Page 1
Page 2
Introduction DA 42 AFM
NOTE
This airplane flight manual is valid for DA42 airplanes with
a KAP 140 or no autopilot system installed.
Refer to the airplane flight manual “DA42 with Garmin
GFC 700 (OÄM 42-102)”, Doc. No. 7.01.06-E for airplanes
with a Garmin Autopilot system installed.
Page 0 - 0a Rev. 5 15 Nov 2007 Doc. # 7.01.05-E
Page 3
DA 42 AFM Introduction
FOREWORD
We congratulate you on the acquisition of your new DIAMOND DA 42.
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.
Copyright © by: DIAMOND AIRCRAFT INDUSTRIES GMBH
N.A. Otto-Strasse 5
A-2700 Wiener Neustadt, Austria
Phone : +43-2622-26700
Fax : +43-2622-26780
E-Mail : [email protected]
Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 0 - 1
Page 4
Introduction DA 42 AFM
0.1 APPROVAL
The content of approved chapters is approved by EASA. All other content is approved
by DAI under the authority of EASA DOA No. EASA.21J.052 in accordance with
Part 21.
0.2 RECORD OF REVISIONS
All revisions of this manual, with the exception of -
• 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 handwriting.
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 Ai rplane
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.
Page 0 - 2 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E
Page 5
DA 42 AFM Introduction
Rev.
No.
1
2
Reason
IFR
certification;
corrections
MÄM 42-034
(elevator
stop);
OÄM 42-060
(T&B
coordinat.);
Take-off
diagrams
FAA
Certification
Chap-
ter
all
0
4A
4B
5
6
7
Page(s)
all except
cover page
0-3, 0-5,
0-7, 0-8, 0-9
4A-9
4B-25
5-11, 5-12
6-18
7-7
Date of
Revision
1 Dec 2004 2005-196
28 Jan 2005
Approval Verification
[Ing. Andreas
Winkler for
ACG]
[10 Feb 2005
Dipl.-Ing.
(FH)
Manfred
Reichel
for DAI]
Date
Inserted
Signature
-062, -070/a,
3
MÄM 42-
-079, -080,
-091, -101,
-111/b
(TR-MÄM42-111/a),
-115
OÄM 42-
-053, -056,
-057, -059,
-079
Corrections
all all 15 Oct 2005
[25 Oct 2005
Ing. Andreas
Winkler for
ACG]
Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 0 - 3
Page 6
Introduction DA 42 AFM
Rev.
No.
4
Reason
MÄM 42-
-037, -046,
-063, -088,
OÄM 42-
-054, -077,
-080
corrections
Chap-
ter
0 0-3 thru 0-10
1 1-2, 1-11
2
3
0,16667
4B
5
6
7
8 8-4, 8-12
9 39692
Page(s)
2-2, 2-4, 2-7,
2-8, 2-10, 2-
2-15, 2-18,
2-21 thru 2-
2-26, 2-27, 2-
3-30, 3-31,
3-32, 3-38
all (4A-1 thru
4A-40)
4B-2, 4B-13,
4B-25, 4B-27,
4B-30 thru
4B-34
all (5-1 thru
5-34)
6-5, 6-8,
6-10 thru 6-
6-16, 6-20
7-1, 7-2,
7-40 thru 7-66
14,
23,
32
14,
Date of
Revision
30 Nov
2005
Approval Verification
[20 Dec 2005
EASA A.C.
Ø2618
Ing. Andreas
Winkler for
ACG]
Date
Inserted
Signature
Page 0 - 4 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E
Page 7
DA 42 AFM Introduction
Rev.
No.
5
Reason
MÄM 42-
-174/a, -186,
-198/b, -206,
-240, -254,
-258/a,
OÄM 42-
-055/a,
-056/d,
-062, -065,
-066, -067,
-070, -074,
-082, -092,
-094, -095,
-099, -101,
-105, -112,
-116, -121,
-129,
Chap-
ter
all
Page(s)
all
except cover
page
Date of
Revision
15 Nov
2007
Approval Verification
Revision
No. 5 of the
AFM Doc.
No.
7.01.05-E is
approved
under the
authority of
DOA No.
EASA.21J.
052
Date
Inserted
Signature
corrections
Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 0 - 5
Page 8
Introduction DA 42 AFM
Rev.
No.
6
Reason
MÄM 42-
-268/a, -270,
-272, -284,
-292, -301,
-304, -310,
-336, -347,
-377, -405,
-443,
OÄM 42-
-053/d &
-054/d,
-056/e,
-074/a,
-106/a,
-107/d,
-108/a,
-109/a,
-111/a &
-158, -116/a,
-125, -127,
-130, -141,
-142, -145,
-146/a, -175,
-188, -195,
-205, -208,
Chap-
ter
all
Page(s)
all
except cover
page
Date of
Revision
30 Apr 2011
Approval Verification
Revision
No. 6 of the
AFM Doc.
No.
7.01.05-E is
approved
under the
authority of
DOA No.
EASA.21J.
052
Date
Inserted
Signature
VÄM 42-002,
corrections
Page 0 - 6 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E
Page 9
DA 42 AFM Introduction
Rev.
No.
7
Reason
MÄM 42-
-529, -542,
-545/a, -546,
-575, -584/a,
-641, -685,
-716, -756,
-764/c, -814,
-861,
OÄM 42-
-055/d,
-056/f,
-094/a,
-107/f,
-111/b&
-158/a&-246,
-119, -178,
-185, -215,
-252, -253,
-259, -279,
-280,
Chap-
ter
all
Page(s)
all
except cover
page
Date of
Revision
30 Nov
2015
Approval Verification
Revision
No. 7 of the
AFM Doc.
No.
7.01.05-E is
approved
under the
authority of
DOA No.
EASA.21J.
052
Date
Inserted
Signature
corrections
'
Revision'
OÄM 42-'
-222, -252/b,'
'
8
''
'
-304/a,'
corrections'
all'
all'
except cover'
page'
15 Dec'
2017'
'
No. 8 of the'
AFM Doc.'
No.'
7.01.05-E is'
approved'
under the'
authority of'
DOA No.'
EASA.21J.'
052 '
09 Feb 2018'
'
Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 0 - 7
Page 10
Introduction DA 42 AFM
0.3 LIST OF EFFECTIVE PAGE
Ch. Page Date
0 0-0 15 Nov 2007
0-0a 15 Nov 2007
'
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Introduction DA 42 AFM
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DA 42 AFM 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 / 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
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Introduction DA 42 AFM
Intentionally left blank.
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DA 42 AFM General
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 / 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
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General DA 42 AFM
1.1 INTRODUCTION
This Airplane Flight Manual has been prepared in order to provide pilots and instructors
with all the information required for the safe and efficient operation of the airplane.
The Airplane Flight Manual includes all the data which must be made available to the pilot
according to the JAR-23 requirement. 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 with a KAP 140 or no autopilot
system installed. 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
Use of Diesel Fuel MÄM 42-037 9 yes 9 no
Increased Take-Off Mass MÄM 42-088 9 yes 9 no
New Engine Instrument Markings MÄM 42-101 9 yes 9 no
Autopilot Static Source MÄM 42-186 9 yes 9 no
TAE 125-02-99 Engine MÄM 42-198 9 yes 9 no
ECU Backup Battery MÄM 42-240 9 yes 9 no
Firmware 2.7,
Mapping O28V273DA42
Firmware 2.91,
Mapping O28V291DA42
MÄM 42-284 9 yes 9 no
MÄM 42-304 9 yes 9 no
ECU Firmware TAE-125 m2.91,
ECU Mapping R28V291DIA
Page 1 - 2 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E
MÄM 42-310 9 yes 9 no
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DA 42 AFM General
Modification Source Installed
Firmware 2.91,
Mapping O28V294DA42
Ice Protection System OÄM 42-053 9 yes 9 no
Ice Protection System
(Known Icing)
Oxygen System OÄM 42-055 9 yes 9 no
Auxiliary Fuel Tanks OÄM 42-056 9 yes 9 no
Front Seats with Adjustable
Backrest
Electrical Rudder Pedal
Adjustment
Mission Power Supply System OÄM 42-074/a 9 yes 9 no
Removable Fuselage Nose Cone OÄM 42-077 9 yes 9 no
Operator Desk
(Full CFRP Version)
MÄM 42-529 9 yes 9 no
OÄM 42-054 9 yes 9 no
OÄM 42-067 9 yes 9 no
OÄM 42-070 9 yes 9 no
OÄM 42-111 9 yes 9 no
Operator Desk (CFRP Version
with Aluminum Joint)
Garmin GWX 68 Weather Radar OÄM 42-119 9 yes 9 no
ECU Backup Battery OÄM 42-129 9 yes 9 no
Exhaust End Pipe OÄM 42-130 9 yes 9 no
DA 42 M - IFR OÄM 42-141 9 yes 9 no
Operator Desk
(Full Aluminum Version)
Increase of Maximum
Zero Fuel Mass
Maximum Landing Mass 1785 kg OÄM 42-195 9 yes 9 no
Emergency Axe OÄM 42-205 9 yes 9 no
Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 1 - 3
OÄM 42-111/a 9 yes 9 no
OÄM 42-158 9 yes 9 no
OÄM 42-188 9 yes 9 no
Page 24
General DA 42 AFM
Modification Source Installed
TAE 125-02-114 Engine OÄM 42-252/b' 9 yes 9 no
Front Seats with Adjustable
Backrest - Hydrolok
Emergency Egress Hammer' OÄM 40-304' 9 yes' 9 no'
OÄM 42-259 9 yes 9 no
NOTE
The use of ECU Mapping O28V273DA42, ECU
Mapping O28V291DA42 and ECU Mapping O28V294DA42
is limited to TAE 125-02-99 engines (MÄM 42-198, latest
revision carried out).
NOTE
The use of ECU Mapping R28V291DIA is limited to
TAE 125-01 engines.
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.
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DA 42 AFM General
CAUTION
The DA 42 is a twin engine airplane. When the operating
limitations and maintenance requirements are complied with,
it has the high degree of reliability which is required by the
certification basis. Nevertheless, an engine failure is not
completely impossible. For this reason it is highly
recommended 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.
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General DA 42 AFM
1.2 CERTIFICATION BASIS
The certification basis is JAR-23, published on 11-Mar-1994, including Amdt. 1, and
additional requirements as laid down in CRI A-01.
1.3 WARNINGS, CAUTIONS AND NOTES
Special statements in the Airplane Flight Manual concerning the safety or operation of
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.
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DA 42 AFM General
1.4 DIMENSIONS
NOTE
All dimensions shown below are approximate.
Overall Dimensions
Span : 13.42 m 44.0 ft
13.55 m 44.5 ft including ACL
Length : 8.56 m 28 ft 1 in
Height : 2.49 m 8 ft 2 in
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.
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General DA 42 AFM
Wing Flaps
Area (total, left + right) : 2.18 m² 23.4 sq.ft.
Horizontal Tail
Area : 2.35 m
2
25.3 sq.ft.
Elevator area : 0.66 m² 7.1 sq.ft.
Angle of incidence : -1.1° relative to longitudinal axis of airplane
Vertical Tail
Area : 2.43 m² 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*
Main wheel : 15x6.0-6*
* for details refer to the Airplane Maintenance
Manual, Doc. No. 7.02.01, latest revision
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DA 42 AFM General
1.5 DEFINITIONS AND ABBREVIATIONS
(a) Airspeeds
CAS: Calibrated Airspeed. Indicated airspeed, corrected for installation and instrument
errors. CAS equals TAS at standard atmospheric conditions (ISA) at MSL.
IAS: Indicated Airspeed as shown on an airspeed indicator.
KCAS: CAS in knots.
KIAS: IAS in knots.
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.
v
: Minimum Control Speed. Minimum speed necessary to be able to control the
mCA
airplane in case of one engine inoperative.
vNE: Never Exceed Speed in smooth air. This speed must not be exceeded in any
operation.
vNO: Maximum Structural Cruising Speed. This speed may be exceeded only in
smooth air, and then only with caution.
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General DA 42 AFM
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.
v
: Minimum Control Speed for Schooling. Minimum speed necessary in case of
SSE
one engine intentionally inoperative / idle (training purposes).
vx: Best Angle-of-Climb Speed.
vy: Best Rate-of-Climb Speed.
v
: Best Rate of-Climb Speed for one engine inoperative.
YSE
(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 1,013.25 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.
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.
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DA 42 AFM General
Density Altitude:
Altitude in ISA conditions at which the air density is equal to the current
air density.
Indicated Pressure Altitude:
Altitude reading with altimeter set to 1,013.25 hPa (29.92 inHg).
Pressure Altitude:
Altitude indicated by a barometric altimeter, which is set to 1,013.25 hPa
(29.92 inHg). 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.
(c) Flight Performance and Flight Planning
AGL: Above Ground Level.
Demonstrated Crosswind Component:
The speed of the crosswind component at which adequate
maneuverability for take-off and landing has been demonstrated during
type certification.
MET: Weather, weather advice.
NAV: Navigation, route planning.
RoC: Rate of Climb.
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General DA 42 AFM
(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 fluids 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.
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DA 42 AFM General
Usable Fuel: The quantity of fuel available for flight planning.
Unusable Fuel: The quantity of fuel remaining in the tank which cannot be used for flight.
Useful Load: The difference between take-off mass and empty mass.
(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.
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General DA 42 AFM
(f) Designation of the Circuit Breakers on the Instrument Panel
LH MAIN BUS:
COM1 COM Radio No. 1
GPS/NAV1 Global Positioning System and NAV Receiver No. 1
XPDR Transponder
ENG INST Engine Instruments
PITOT Pitot Heating System
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
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. Avionic Control
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DA 42 AFM General
AVIONICS BUS:
COM2 COM Radio No. 2
GPS/NAV2 Global Positioning System and NAV Receiver No. 2
AUDIO Audio Panel
AUTO PILOT Auto Pilot System
Wx 500 Stormscope
ADF Automatic Direction Finder
DME Distance Measuring Equipment
Wx RDR Weather Radar
TAS Traffic Advisory System
DATA LINK GDL 69A Data Link System
LH ENG ECU BUS:
ECU BUS LH ECU Bus
ECU B LH ECU B
ECU A LH ECU A
LH BUS:
ALT.LH LH Alternator
BATT Battery
RH BUS:
ALT.RH RH Alternator
BATT Battery
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General DA 42 AFM
RH ENG ECU BUS:
ECU BUS RH ECU Bus
ECU B RH ECU B
ECU A RH ECU A
(g) Equipment
ELT: Emergency Locator Transmitter.
(h) Design Change Advisories
MÄM: Mandatory Design Change Advisory.
OÄM: Optional Design Change Advisory.
(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.
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DA 42 AFM General
1.6 UNITS OF MEASUREMENT
1.6.1 CONVERSION FACTORS
Dimension SI-Units US Units Conversion
Length [mm] millimeters
[m] meters
[km] kilometers
Volume [l] liters [US gal] US gallons
Speed [km/h] kilometers
per hour
[m/s] meters per
second
Speed of
rotation
Mass [kg] kilograms [lb] pounds [kg] x 2.2046 = [lb]
Force,
weight
[RPM] revolutions per minute
[N] newtons [lbf] pounds
[in] inches
[ft] feet
[NM] nautical
miles
[qts] US quarts
[kts] knots
[mph] miles per
hour
[fpm] feet per
minute
force
[mm] / 25.4 = [in]
[m] / 0.3048 = [ft]
[km] / 1.852 = [NM]
[l] / 3.7854 = [US gal]
[l] / 0.9464 = [qts]
[km/h] / 1.852 = [kts]
[km/h] / 1.609 = [mph]
[m/s] x 196.85 = [fpm]
--
[N] x 0.2248 = [lbf]
Pressure [hPa] hecto-
pascals
[mbar] millibars
[bar] bars
Temperature
Doc. No. 7.01.05-E Rev. 8 15-Dec-2017 Page 1 - 17
[°C] degrees
Celsius
[inHg] inches of
mercury
[psi] pounds per
square inch
[°F] degrees
Fahrenheit
[hPa] = [mbar]
[hPa] / 33.86 = [inHg]
[bar] x 14.504 = [psi]
[°C]x1.8 + 32 = [°F]
([°F] - 32)/1.8 = [°C]
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General DA 42 AFM
Dimension SI-Units US Units Conversion
Intensity of
electric
current
Electric
charge
(battery
capacity)
Electric
potential
Time [sec] seconds --
[A] ampères --
[Ah] ampère-hours
[V] volts
--
--
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DA 42 AFM General
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
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General DA 42 AFM
1.7 THREE-VIEW DRAWING
(9 ft 8 in)
)
mm
0
n
i
7
2950 mm
2
18
ft
6
(
13420 mm (44 ft 0 in)
13550 mm (44.5 ft) including ACL
(8 ft 2 in)
2490 mm
(5 ft 8 in)
8560 mm (28 ft 1 in)
1735 mm
(6 ft 5 in)
1950 mm
(7 ft 3 in)
2205 mm
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DA 42 AFM General
1.8 G1000 AVIONICS SYSTEM
1. The G1000 Integrated Avionics System is a fully integrated flight, engine,
communication, navigation and surveillance instrumentation system. The system
consists of a Primary Flight Display (PFD), Multi-Function Display (MFD), audio panel,
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.
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General DA 42 AFM
(b)The systems meets RNP5 airspace (BRNAV) requirements of AC 90-96 and in
accordance with AC 20-138A, and FAA Order 8110.60 for oceanic and remote
airspace operations, provided it is receiving useable navigation information from
the GPS receiver. The system meets the accuracy requirements of EASA AMC 20-4
for Basic RNAV.
(c) The Garmin GNSS navigation system as installed in this airplane complies with
the equipment requirements of FAA AC 90-100A for RNAV 2 and RNAV 1
operations.
(d) The Garmin GNSS navigation system as installed in this airplane complies with
the equipment requirements of FAA AC 90-105 and meets the equipment
performance and functional requirements to conduct RNP terminal departure and
arrival procedures and RNP approach procedures without RF (radius to fix) legs.
(RNP1, RNP APCH0.3 LNAV).
(e)The Garmin GNSS navigation system as installed in this airplane has been found
to comply with the requirements for primary means of Class II navigation in oceanic
and remote navigation (RNP-10) without time limitations in accordance with FAA
AC 20-138A and FAA Order 8400.12A. The Garmin GNSS navigation system can
be used without reliance on other long-range navigation system.
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.
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DA 42 AFM General
5. If the Garmin GWX 68 Weather Radar System is installed, it can be used to aid the
pilot in avoiding thunderstorms and associated turbulence or for ground mapping. The
GWX 68 shall be used to avoid severe weather and not for penetrating severe weather.
Pulse type weather radar systems like the GWX 68 detect precipitation only, not clouds
or turbulence. The display may indicate clear areas between intense returns, but this
does not necessarily mean it is safe to fly between them. As installed on the DA 42,
the Garmin GWX 68 has a demonstrated range of 160 nautical miles. Refer to Garmin
G1000 Pilot’s Guide for the DA 42, P/N 190-00649-04 in the latest effective issue for
further information.
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General DA 42 AFM
1.9 SOURCE DOCUMENTATION
This Section lists documents, manuals and other literature that were used as sources
for the Airplane Flight Manual, and indicates the respective publisher. However, only the
information given in the Airplane Flight Manual is valid.
1.9.1 ENGINE
Address: Technify Motors GmbH
Platanenstrasse 14
D-09356 St. Egidien
GERMANY
Phone: +49-(37204)-696-0
Fax: +49-(37204)-696-2910
Website: www.technify.de
Documents: TAE 125-01 Operation and Maintenance Manual
or
TAE 125-02-99 Operation and Maintenance Manual
(if MÄM 42-198 carried out)
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DA 42 AFM General
1.9.2 PROPELLER
Address: mt-propeller
Airport Straubing Wallmühle
D-94348 Atting
GERMANY
Documents: E-124, Operat ion 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-( ), latest effective issue'
G1000 Pilot’s Guide
P/N 190-00649-( ), latest effective issue'
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General DA 42 AFM
Intentionally left blank.
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DA 42 AFM Operating Limitations
CHAPTER 2
OPERATING LIMITATIONS
Page
2.1 INTRODUCTION .......................................2-3
2.2 AIRSPEED ............................................2-4
2.3 AIRSPEED INDICATOR MARKINGS ........................2-6
2.4 POWER-PLANT LIMITATIONS ............................2-7
2.5 ENGINE INSTRUMENT MARKINGS .......................2-10
2.6 WARNING, CAUTION AND ADVISORY ALERTS .............2-12
2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000
...............................................2-12
2.6.2 OTHER WARNING ALERTS ........................2-15
2.7 MASS (WEIGHT) ......................................2-16
2.8 CENTER OF GRAVITY .................................2-18
2.9 APPROVED MANEUVERS ..............................2-19
2.10 MANEUVERING LOAD FACTORS ........................2-20
2.11 OPERATING ALTITUDE ................................2-21
2.12 FLIGHT CREW........................................2-21
2.13 KINDS OF OPERATION.................................2-21
2.14 FUEL................................................2-25
2.15 LIMITATION PLACARDS ................................2-27
2.16 OTHER LIMITATIONS .................................. 2-31
2.16.1 FUEL TEMPERATURE............................2-31
2.16.2 BATTERY CHARGE..............................2-31
2.16.3 EMERGENCY SWITCH ...........................2-32
2.16.4 DOOR LOCKING DEVICE .........................2-32
2.16.5 ELECTRONIC EQUIPMENT........................2-32
Doc. No. 7.01.05-E Rev. 8 15-Dec-2017
EASA
Page 2 - 1
approved
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Operating Limitations DA 42 AFM
2.16.6 GARMIN G1000 AVIONICS SYSTEM ............... 2-33
2.16.7 SMOKING ..................................... 2-37
2.16.8 GROUND OPERATION .......................... 2-37
2.16.9 USE OF THE SUN VISORS ....................... 2-37
2.16.10 STRUCTURAL TEMPERATURE ................... 2-37
2.16.11 GARMIN GWX 68 WEATHER RADAR OPERATION . . . 2-38
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DA 42 AFM Operating Limitations
2.1 INTRODUCTION
Chapter 2 of this Airplane Flight Manual provides operating limitations, instrument markings
and placards necessary for the safe operation of the airplane, its powerplants, standard
systems and standard equipment.
The limitations included in this Chapter are approved.
WARNING
Operation of the airplane outside of the approved operating
limitations is not permissible.
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Operating Limitations DA 42 AFM
2.2 AIRSPEED
Airspeed IAS Remarks
v
A
Maneuvering
speed if
MÄM 42-088 or
OÄM 42-054 or
both
above 1542 kg
(3400 lb)
up to 1542 kg
(3400 lb)
126 KIAS Do not make full or abrupt
control surface movement
above this speed.
120 KIAS
incorporated
Neither
MÄM 42-088
nor
OÄM 42-054
above 1468 kg
(3236 lb)
up to 1700 kg
(3748 lb)
124 KIAS
incorporated
1250 kg
121 KIAS
(2756 lb) to
1468 kg
(3236 lb)
v
FE
Max. flaps
extended speed
LDG 111 KIAS Do not ex ceed these speeds
with the given flap setting.
APP 137 KIAS
v
LO
Max. landing
gear operating
speed
Extension v
Retraction v
LOE
LOR
194 KIAS Do not operate the landing
gear above this speed.
156 KIAS
v
v
LE
MCA
Max. landing gear extended speed 194 KIAS Do not exceed thi s speed
Minimum control speed airborne 68 KIAS With one engine inoperative
Page 2 - 4 Rev. 8 15-Dec-2017
with the landing gear
extended.
keep airspeed above this
limit.
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DA 42 AFM Operating Limitations
Airspeed IAS Remarks
v
NO
Max. structural cruising speed 155 KIAS Do not exceed this speed
except in smooth air, and
then only with caution.
v
NE
Never exceed speed in smooth air 194 KIAS Do not exceed this speed
in any operation.
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Operating Limitations DA 42 AFM
2.3 AIRSPEED INDICATOR MARKINGS
Marking KIAS Significance
White arc 56 - 111 KIAS Operating range with flaps fully extended.
Green arc 62 - 155 KIAS Normal operating range.
Yellow arc 155 - 194 KIAS ‘Caution range’ - “Only in smooth air”.
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.
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DA 42 AFM Operating Limitations
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
or
TAE 125-02-99 (if MÄM 42-198 is carried out)
(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:
TAE 125-01 TAE 125-02-99
(MÄM 42-198 carried out)
Minimum -30 oC -30 oC
o
Maximum +75
C +75 oC
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 liter (appr. 4.8 US qts)
Maximum : 6.0 liter (appr. 6.3 US qts)
Maximum oil consumption : 0.1 liter/hr (appr. 0.1 US qts/hr)
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Operating Limitations DA 42 AFM
i) Oil temperature:
TAE 125-01 TAE 125-02-99
(MÄM 42-198 carried out)
Minimum -32
Maximum +140 oC +140 oC
j) Gearbox temperature
Maximum : 120 °C
k) Coolant temperature:
TAE 125-01 TAE 125-02-99
Minimum -32 oC -30 oC
Maximum +105 oC +105 oC
l) Voltage
Minimum : 24.1 V
Maximum : 32.0 V
o
C -30 oC
(MÄM 42-198 carried out)
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° (low pitch)
15° (start lock position)
81° (feathered position)
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DA 42 AFM Operating Limitations
r) Approved fuel grades : see Section 2.14 - FUEL
s) Oil specification : SHELL Helix Ultra 5W-30
SHELL Helix Ultra 5W-40
AEROSHELL Oil Diesel 10W-40
AERO SHELL Oil Diesel Ultra 5W-30
t) Gearbox oil (propeller gearbox): SHELL EP 75W90 API GL-4
SHELL SPIRAX GSX 75W-80 GL-4
SHELL SPIRAX S4 G 75W-90
SHELL SPIRAX S6 GXME 75W-80 APT GL-4
Additionally, if MÄM 42-198 is incorporated:
CENTURION Gearbox Oil N1
SHELL SPIRAX S6 ATF ZM 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).
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 (TAE 125-01 engine installed)
8000 ft (TAE 125-02-99 engine installed)
w) Restart airspeed : 80 to 120 KIAS
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Operating Limitations DA 42 AFM
2.5 ENGINE INSTRUMENT MARKINGS
Engine instrument markings and their color code significance are shown in the tables
below.
If the TAE 125-01 engine is installed:
Indi-
cation
RPM -- -Oil
pressure
Oil
temp.
Coolant
temp.
Gearbox
temp.
Red
arc/bar
=
lower
prohibited
range
Yellow
arc/bar
=
caution
range
Green
arc/bar
=
normal
operating
range
up to
2300 RPM
below
1.0 bar
below
-32 °C
below
-32 °C
1.0 to 2.3 bar 2.3 to 5.2 bar 5.2 to 6.5 bar
1
125 to 140 °C
2
131 to 140 °C
1
96 to 105 °C
2
102 to 105 °C
-32 to 50 °C
-32 to 60 °C
50 to 125 °C
50 to 130 °C
60 to 96 °C
60 to 101 °C
-- -- up to 115 °C 115 to 120 °C
Yellow
arc/bar
=
caution
range
arc/bar
upper
prohibited
range
above
2300 RPM
above
6.5 bar
1
2
1
2
above
140 °C
above
105 °C
above
120 °C
Red
Load -- -- 0 to 100 % -- -Fuel
temp.
below
-30 °C
-30 to -22 °C
-30 to +4 °C
1
-22 to 70 °C
2
+5 to 69 °C
1
2
70 to 75 °C
above
75 °C
=
Ammeter -- -- up to 60 A -Volt-
meter
Fuel qty. 0 US gal --
1)
MÄM 42-101 not implemented, 2) MÄM 42-101 implemented (refer to Section 1.1)
below
24.1 V
24.1 to 25 V 25 to 30 V 30 to 32 V
0 to 25
US gal
-- –
above
60 A
above
32 V
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DA 42 AFM Operating Limitations
If the TAE 125-02-99 engine is installed (MÄM 42-198 carried out):
Indi-
cation
RPM -- -Oil
pressure
Oil
temp.
Coolant
temp.
Gearbox
temp.
Load -- -- 0 to 100 % -- -Fuel
temp.
Red
arc/bar
=
lower
prohibited
range
below
1.0 bar
below
-30 °C
below
-30 °C
-- -- up to 115 °C 115 to 120 °C
below
-30 °C
Yellow
arc/bar
=
caution
range
1.0 to 2.3 bar 2.3 to 5.8 bar 5.8 to 6.5 bar
-30 to 50 °C 50 to 130 °C 131 to 140 °C
-30 to 60 °C 60 to 101 °C 102 to 105 °C
-30 to +4 °C +5 to 69 °C 70 to 75 °C
Green
arc/bar
=
normal
operating
range
up to
2300 RPM
Yellow
arc/bar
=
caution
range
--
Red
arc/bar
upper
prohibited
range
above
2300 RPM
above
6.5 bar
above
140 °C
above
105 °C
above
120 °C
above
75 °C
=
Ammeter -- -- up to 60 A -Volt-
meter
Fuel qty. 0 US gal --
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below
24.1 V
24.1 to 25 V 25 to 30 V 30 to 32 V
0 to 25
US gal
EASA
approved
above
60 A
above
32 V
-- --
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Operating Limitations DA 42 AFM
2.6 WARNING, CAUTION AND ADVISORY ALERTS
2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000
NOTE
The alerts described in the following are displayed on the
Garmin G1000. Section 7.10.3 - WARNING, CAUTION AND
ADVISORY MESSAGES includes a detailed description of
the alerts.
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)
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).
L/R 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).
Meaning / Cause
L/R ENG FIRE Left / Right engine fire detected.
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DA 42 AFM Operating Limitations
Warning Alerts
(red)
L/R STARTER Left / Right engine starter is engaged.
DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed
and locked.
POSN ERROR G1000 will no longer provide GPS based navigational guidance.
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 re ceiving altitude input from the air data
computer.
VERT SPEED
FAIL
HDG The display system is not receiving valid heading input from the
The display system is not receiving vertical speed input from the
air data computer.
AHRS.
Meaning / Cause
WARN RAIM position warning. The nav deviation bar is removed.
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Operating Limitations DA 42 AFM
Color and Significance of the Caution Alerts on the G1000
Caution Alerts
(amber)
* A fault has occurred in the left/right engine ECU A (one reset
of minor faults is possible)
L/R ECU A FAIL
L/R ECU B FAIL
L/R FUEL LOW Left / Right main tank fuel quantity is low.
L/R ALTN FAIL Left / Right engine alternator has failed.
L/R VOLTS LOW Left / Right bus voltage is less than 25 Volts.
or
* ECU A is being tested during FADEC-test procedure during
the 'before take-off check'.
* A fault has occurred in the left/right engine ECU B (one reset
of minor faults is possible)
or
* ECU B is being tested during FADEC-test procedure during
the 'before take-off check'.
Meaning / Cause
L/R COOL LVL Left / Right engine coolant level is low.
PITOT FAIL Pitot heat has failed.
PITOT HT OFF Pitot heat is OFF.
STAL HT FAIL Stall warning heat has failed.
STAL HT OFF Stall warning heat is OFF.
STICK LIMIT Control stick limiting system (variable elevator stop) has failed.
INTEG RAIM not
available
AHRS ALIGN:
Keep Wings
Level
L/R AUX FUEL E Left / Right auxiliary fuel tank empty (if installed).
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RAIM (Receiver Autonomous Integrity Monitor) is not available.
The AHRS (Attitude and Heading Reference System) is aligning.
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DA 42 AFM Operating Limitations
Caution Alerts
(amber)
CHECK GEAR
(if installed)
Color and Significance of the Advisory Alerts on the G1000
Advisory Alerts
(white)
L/R GLOW ON Left / Right engine glow plug active.
L/R FUEL XFER Fuel transfer from auxiliary to main tank is in progress.
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.
Landing gear is not down and locked.
Meaning / Cause
Meaning / Cause
2.6.2 OTHER WARNING ALERTS
Warning Alerts on the Instrument Panel
GEAR UNSAFE
WARNING LIGHT
(red)
Audible Warning Alerts
GEAR
RETRACTED
CHIME TONE
(repeating)
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Illuminates if the landing gear is neither in the final up nor in
the down & locked position.
Resounds if the landing gear is retracted while the flaps
move into position LDG or when the power lever is placed in
a position below approx. 20%.
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Operating Limitations DA 42 AFM
2.7 MASS (WEIGHT)
Value Mass (Weight)
Minimum flight mass 1250 kg 2756 lb
Maximum take-off
mass
Maximum zero fuel mass 1650 kg 3638 lb
Maximum zero fuel mass,
if OÄM 42-188 is carried out (see Note below)
Maximum zero fuel mass,
if OÄM 42-188 and OÄM 42-195 are carried out
(see Note below)
Maximum landing mass (see NOTE below) 1700 kg 3748 lb
Maximum landing mass,
if OÄM 42-195 is carried out
Max. load in nose baggage compartment
(in fuselage nose)
Max. load in cabin baggage compartment
(behind rear seats)
Max. load in baggage extension
(behind cabin baggage compartment)
MÄM 42-088 not carried out 1700 kg 3748 lb
MÄM 42-088 carried out 1785 kg 3935 lb
1674 kg 3690 lb
1730 kg 3814 lb
1785 kg 3935 lb
30 kg 66 lb
45 kg 100 lb
18 kg 40 lb
Max. load, cabin baggage compartment and baggage
extension together
WARNING
Exceeding the mass limits will lead to overstressing of the
airplane as well as to degradation of flight characteristics and
flight performance.
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45 kg 100 lb
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DA 42 AFM Operating Limitations
NOTE
In some countries the beginning of a flight is defined by
starting the powerplant. In those countries a ramp mass of
maximal MTOM + 8 kg (MTOM + 18 lb) is approved. At the
time of lift-off the maximum permitted take-off mass must not
be exceeded.
NOTE
If MÄM 42-088 is carried out and OÄM 42-195 is not carried
out, a landing with a mass between 1700 kg (3748 lb) and
1785 kg (3935 lb) constitutes an abnormal operating
procedure.
NOTE
For a zero fuel mass above 1650 kg (3638 lb) a structural
temperature limit has been established which must be
observed before flight.
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Operating Limitations DA 42 AFM
2.8 CENTER OF GRAVITY
Datum Plane
The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and
in front of the airplane as seen from the direction of flight. The airplane*s longitudinal axis
is parallel with the floor of the nose baggage compartment. 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.
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DA 42 AFM Operating Limitations
2.9 APPROVED MANEUVERS
The airplane is certified in the Normal Category in accordance with JAR-23.
Approved Maneuvers
1) All normal flight maneuvers;
2) Stalling (with the exception of dynamic stalling); and
3) Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which
an angle of bank of not more than 60° 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.
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Operating Limitations DA 42 AFM
2.10 MANEUVERING LOAD FACTORS
NOTE
The tables below show structural limitations. The load factor
limits for the TAE 125 engine must also be observed. Refer
to the corresponding Operation & Maintenance Manual for
the engine.
CAUTION
Avoid extended negative g-loads duration. Extended negative
g-loads can cause propeller control problems and engine
surging.
at v
A
Positive 3.8 3.8 2.0
Negative -1.52 0
at v
NE
With Flaps in APP
or LDG Position
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
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DA 42 AFM Operating Limitations
2.11 OPERATING ALTITUDE
The maximum operating altitude is 18,000 ft (5,486 m) pressure altitude.
2.12 FLIGHT CREW
Minimum crew : 1 (one person)
Maximum number of occupants : 4 (four persons)
2.13 KINDS OF OPERATION
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
(NVFR)
• 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.
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Operating Limitations DA 42 AFM
NOTE
Many of the items of minimum equipment listed in the
following table are integrated in the G1000.
Minimum Operational Equipment (Serviceable)
Flight
and
Navigation
Instruments
For Daytime VFR
Flights
* Airspeed indicator
(on G1000 PFD or
backup)
* Altimeter (on G1000
PFD or backup)
* Magnetic compass
* 1 Headset, used by
pilot in command
In Addition
for Night VFR Flights
* Vertical speed
indicator (VSI)
* Attitude gyro
(artificial horizon);
(on G1000 PFD
or backup)
* Turn & bank
indicator
(on G1000 PFD)
* Directional gyro
* VHF radio (COM)
with speaker and
microphone
* Chronometer with
indication of hours,
minutes, and
seconds
In addition
for IFR Flights
* 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)
* VOR receiver
* Transponder
(XPDR), Mode A
and Mode C
* GPS receiver (part
of G1000)
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DA 42 AFM Operating Limitations
Minimum Operational Equipment (Serviceable)
For Daytime VFR
Flights
Engine
Instruments
Lighting * Position lights
* 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
* Strobe lights (anti
In Addition
for Night VFR Flights
collision lights)
In addition
for IFR Flights
* Landing light
* Instrument lighting
* Flood light
* Flashlight
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Operating Limitations DA 42 AFM
Minimum Operational Equipment (Serviceable)
Other
Operational
Minimum
Equipment
For Daytime VFR
Flights
* 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
* Alternate static
In Addition
for Night VFR Flights
* Emergency battery
system
valve
NOTE
A list of approved equipment can be found in Chapter 6.
In addition
for IFR Flights
(for backup attitude
gyro and flood light)
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DA 42 AFM Operating Limitations
2.14 FUEL
Approved Fuel Grades:
JET Fuel: JET A-1 (ASTM D 1655),
JET A (ASTM D 1655),
JET Fuel No. 3 (GB6537-94),
JET Fuel No. 3 (China, GB 6537-2006),
JP-8 (MIL-DTL-83133)
Additionally, if MÄM 42-198 is incorporated:
TS-1 (GOST 10227-86),
TS-1 (Ukraine GSTU 320.00 1U9943011-99),
and blends of the above listed Jet Fuel grades.
Diesel Fuel:
Only if MÄM 42-037 is incorporated: Diesel (EN 590)
and blends of the above listed Jet Fuel grades,
and Diesel.
CAUTION
Limitations for DA 42 registered and/or operated in the
following countries:
Indonesia, Malaysia: Use of Diesel Fuel is NOT approved.
CAUTION
If the airplane is operated with Diesel Fuel or a blend of Diesel
Fuel with Jet Fuel, the use of the auxiliary tanks, if installed
(OÄM 42-056), is not permitted.
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Operating Limitations DA 42 AFM
CAUTION
Additional temperature limitations must be observed if the
airplane is operated with Diesel Fuel or blends of Diesel Fuel
with Jet Fuel. Refer to Section 2.16.1.
NOTE
Use only uncontaminated fuel from reliable sources.
Main Tanks
US gal liter US gal liter US gal liter
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
Auxiliary Tanks
(if installed)
Total
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DA 42 AFM Operating Limitations
2.15 LIMITATION PLACARDS
All limitation placards are shown below. A list of all placards is included in the Airplane
Maintenance Manual (Doc. No. 7.02.01), Chapter 11.
On the Instrument Panel:
MÄM 42-088 or
OÄM 42-054 or
both
incorporated:
Neither
MÄM 42-088 nor
OÄM 42-054
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:
V
= 126 KIAS (ABOVE 1542 KG / 3400 LB)
A
V
= 120 KIAS (UP TO 1542 KG / 3400 LB)
A
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:
V
= 124 KIAS (ABOVE 1468 UP TO 1700 KG / ABOVE 3236 UP TO 3748 LB)
A
V
= 121 KIAS (1250 TO 1468 KG / 2756 TO 3236 LB)
A
LANDING GEAR
v
LE / vLOE
v
= 194 KIAS
= 156 KIAS
LOR
On the Emergency Landing Gear Extension Lever:
EMERGENCY
Gear Extension
Max. 156 KIAS
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On the Instrument Panel, Next to the Fuel Quantity Indication:
(a) Standard Tank: (b) Auxiliary Tank (if installed):
max. usable
fuel: 2 x 25 US gal
max. difference LH/RH
tank 5 US gal
If MÄM 42-037 Is Carried Out, on the Garmin G1000 MFD Next to the Fuel
Temperature Indication:
Diesel Fuel or
Unknown Fuel Blend:
Below -5 °C:
No engine start permitted.
Below +5 °C:
No take-off permitted.
(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):
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
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In Each Cowling, on the Door for the Oil Filler Neck:
OIL
Shell Helix Ultra
5W-30
or see AFM
Next to the Flap Selector Switch:
Flaps
UP
APP
137 KIAS
In the Cabin, on the Left Fuselage Sidewall:
LDG
111 KIA S
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Next to the Cabin Baggage Compartment:
In the Nose Baggage Compartment:
Max. Baggage:
30 kg [66 lb]
Beside the Door Locking Device Installed in the Passengers* Door:
EMERGENCY EXIT:
The keylock must be
unlocked during flight
On the Right-Hand Side of the Instrument Panel Above the Circuit Breakers:
______
NO SMOKING
______
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2.16 OTHER LIMITATIONS
2.16.1 FUEL TEMPERATURE
JET Fuel grades and blends thereof:
from -30 °C to +75 °C (from -22 °F to +167 °F)
NOTE
Operation with Diesel Fuel, or blends of Diesel Fuel with Jet
Fuel, is only approved when MÄM 42-037 is incorporated.
Diesel Fuel, Blends of Diesel Fuel with Jet Fuel, 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.
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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 CRTs
- 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.
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2.16.6 GARMIN G1000 AVIONICS SYSTEM
1. The Garmin G1000 Cockpit Reference Guide, P/N 190-00406-( ), latest effective issue'
must be immediately available to the flight crew.
2. If MÄM 42-101 has been implemented (refer to Section 1.1), the G1000 must utilize
the software Garmin P/N: 010-00370-11, or later approved software in accordance
with the Mandatory Service Bulletin DAI MSB 42-008, latest version.
3. If MÄM 42-198 (TAE 125-02-99 engines, refer to Section 1.1) is implemented, the
G1000 must utilize the software Garmin P/N 010-00370-15, or later approved software
in accordance with the Mandatory Service Bulletin DAI MSB42-008, latest version.
Software Part Number
System
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
Approved
Version
for approved version see DAI MSB 42-008, latest
version
Function
006-D0159-( ) GRS1 MV DB
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Operating Limitations DA 42 AFM
Software Part Number
006-D0202-( )
006-B0261-( ) GDC1-GIA1
006-B0081-( ) COM1, COM2
006-B0083-( ) GS1, GS2
006-B0082-( ) NAV1, NAV2
Approved
Version
for approved
version see
DAI MSB
42-008, latest
version
Function
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".
4. 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 way point for accuracy by reference to current approved data.
5. 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.
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(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.
(c) Use of the G1000 VOR/ILS receiver to fly approaches not approved for GPS
require VOR/ILS navigation data to be present on the display.
(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.
6. 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")
(c) POSITION : deg-min (sets navigation grid units to decimal minutes)
NOTE
Navigation Information is referenced to WGS-84 reference
system, and should only be used where the Aeronautical
Information Publication (including electronic data and
aeronautical charts) conforms to WGS-84 or equivalent.
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7. When AHRS is required to meet the items listed in the minimum operational equipment
(serviceable) table in Section 2.13 - KINDS OF OPERATION, operation is prohibited
in the following areas:
(a) North of 72° N latitude at all longitudes.
(b) South of 70° S latitude at all longitudes.
(c) North of 65° N latitude between longitude 75° W and 120° W (Northern Canada).
(d) North of 70° N latitude between longitude 70° W and 128° W (Northern Canada).
(e) North of 70° N latitude between longitude 85° E and 114° E (Northern Russia).
(f) South of 55° S latitude between longitude 120° E and 165° E (Region south
of Australia and New Zealand).
When day VFR operations are conducted in the above areas, the MFD must be in
a non-Heading Up orientation.
8. 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.
9. 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.
10. The pilot*s altimeter is the primary altitude reference during all operations using
advisory vertical navigation (VNAV) information and the autopilot. A flight altitude
selected via the autopilot must be verified and corrected according to the indication
of the calibrated altimeter.
11. The availability of Safe Taxi®, ChartView, or FliteCharts® in electronic form on the
G1000 is for information purposes only, it is still mandatory to carry another source
of charts on-board the airplane.
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DA 42 AFM Operating Limitations
2.16.7 SMOKING
Smoking in the airplane is not permitted.
2.16.8 GROUND OPERATION
Take-off and landing has been demonstrated on hard paved surfaces (asphalt, concrete,
etc.) and grass runways.
2.16.9 USE OF THE SUN VISORS
The sun visors (if installed, OÄM 42-101 or OÄM 42-142) may only be used during cruise.
During all other phases of flight the sun visors must be locked in the fully upward position.
2.16.10 STRUCTURAL TEMPERATURE
CAUTION
The max. zero fuel mass of 1650 kg (3638 lb) may only
be exceeded if OÄM 42-188 is carried out.
If the zero fuel mass exceeds 1650 kg (3638 lb) the maximum permissible structural
temperature of 55 °C (131 °F) must not be exceeded before flight. Temperature indicators
in the LH and RH landing gear bays indicate the structural temperature.
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2.16.11 GARMIN GWX 68 WEATHER RADAR OPERATION
WARNING
The Garmin GWX 68 Weather Radar System (if installed)
must not be operated on ground. If the system is transmitting,
it may result in bodily injury if persons are within the minimum
safe distance of 2.8 m (9.16 ft). Never operate the radar in
a hangar or other enclosure as radiation can be reflected
throughout the area.
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DA 42 AFM
3.1 INTRODUCTION .......................................3-4
3.2 AIRPLANE-RELATED G1000 WARNINGS ...................3-6
Emergency
Procedures
CHAPTER 3
EMERGENCY PROCEDURES
Page
3.1.1 GENERAL........................................3-4
3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES ..............3-5
3.1.3 SELECTING EMERGENCY FREQUENCY ..............3-5
3.2.1 WARNINGS / GENERAL ............................3-6
3.2.2 L/R ENG TEMP....................................3-6
3.2.3 L/R OIL TEMP ....................................3-8
3.2.4 L/R OIL PRES.....................................3-9
3.2.5 L/R GBOX TEMP .................................3-10
3.2.6 L/R FUEL TEMP..................................3-11
3.2.7 L/R ALTN AMPS..................................3-12
3.2.8 L/R ENG FIRE ...................................3-12
3.2.9 L/R STARTER....................................3-13
3.2.10 DOOR OPEN....................................3-13
3.3 G1000 SYSTEM WARNINGS .............................3-14
3.3.1 RED X..........................................3-14
3.3.2 POSN ERROR ...................................3-14
3.3.3 ATTITUDE FAIL ..................................3-14
3.3.4 AIRSPEED FAIL ..................................3-14
3.3.5 ALTITUDE FAIL ..................................3-15
3.3.6 VERT SPEED FAIL ................................3-15
3.3.7 HDG ...........................................3-15
3.3.8 WARN..........................................3-15
3.4 G1000 FAILURES ......................................3-16
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3.5 ONE ENGINE INOPERATIVE PROCEDURES ............... 3-21
DA 42 AFM
3.4.1 NAVIGATION INFORMATION FAILURE .............. 3-16
3.4.2 PFD OR MFD DISPLAY FAILURE ................... 3-16
3.4.3 AHRS FAILURE ................................. 3-17
3.4.4 AIR DATA COMPUTER (ADC) FAILURE .............. 3-18
3.4.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS
.............................................. 3-19
3.4.6 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS
.............................................. 3-20
3.5.1 DETECTING THE INOPERATIVE ENGINE ............ 3-21
3.5.2 ENGINE TROUBLESHOOTING ..................... 3-22
3.5.3 ENGINE SECURING (FEATHERING) PROCEDURE .... 3-24
3.5.4 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT
.............................................. 3-25
3.5.5 ENGINE FAILURE DURING TAKE-OFF ............... 3-33
3.5.6 ENGINE FAILURES IN FLIGHT ..................... 3-36
3.5.7 LANDING WITH ONE ENGINE INOPERATIVE ......... 3-39
3.5.8 GO-AROUND / BALKED LANDING WITH ONE ENGINE
INOPERATIVE .................................. 3-42
3.5.9 FLIGHT WITH ONE ENGINE INOPERATIVE........... 3-45
3.6 LANDING GEAR SYSTEM FAILURES ..................... 3-46
3.6.1 LANDING GEAR UNSAFE WARNING ................ 3-46
3.6.2 MANUAL EXTENSION OF THE LANDING GEAR ....... 3-48
3.6.3 LANDING WITH GEAR UP......................... 3-50
3.6.4 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING
GEAR......................................... 3-51
3.6.5 LANDING WITH DEFECTIVE BRAKES ............... 3-52
3.7 FAILURES IN THE ELECTRICAL SYSTEM ................. 3-53
3.7.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . 3-53
3.7.2 HIGH CURRENT ................................. 3-54
3.7.3 STARTER MALFUNCTION ......................... 3-54
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DA 42 AFM
3.8 SMOKE AND FIRE.....................................3-55
3.9 OTHER EMERGENCIES ................................3-59
Emergency
Procedures
3.8.1 ENGINE FIRE ON GROUND ........................3-55
3.8.2 ENGINE FIRE DURING TAKE-OFF ...................3-56
3.8.3 ENGINE FIRE IN FLIGHT...........................3-56
3.8.4 ELECTRICAL FIRE ON GROUND ....................3-57
3.8.5 ELECTRICAL FIRE IN FLIGHT ......................3-58
3.9.1 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE
CABIN .........................................3-59
3.9.2 UNLOCKED DOORS ..............................3-60
3.9.3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM . . 3-62
3.9.4 UNINTENTIONAL FLIGHT INTO ICING................3-64
3.9.5 FUEL SUPPLY FAILURE ...........................3-65
3.9.6 RECOVERY FROM AN UNINTENTIONAL SPIN .........3-66
3.9.7 EMERGENCY DESCENT...........................3-67
3.9.8 EMERGENCY EXIT ...............................3-67
NOTE
Procedures for uncritical system faults are given in Chapter
4B - ABNORMAL OPERATING PROCEDURES.
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DA 42 AFM
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.
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DA 42 AFM
Emergency
Procedures
3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES
Event Airspeed
One engine inoperative minimum control speed (air) v
One engine inoperative speed for best rate of climb v
mCA
YSE
68 KIAS
82 KIAS
3.1.3 SELECTING EMERGENCY FREQUENCY
In an in-flight emergency, depressing and holding the Com transfer button ȼ 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.
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DA 42 AFM
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
Coolant temperatures above the limit value of 105 °C can lead to a total loss of power
due to engine failure.
- 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.
Left / Right engine coolant temperature is in the upper
red range (too high / above 105 °C).
CONTINUED
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DA 42 AFM
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
Emergency
Procedures
precautionary landing on the nearest suitable airfield. Prepare
for an engine failure in accordance with 3.5.6 - ENGINE
FAILURES IN FLIGHT.
END OF CHECKLIST
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.
END OF CHECKLIST
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3.2.3 L/R OIL TEMP
DA 42 AFM
L/R OIL TEMP
Oil temperatures above the limit value of 140 °C can lead to a total loss of power due
to engine failure.
- 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.
Left / Right engine oil temperature is in the upper red
range (too high / above 140 °C).
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.
CONTINUED
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DA 42 AFM
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.
END OF CHECKLIST
Emergency
Procedures
CAUTION
3.2.4 L/R OIL PRES
L/R OIL PRES
Oil pressures below the limit value of 1 bar can lead to a total loss of power due to engine
failure.
- Reduce power on affected engine.
- Expect loss of oil.
Left / Right engine oil pressure is in the lower red
range (too low / below 1 bar).
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
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3.2.5 L/R GBOX TEMP
DA 42 AFM
L/R GBOX TEMP
Gearbox temperatures above the limit value of 120 °C can lead to a total loss of power
due to engine failure.
- Reduce power on affected engine.
- Increase airspeed.
Left / Right engine gearbox temperature is in the upper
red range (too high / above 120 °C).
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
precautionary landing on the nearest suitable airfield. Prepare
for an engine failure in accordance with 3.5.6 - ENGINE
FAILURES IN FLIGHT.
END OF CHECKLIST
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DA 42 AFM
3.2.6 L/R FUEL TEMP
Emergency
Procedures
L/R FUEL TEMP
Fuel temperatures above the limit value of 75 °C can lead to a noticeable reduction of
the high pressure pump efficiency.
- Reduce power on affected engine.
- Increase airspeed.
Left / Right fuel temperature is in the upper red range
(too high / above 75 °C).
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.
END OF CHECKLIST
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3.2.7 L/R ALTN AMPS
DA 42 AFM
L/R ALTN AMPS
Proceed according to:
3.7.2 - HIGH CURRENT
3.2.8 L/R ENG FIRE
L/R ENG FIRE
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:
Left / Right engine alternator output is in the upper red
range (too high / above 60 amps).
Left / Right engine fire detected.
3.8.1 - ENGINE FIRE ON GROUND
3.8.2 - ENGINE FIRE DURING TAKE-OFF
3.8.3 - ENGINE FIRE IN FLIGHT
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DA 42 AFM
3.2.9 L/R STARTER
Emergency
Procedures
L/R STARTER
Proceed according to:
3.7.3 - STARTER MALFUNCTION
3.2.10 DOOR OPEN
DOOR OPEN
Proceed according to:
3.9.2 - UNLOCKED DOORS
Left / Right engine starter is engaged.
Front and/or rear canopy and/or baggage door are/is
not closed and locked.
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Emergency
Procedures
DA 42 AFM
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
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
Revert to the standby attitude indicator.
3.3.4 AIRSPEED FAIL
The system will flag and no longer provide GPS based
navigational guidance.
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.
AIRSPEED FAIL
Revert to the standby airspeed indicator.
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The display system is not receiving airspeed input from
the air data computer; accompanied by a red X through
the airspeed display.
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DA 42 AFM
3.3.5 ALTITUDE FAIL
Emergency
Procedures
ALTITUDE FAIL
Revert to the standby altimeter.
3.3.6 VERT SPEED FAIL
VERT SPEED FAIL
Determine vertical speed based on the change of altitude information.
3.3.7 HDG
The display system is not receiving altitude input from the
air data computer; accompanied by a red X through the
altimeter display.
The display system is not receiving vertical speed input
from the air data computer; accompanied by a red X
through the vertical speed display.
HDG
Revert to the emergency compass.
3.3.8 WARN
WARN
1. CDI softkey.......................... switch to VOR/LOC
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The display system is not receiving valid heading input
from the AHRS; accompanied by a red X through the
digital heading display.
RAIM position warning - nav deviation bar removed.
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Emergency
Procedures
DA 42 AFM
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
Automatic Entry of Display Reversionary Mode
- If the PFD and MFD have automatically entered reversionary mode, use the following
procedure.
(a) DISPLAY BACKUP Button on Audio Panel . . PUSH (Button will be OUT)
NOTE
After automatic entry of reversionary mode, the pilot must
press the DISPLAY BACKUP button on the audio panel. After
the DISPLAY BACKUP button has been pushed, the system
will remain in reversionary mode even if the problem causing
the automatic entry of reversionary mode is resolved. A
maximum of one attempt to return to normal mode is
approved using the following procedure.
CONTINUED
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