplane Maintenance
Manual, Doc.
No. 7.02.01, latest revision
15-Dec-2017 Doc. No. 7.01.05-E

IDA 4 2AF M
~Diamond
AIRCRAFT G
e"emll
1.5 DEFINITIONS AND ABBR EVI ATIONS
(a) Airspeeds
CAS:
Cal ibrated Airspeed.lndicatedairspeed,corrected for installation and instrument
errors. CAS equals TAS at standard atmospheric conditions (ISA) at MSL.
lAS: lndicated Airspeed as shown
on an airspeed indicator.
KCAS: CAS
in knots.
KlAS: lAS
in knots.
TAS: True Airspeed. The speed of the airplane relative to the air. TAS
is CAS
corrected
fo r errors due to altitude and temperature.
v
A: Maneuvering Speed. Full orabruptcontrol surface movement is notpermissible
above this speed.
v
FE : 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
duri
ng the extension or retraction ofthe landing gear.
vLE: Maximum Landing Gear Extended Speed. This speed may not be exceeded
ifthe landing gear
is extended.
V mcA: Minimum Control Speed. Minimum speed necessary to be able to control the
airplane
in case ofone engine inoperative.
v
NE : Never Exceed Speed in smooth air.This speed must not be exceeded in any
operation.
vN
0: Maximum Structural Cruising Speed. This speed may be exceeded only
in
smooth air, and then only with caution.
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1 Gen.,al
6â Diamond
V#"' AIRCRAFT
DA42AFM 1
V s: Stalling Speed, orthe minimum continuous speed atwhich the airplane is still
controllable
in the given configuration.
Vs0: Stalling Speed, orthe minimum continuous speed atwhich the airplane is still
controllable
in the landing configuration.
Vs1: Stalling Speed, orthe minimum continuous speed atwhich the airplane is still
controllable with flaps and landing gear retracted.
V ssE : Minimum Control Speed for Schooling. Minimum speed necessary in case of
one engine intentionally inoperative 1idle (training purposes).
v
x: Best Angle-of-Ciimb Speed.
v
Y: Best Rate-of-Ciimb Speed.
V vsE : Best Rate of-Ciimb Speed for one engine inoperative.
(b) Meteorological Terms
ISA: International Standard Atmosphere. Conditions atwhich air is identified
as an ideal drygas. The temperature at mean sea level is 15 oc(59 °F),
air pressure at MSL is 1,013.25 hPa (29.92 inHg); the temperature
gradient up to the altitude at which the temperature reaches -56.5 oc
(-69.7 °F) is -0 .0065°C/m (-0.00357 °F/ft), and abovethisO °C/m (0 °F/ft).
MSL: Mean Sea Level.
OAT: Outside Air Temperature.
QNH: Theoretical atmospheric pressureatMSL,calculated from theelevation
of the measuring pointabove MSL and the actual atmosphericpressure
at the measuring point.
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1 DA42AFM
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AIRCRAFT
Gen.,•ll
Density Altitude:
Altitude
in ISA conditions at which the airdensity is equal to the current
air density.
lndicated Pressure Altitude:
Altitude reading with altimeler set to 1,013.25 hPa (29.92 inHg).
Pressure Altitude:
Wind:
Altitudeindicated by a barometricaltimeter,which issetto 1,013.25hPa
(29.92 inHg). The Pressure Altitude is the lndicated Pressure Altitude
corrected for installation and instrument errors.
ln this Airplane Flight Manual altimeter instrument errors are regarded
as zero.
The wind speeds which are shown as variables
in the diagrams in this
manual should be regarded as headwind ortailwind components
of the
measured wind.
le) Fliqht Performance and Flight Planning
AGL: Above Ground Level.
Demonstrated Crosswind Component:
The speed
of the crosswind component at which adequate
maneuverability forlake-offand landing has been demonstrated during
type certification.
MET: Weather, weather advice.
NAV: Navigation, route planning.
RoC: Rate
of Climb.
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1Gene<al
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V#" AIRCRAFT
DA42AFM 1
(dl Mass and Balance
CG: Center
of Gravity, also calied 'center of mass'. lmaginary point in which
the airplane mass is assumed to be concentrated for massand balance
calculations. lts distance from the Datum Plane is equal to the Center
of Gravity Moment Arm.
Center
of Gravity Moment Arm:
TheMomentArm which
is obtained ifone divides the sum of theindividual
moments
of the airplane by its total mass.
Center
of Gravity Limits:
OP:
The Center of Gravity range within which the airplane,at a given mass,
must be operated.
Datum Plane; an imaginary vertical plane from which ali horizontal
distances for center
of gravity calculations are measured.
EmptyMass: Themass
of theairplaneincluding unusablefuel,ali operating fluids and
the maximum quantity
of oil.
Maximum Take-off Mass:
The maximum permissible mass for take-off.
Maximum Landing Mass:
Thehighestmassforlanding conditionsatthe maximum descentvelocity.
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.
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Ge""''l
Usable Fuel: The quantity of fuel available for flight planning.
Unusable Fuel: Thequantityoffuelremaining
in thetank which cannet be used for flight.
Useful Load: The difference between take-off mass and empty mass.
le) 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-offfuel temperature:
Above this fuel temperature take-off power setting is permitted.
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DA42AFM 1
(f) Designation of the Circuit Breakers on the Instrument Panel
LHMAINBUS :
COM1
GPS/NAV1
XPDR
ENG INST
PITOT
XFR PUMP/DE-ICE
TAXI/MAP/ACL
FLOOD/OXY
PFD
AOC
AHRS
GEAR WRN/ELEV. LIMIT
GEAR
RH MAIN BUS:
MFD
AH
STALL WRN
FLAP
LOG LT/START
INSTLT/NAVLT
AV/COU/FAN
AVIONIC BUS
AV CONT.
Page 1 - 14 Rev. 8
COM Radio No. 1
Global Positioning System and
NAV Receiver No. 1
Transponder
Engine Instruments
Pitot Heating System
Fuel Transfer Pump 1De-lcing System
Taxi-, Map-, Anti Collision Light
Flood Light1Oxygen System
Primary Flight Display
Air Data Computer
Attitude Heading Reference System
Landing Gear Annunciation 1Variable Elevator Stop
Landing Gear Control
Mul
ti Function Display
Artificial Horizon
Stail Warning System
Flap System
Landing Light 1Start
Instrument-, Navigation (Position) Light
Avionic-, CDU-Cooling Fans
Avionic Bus
Avionic Control
15-Dec-2017 Doc. No.
7.01 .05-E

1D A4 2 A FM
AVION/CS BUS:
COM2
GPS/NAV2
AUDIO
AUTO PILOT
Wx500
ADF
DME
WxRDR
TAS .
DATA LINK
LH ENG ECU BUS:
ECU BUS
ECU B
ECUA
LHBUS :
ALT.
LH
BATT
RH BUS:
ALT.RH
BATT
Doc. No. 7.01.05-E
<f.tDiamond
AIRCRAFT
Gen.,a ll
CO M Radio No . 2
Global Positioning System and NAV Receiver No. 2
Audio Panel
Auto Pilot System
Stormscope
Automatic Direction Finder
Distance Measuring
Equ ipment
Weather Radar
Traffic Advisory System
GDL 69A Data Link System
LH ECU Bus
LH ECU B
LH ECU A
LH Alternator
Battery
RH Alternator
Battery
Rev. 8 15-Dec-2017 Page 1 - 15

1Go"oml
RH ENG ECU BUS:
ECU BUS
ECU B
ECU A
(g) Equipment
.. Diamond
"T AJRCRAFT
RH ECU Bus
RH ECU B
RH ECU A
ELT: Emergency Locator Transmitter.
(hl Design Change Advisories
MAM: Mandatory Design Change Advisory.
OAM: Optional Design Change Advisory.
(i) Miscellaneous
DA42 A FM 1
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 lntegrated Avionics.
GFRP: Glass Fiber Reinforced Plastic.
JAR: Joint Aviation Requirements.
JCNP: Joint CertificationNalidation Procedure.
PC A: Primary Certification Authority.
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