Robin DR400 Series, DR400/140B, DR400/120D, DR400/200R, DR400/180R Pilot Operating Handbook

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Page 1

PILOT’S OPERATING HANDBOOK

SUPPLEMENT

DR400/135CDI

Document n° 1001639GB

Page 2

Page 3

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Pilot´s Operating Handbook

Supplement

for the

DR400/120D DR400/140B DR400/180R DR400/200R

DR400/RP

Equipped with TAE 125 Installation

TYPE ................................ DR 400

MODEL No. ......................

SERIAL No. ......................

This supplement must be attached to the EASA approved Pilot´s Operating Handbook of the DR400/120D, DR400/140B, DR400/180R, DR400/200R or DR400/RP when the TAE 125-01 or TAE 125-02-99 installation has been installed in accordance with EASA.A.S.01380 or EASA STC 10014219.

The information contained in this supplement supersedes or adds to the information published in the EASA approved Pilot´s Operating Handbook only as set forth herein.

For limitations, procedures, performance and loading information not contained in this supplement, consult the EASA approved Pilot´s Operating Handbook.

This supplement Pilot‘s Operating Handbook is approved with EASA

STC 10014219.

Doc.Nr.: 1001639GB

Issue 3 – July 2014 Page i

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Page - ii Issue 3 - July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Issue/ Rev.

Section

Description Approval

D at

Endorsed

2/1

New fuel, new gearbox oil

M ar

c h 1 6 2 0

Revision No. 1 to AFM

supplement ref 60-0310-

60022 is approved under

the authority of DOA ref.

EASA.21J.010.

Date: March 16 ,2012

Office of Airworthiness

Procedures updated

3/0

all

Change of TC holder Initial issue C.E.A.P.R Numbering of CEAPR

documents

y 2 0

EASA STC 10014219

transfer

APPROVAL

Issue 2: The content of approved sections is approved by EASA. All other content

is approved by TAE under the authority of EASA DOA No. EASA.21J.010 in accordance with Part 21.

Issue 3: The content of approved sections is approved by EASA, transfer of STC

10014219. C.E.A.P.R is TC holder.

LOG OF REVISIONS

The parts of the text which changed are marked with a vertical line on the margin of the page.

Issue 3 – July 2014 Page iii

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Section

Issue/ Revision

Date

3/0

July 2014

3/0

July 2014

3/0

July 2014

3/0

July 2014

3/0

July 2014

3/0

July 2014

3/0

July 2014

3/0

July 2014

LIST OF EFFECTIVE SECTIONS

Page - iv Issue 3 - July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

TABLE OF CONTENTS

APPROVAL .............................................................................................. iii

LOG OF REVISIONS ............................................................................... iii

LIST OF EFFECTIVE SECTIONS ........................................................... iii

ABBREVIATIONS .................................................................................... xi

SECTION 0 GENERAL

CONVENTIONS IN THIS HANDBOOK ................................................. 0-1

FOR DR400 AIRCRAFT FROM SERIAL NUMBER 2500 AND UP ...... 0-1

UPDATE AND REVISION OF THE MANUAL ....................................... 0-1

SECTION 1 DESCRIPTION

OVERALL DIMENSIONS ...................................................................... 1-1

ENGINE ................................................................................................. 1-1

PROPELLER.......................................................................................... 1-2

NOISE LIMITATION ............................................................................... 1-2

ELECTRICAL SYSTEM ......................................................................... 1-3

FADEC-RESET ...................................................................................... 1-6

FUELS, OILS and LIQUIDS ................................................................... 1-6

ENGINE OIL........................................................................................... 1-7

FUEL SYSTEM ...................................................................................... 1-7

OPTIONAL EXTENDED RANGE TANK ............................................... 1-8

INSTRUMENT PANEL.........................................................................1-11

HEATING AND VENTILATION ............................................................1-20

Issue 3 – July 2014 Page v

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 2 LIMITATIONS

APPROVED OPERATION .................................................................... 2-1

MAXIMUM ALTITUDE........................................................................... 2-1

FLIGHT LOAD FACTOR LIMITS AT MAXIMUM WEIGHT .................. 2-2

MAXIMUM AUTHORIZED WEIGHTS .................................................. 2-2

WEIGHT AND BALANCE ..................................................................... 2-2

LOAD PLANNING ................................................................................. 2-3

ENGINE OPERATING LIMITS .............................................................. 2-3

ENGINE INSTRUMENT MARKINGS ................................................... 2-6

GROUNDING (EARTHING) BEFORE AND DURING FUELING ......... 2-6

PERMISSIBLE FUEL GRADES ............................................................ 2-7

MAXIMUM FUEL QUANTITIES ............................................................ 2-7

PERMISSIBLE OIL GRADES ............................................................... 2-7

PERMISSIBLE COOLING LIQUID ....................................................... 2-8

LOAD LIMITS ........................................................................................ 2-8

OPERATIONAL LIMITATIONS IN THE “U” CATEGORY .................... 2-8

PLACARDS ........................................................................................... 2-9

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 3 EMERGENCY PROCEDURES

ENGINE FAILURE OR LOSS OF POWER ........................................... 3-2

During takeoff roll ................................................................................... 3-2

Immediately after takeoff ....................................................................... 3-2

During flight ............................................................................................ 3-3

LANDING WITHOUT ENGINE POWER ............................................... 3-4

Restart after engine failure .................................................................... 3-5

FADEC malfunction in flight ................................................................... 3-6

ENGINE SHUT-DOWN IN FLIGHT ....................................................... 3-8

FIRE ....................................................................................................... 3-9

Engine fire on the ground, during starting ............................................. 3-9

Engine fire in flight ................................................................................ 3-9

Electrical fire ........................................................................................3-10

ROUGH ENGINE OPERATION ..........................................................3-11

Oil pressure too low .............................................................................3-11

Oil temperature too high ......................................................................3-12

Coolant temperature too high ..............................................................3-12

“Cool level” light illuminates .................................................................3-13

Gearbox temperature too high .............................................................3-13

Fuel temperature too low .....................................................................3-13

Propeller RPM too high ........................................................................3-14

Fluctuations in propeller RPM ..............................................................3-14

ICING ...................................................................................................3-14

ELECTRICAL POWER SUPPLY MALFUNCTION .............................3-16

If the “ALT” light is lit or the ammeter shows battery discharge during

normal engine operation for more than 5 minutes ...............................3-17

INADVERTENT SPIN ..........................................................................3-18

LOSS OF ELEVATOR CONTROL ......................................................3-18

Issue 3 – July 2014 Page vii

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 4 NORMAL PROCEDURES

NORMAL OPERATING SPEEDS ......................................................... 4-1

Best rate of climb speed ........................................................................ 4-1

Maximum operating speed in turbulent air ............................................ 4-1

Never Exceed speed ............................................................................. 4-1

Maximum speed .................................................................................... 4-1

Landing speed, final approach .............................................................. 4-1

PRE-FLIGHT INSPECTION .................................................................. 4-2

CABIN INTERIOR CHECK BEFORE START-UP ................................ 4-5

STARTING THE ENGINE ..................................................................... 4-6

AFTER ENGINE START ....................................................................... 4-7

FADEC BACKUP BATTERY TEST ...................................................... 4-7

WARM UP ............................................................................................. 4-8

TAXIING ................................................................................................ 4-8

BEFORE TAKEOFF .............................................................................. 4-8

TAKEOFF ............................................................................................ 4-11

Short takeoff ....................................................................................... 4-11

Crosswind takeoff ................................................................................ 4-11

CLIMB .................................................................................................. 4-12

Normal climb (flaps up) ....................................................................... 4-12

CRUISE ............................................................................................... 4-12

DESCENT ........................................................................................... 4-13

Approach or downwind ........................................................................ 4-13

Final ..................................................................................................... 4-13

LANDING ............................................................................................. 4-14

Short landing ....................................................................................... 4-14

Overshoot procedure........................................................................... 4-14

AFTER LANDING ................................................................................ 4-14

ENGINE SHUT-DOWN ....................................................................... 4-14

After the engine stops ......................................................................... 4-14

PARKING BRAKE USE ...................................................................... 4-15

Brake on .............................................................................................. 4-15

Brake off .............................................................................................. 4-15

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 5 PERFORMANCE

AIRSPEED INSTALLATION CALIBARTION ......................................... 5-1

STALL SPEEDS .................................................................................... 5-1

TAKEOFF PERFORMANCE ................................................................. 5-2

Takeoff distance, 1100 kg ...................................................................... 5-3

Takeoff distance, 1000 kg ...................................................................... 5-4

CLIMB PERFORMANCE ....................................................................... 5-5

Climb speeds ......................................................................................... 5-5

Rate of climb, Flaps retracted, 1100 kg ................................................. 5-6

Rate of climb, Flaps retracted, 1000 kg ................................................. 5-7

Time, fuel and distance to climb, Flaps retracted, 1100kg .................... 5-8

Time, fuel and distance to climb, Flaps retracted, 1000kg .................... 5-9

Maximum angle of climb in takeoff position .........................................5-10

Glide performance ...............................................................................5-10

CRUISE PERFORMANCE ..................................................................5-11

At maximum take-off weight, 1100 kg .................................................5-12

At take-off weight 980 kg .....................................................................5-15

LANDING PERFORMANCE ................................................................5-18

SECTION 6 WEIGHT AND BALANCE

USE OF WEIGHT AND BALANCE DIAGRAM ..................................... 6-3

Example of loading problem (dashed line on the diagram) ................... 6-3

SECTION 7 SUPPLEMENTS

No supplements

Issue 3 – July 2014 Page ix

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Page -x Issue 3 - July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

ABBREVIATIONS

TAE Thielert Aircraft Engines GmbH, developing and

manufacturing company of the Centurion 2.0 S engine, (since

July 2013, Technify Motors GmbH). FADEC Full Authority Digital Engine Control CED 125 Compact Engine Display. Multifunctional instrument for

indication of engine data of the TAE 125-01 and TAE 125-02-

99 engine.

Issue 3 – July 2014 Page xi

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 0

GENERAL

CONVENTION IN THIS HANDBOOK

This manual contains the following convention and warnings. They should be strictly followed to rule out personal injury, property damage, and impairment to the aircraft´s operating safety or damage to it as a result of improper functioning.

▲ WARNING: Non-compliance with these safety rules could lead to

injury or even death.

 CAUTION: Non-compliance with these special notes

and safety measures could cause damage to the engine or to the other components.

 Note: Information added for a better understanding of an

instruction.

FOR DR400 AIRCRAFT FROM SERIAL NUMBER 2500 AND UP

This supplement is valid if the TAE 125-01 or TAE 125-02-99 aircraft engine is installed.

UPDATE AND REVISION OF THE MANUAL

▲ WARNING: A safe operation is only assured with an up to date POH

supplement.

 Note: The document number of this POH supplement is

published on the cover sheet of this supplement.

Issue 3 – July 2014 Page 0 - 1

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Page 0 - 2 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 1

DESCRIPTION

OVERALL DIMENSIONS

Wing span ................................................................ (28 ft 7.3 in) 8.72 m

Overall length ...............................................................(23 ft 8 in) 7.20 m

Overall height ........................................................... (7 ft 3.79 in) 2.23 m

Propeller ground clearance ............................................... (9.5 in) 0.26 m

ENGINE

Engine manufacturer ........................................... Technify Motors GmbH

Engine models ........................................ TAE 125-01 or TAE 125-02-99

The TAE 125-02-99 is the successor of the TAE 125-01. Both engine variants have the same power output and the same propeller speeds but different displacement. While the TAE 125-01 has 1689 ccm, the TAE 125-02-99 has 1991 ccm. Both engine variants are liquid cooled in-line four-stroke 4-cylinder engines with DOHC (double overhead camshaft) and are direct Diesel injection engines with common-rail technology and turbocharging. Both engine variants are controlled by a FADEC system. The propeller is driven by a built-in gearbox (i = 1.69) with mechanical vibration damping and overload release. The engine variants have an electrical self-starter and an alternator.

▲ WARNING: The engine requires an electrical power source for

operation. If the main battery and alternator fail simultaneously, the engine will operate for a very limited time on FADEC backup battery power (TAE 125-02-99 installation). Therefore, it is important to pay attention to indications of alternator failure.

Issue 3 – July 2014 Page 1 - 1

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Due to the specific characteristic of the TAE 125 engine, all of the information from the original DR400 flight manual recognized by EASA are no longer valid with the reference to:

 carburetor and carburetor pre-heating,  ignition magnetos and spark plugs, and  mixture control and priming system.

PROPELLER

Manufacturer ....................................... MT Propeller Entwicklung GmbH

Model ........................................................................... MTV-6-A/187-129

Number of blades ................................................................................... 3

Diameter ......................................................................................... 1.87m

Type ................................................................................ Constant Speed

NOISE LIMITATION

In compliance with the regulation ICAO, annex 16, Volume I, Part II, Chapter X, the maximum acceptable noise level for the DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP at a certified max. take-off weight of 980 kg (2161 lb) is 78.4 dB(A).

For the TAE 125-01 installation: The noise level determined under the conditions of the abovementioned regulation, with the MT Propeller MTV-6-A/187-129 propeller together with "Akrapovic type for TAE 125" muffler, is 70.9 dB(A).

The noise level determined under the conditions of the abovementioned regulation, with the MT Propeller MTV-6-A/187-129 propeller together with no installed muffler, is 74.4 dB(A).

For the TAE 125-02-99 installation: The noise level determined under the conditions of the abovementioned regulation, with the MT Propeller MTV-6-A/187-129 propeller together with "Akrapovic type for TAE 125" muffler, is 70.2 dB(A).

The noise level determined under the conditions of the abovementioned regulation, with the MT Propeller MTV-6-A/187-129 propeller together with “Langer LA 44” muffler, is 69.1 dB(A).

ELECTRICAL SYSTEM

The electrical system of the TAE 125 installation differs from the previous Page 1 - 2 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

installation and is equipped with the following operating and display elements:

1. Rocker Switch "Battery"

The battery must be switched ON in normal operation.

2. The circuit breaker below the Rocker Switch "Battery" disables the

alternator. The alternator can be left ON always.

3. Key Switch "Starter"

This switch controls the starter motor only.

4. Voltmeter

5. Warning lamp "Alternator".

Illuminates when the power output of the alternator is too low or the circuit breaker “Alternator” (Switch resp.) is switched off. Normally, this warning lamp always illuminates when the “Engine Master” (“IGN” resp.) is switched on without revolution and extinguished immediately after starting the engine.

6. Switch "Engine Master"

The Engine Master switch controls the two redundant FADEC components, and the back-up alternator excitation battery, with three independent contacts. It is protected against unintentional switching with a pull-to-actuate mechanism and a guard. The alternator excitation battery is used to ensure that the alternator continues to function in any circumstances even if the main battery fails.

7. Switch "FORCE B"

If the FADEC does not automatically switch from A-FADEC to the BFADEC in case of an emergency despite of obvious necessity, this switch allows to switch manually to the B-FADEC.

8. FADEC Backup Battery (TAE 125-02-99 installation)

The backup battery ensures power supply to A-FADEC only when supply from main battery and alternator is interrupted. This allows continued engine operation for limited time only.

Issue 3 – July 2014 Page 1 - 3

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

STARTER

PITOT HEAT

(optional)

ALTERNATOR

BATTERY

EXTERNAL POWER

PLUG

SWITCH TYPE CIRCUIT BREAKER

TRIP FREE CIRCUIT BREAKER

SWITCH

PUSH BUTTON

WARNING LIGHT

FADEC

PULL TO FORCE B

ENGINE MASTER

ALTERNATOR

BATTERY

TEST

START

(key)

GLOW

CED

COMPACT ENGINE DISPLAY

TEST / ACK

TURN INDICATOR

VOLTMETER

STROBE LIGHT

NAVIGATION LIGHT

TAXI LIGHT

LANDING LIGHT

ELECT. PUMP

FUEL TEMPERATURE

PITOT HEAT

DIMMERS

AVIONICS

STALL WARNING

FUEL GAUGE

ANNUNCIATOR PANEL

FUEL

TEMPERATURE

ICE ZONE

ELECTRONICS INTERNATIONAL

RDO & inst.

Cabin

Figure 1-1 Simplified block diagram

Page 1 - 4 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Figure 1-2 Simplified Block Diagram with FADEC backup battery installed

Issue 3 – July 2014 Page 1 - 5

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

FADEC-RESET

In case of a FADEC-warning, one or both FADEC warning lamps are flashing. If then the "FADEC" Test Knob is pressed for at least 2 seconds:

a) the active warning lamps will extinguish if it was a LOW category

warning.

b) the active warning lamps will be illuminated steady if it was a

HIGH category warning.

 CAUTION: If a FADEC-warning occurred, contact your

service center. Next flight is not permitted.

When a high category warning occurs the pilot should land as soon as practical, since the affected FADEC ECU has diagnosed a severe fault. A low category fault has no significant impact on engine operation. Refer also to the engine manual OM-02-01 or OM-02-02 for additional information.

FUELS, OILS and LIQUIDS

Approved fuels, oil and liquids are published in Section 2 - Limitations of this POH Supplement.

▲ WARNING: The engine must not be started if the oil or coolant level is

too low.

 CAUTION: Use of unapproved fuels, oil and coolant may result in

damage to the engine and fuel system components,

resulting in possible engine failure.

 CAUTION: Normally it is not necessary to fill the cooling liquid or

gearbox oil between maintenance intervals. If the level is

too low, please notify the service department

immediately.

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

ENGINE OIL

Oil quantity between dipstick min and max indication: .................. 1 liter

Total engine capacity including filters and coolers: .................. 6.7 liters

Approved grades: .................................. Refer to Section 2 – Limitations

 CAUTION: Use the approved oil with exact declaration only!

FUEL SYSTEM

The fuel system of the TAE 125 installation includes a variant of the original standard tank of the DR400, plus a level sender and display, and an independent low-level warning light. An additional sensor and display for fuel temperature is installed.

The fuel flows out of the tank to the Fuel Selector Valve which has positions ON and OFF.

The electrically driven fuel pump supports the fuel flow to the filter module if required. Upstream to the fuel filter module a thermostatcontrolled fuel pre-heater is installed. Then, the engine-driven feed pump and the high-pressure pump supply the rail, from where the fuel is injected into the cylinders depending upon the position of the thrust lever and regulation by the FADEC.

Surplus fuel flows to the filter module and then through the fuel selector valve back into the tank. A temperature sensor in the filter module controls the heat exchange between the fuel feed and return. Since Diesel fuel tends to form paraffin at low temperatures, the information in

Section 2 “Limitations“ pertaining to fuel temperature have to be

observed. The fuel return ensures a quicker warm up of the fuel in the tank.

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Fuel capacity

Tank

Total usable

fuel

Total unusable fuel

Total capacity

109 liters

28.7 US gal 24 imp gal

1 liter

0.26 US gal

0.22 imp gal

110 liters 29 US gal

24.2 imp gal

If Diesel fuel is used, Diesel fuel according DIN EN 590 has to be used exclusively.  Note: There are differences in the national

supplements to EN 590. Approved are Diesel fuels with

the addition DIN EN 590.

Table 1-1 Fuel Capacity

OPTIONAL EXTENDED RANGE TANK

▲ WARNING: The optional tank is only approved for Jet-A1 The total fuel capacity can be increased to 160 l / 35.2 Imp gal / 42.24

US gal (159 l / 35 Imp gal / 42 US gal usable) by installing an optional fuel tank of 50 l / 11 Imp gal / 13.2 US gal. The optional tank is located in the fuselage, aft of the rear seat. The fuel from the optional tank can be transferred into the main tank by pulling the transfer valve control, located on the instrument panel. The fuel temperature and the fuel level of the optional tank are displayed either on the triple indicator or on the quad indicator (depending on the instrument panel model) when a momentary switch is pushed (warning LED signal).

 Note: The main fuel tank must be empty enough

to receive full quantity from the optional fuel tank.

Since the optional fuel tank is not heated, it is limited to the use of JET A-1 only to prevent a potential clogging of Diesel Fuel to low temperature.

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Fuel shut-off

with fuel filter and drain-valve

Electric fuel pump,

Switch

Fire-wall

Fuel quantity

transmitter

Vent/overflow line

Filler port

Drain valve

Strainer

Power lever

Fuel

quantity

OFF

Option.fuel quantity

CED

10 12 14

FUEL

½EFUEL

3WESTACH

Fuel

low-level

Fuel

temperature

Optional

switch

Optional tank

50 litres

Engine-driven

fuel pump

FU EL FIL T E R

Excess from fuel injectors

Excess from fuel pump

ENGINE

VOLTSFUEL

EEFUEL

FUEL

WESTACH

FADEC

Figure 1-3/1 fuel system simplified diagram (Instrument panel models #1 and #2)

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Fuel shut-off

with fuel filter and drain-valve

Electric fuel pump,

Switch

Engine-driven

fuel pump

Fire-wall

Fuel quantity

transmitter

Vent/overflow line

Filler port

Drain valve

Strainer

Power lever

Fuel

quantity

OFF

Option.fuel quantity

FU EL FIL T ER

CED

Excess from fuel injectors

Excess from fuel pump

10 12

FUEL

½EFUEL

1 3WESTACH

Fuel

low-level

Fuel

temperature

Optional

switch

Optional tank

50 litres

VOLTS

FUEL

°C

OAT

FUEL

1 3

WESTACH

ENGINE

FADEC

Figure 1-2 Fuel system simplified diagram (Instrument panel model #3)

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

2 2

OPO

arC

CTG

707

070707060

Figure 1-5 Instrument panel model #1

 Note: The avionics instrument panel is shown as an example

only.

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Instrument panel model #1

Pos

Fonction

Pos

Fonction

Pos

Fonction

Airspeed indicator

Warning lights

Fuel tank valve

Gyro horizon

Lights test & day/night dimmer switch

Elevator trim control valve

Altimeter

Instrument panel light

Elevator trim position indicator

Turn coordinator

Safety switches: landing light, taxi light, strobe light, navigation light, pitot heat

Cabin heat / windshield defrost control

Directional gyro

Circuit breakers

Cabin heat

Rate of climb indicator

Electric throttle control

Instrument cut-off

Vacuum gauge

ANR jacks

VOR/LOC indicator

Engine indicator CED-125

Mike and headset jacks

Hourmeter

Parking brake control knob

Fresh air vent

Outside air temperature (OAT)

Westach triple indicator

Battery safety switch

Clock / chronometer

FADEC & alternator excitation battery

Key starter

Stall warning

Electrical fuel pump control

Glow light

Music jack

Alt. Induction air

FADEC test button

Auxiliary 12V

Force FADEC B

CED test / warning switch off

Avionics Master switch

Magnetic compass

CED-125 lighting knob

Alternator relay breaker

Table 1-2 Instrument panel #1 description

Page 1 - 12 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

2 2

POT

CTG

707

706

 Note: The avionics instrument panel is shown as an example

Figure 1-6 Instrument panel model #2

only.

Issue 3 – July 2014 Page 1 - 13

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Instrument panel model #2

Pos

Fonction

Pos

Fonction

Pos

Fonction

Airspeed indicator

Lights test & day/night dimmer switch

Elevator trim position indicator

Gyro horizon

Instrument panel light

Cabin heat / windshield defrost control

Altimeter

Safety switches: landing light, taxi light, strobe light, navigation light, pitot heat

Cabin heat

Turn coordinator

Circuit breakers

Interphone on board

Directional gyro

Electric throttle control

VOR/LOC indicator

Rate of climb indicator

ANR jacks

Hourmeter

Vacuum gauge

Mike and headset jacks

Outside air temperature (OAT)

Engine indicator CED-125

Fresh air vent

Clock / chronometer

Parking brake control knob

Battery safety switch

Instrument cut-off

Westach triple indicator

Key starter

Instrument cut-off

FADEC & alternator excitation battery

Glow light

Auxiliary 12V

Electrical fuel pump control

FADEC test button

Avionics Master switch

Alt. Induction air

CED test / warning switch off

Alternator relay breaker

Force FADEC B

CED-125 lighting knob

ELT control

Magnetic compass

Fuel tank valve

Music jack

Warning lights

Elevator trim control valve

Table 1-3 Instrument panel #2 description

Page 1 - 14 Issue 3 – July 2014

Page 31

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

7 4

CTG

707

706

 Note: The avionics instrument panel is shown as an example

only.

Figure 1-7 Instrument panel model #3

Issue 3 – July 2014 Page 1 - 15

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Instrument panel model #3

Pos

Fonction

Pos

Fonction

Pos

Fonction

Airspeed indicator

Glow light

Clock / chronometer

Gyro horizon

FADEC test button

Hourmeter

Altimeter

CED-125 lighting knob

Circuit breakers

Turn coordinator

CED test / warning switch off

Fresh air vent

Directional gyro

Electric throttle control

Avionics Master switch

Rate of climb indicator

Parking brake control knob

Avionics circuit breakers

Vacuum gauge

Elevator trim control

VOR/LOC indicator

Battery safety switch

Elevator trim position indicator

ELT (optional)

FADEC & alternator excitation battery

Fuel tank valve

Instrument cut-off

Electrical fuel pump control

Lights test & day/night dimmer switch

Instrument cut-off

Westach quad indicator

Warning lights

Auxiliary 12V

Engine indicator CED-125

Magnetic compass

ANR jacks

Alt. Induction air

Instrument panel light

Mike and headset jacks

Alternator relay breaker

Safety switches: landing light, taxi light, strobe light, navigation light, pitot heat

Music jack

Force FADEC B

Cabin heat

Transfer valve control (optional)

Key starter

Cabin heat / windshield defrost control

Tank fuel T°C & level display select push-button (optional)

Table 1-4 Instrument panel #3 description

Page 1 - 16 Issue 3 – July 2014

Page 33

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

7 4

CTG

707

07070

706

 Note: The avionics instrument panel is shown as an example

Figure 1-8 Instrument panel model #4

only.

Issue 3 – July 2014 Page 1 - 17

Page 34

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Instrument panel model #4

Pos

Fonction

Pos

Fonction

Pos

Fonction

Airspeed indicator

Glow light

Cabin heat / windshield defrost control

Gyro horizon

FADEC test button

Clock / chronometer

Altimeter

CED-125 lighting knob

Hourmeter

Turn coordinator

CED test / warning switch off

Circuit breakers

Directional gyro

Electrical throttle control

Fresh air vent

Rate of climb indicator

Parking brake control knob

Avionics Master switch

Vacuum gauge

Elevator trim control

Avionics circuit breakers

Battery safety switch

Elevator trim position indicator

VOR/LOC indicator

FADEC & alternator excitation battery

Fuel tank valve

ELT (optional)

Electrical fuel pump control

Lights test & day/night dimmer switch

Instrument cut-off

Westach quad indicator

Warning lights

Instrument cut-off

Engine indicator CED-125

Magnetic compass

Auxiliary 12V

Alt. Induction air

Instrument panel light

ANR jacks

Alternator relay breaker

Safety switches: landing light, taxi light, strobe light, navigation light, pitot heat

Mike and headset jacks

Force FADEC B

Optional tank fuel T°C qty display select.

Music jack

Table 1-5 Instrument panel #4 description

Page 1 - 18 Issue 3 – July 2014

Page 35

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

”Three-display“ and “four-display“ instruments

Example Of the Westach triple indicator installed on models #1 and #2

Compact Engine Display CED-125

Example of the Westach quad indicator installed on model #3

Figure 1-4 CED-125 detail

Issue 3 – July 2014 Page 1 - 19

Page 36

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

HEATING AND VENTILATION

1 Fresh Air Intake 2 Heat Exchanger 3 Warm Air Distribution Box 4 Warm Air Distribution Box 5 Forward / Aft Selection 6 Defrost / Heating Selection Box 7 Defrost Jet 8 Forward Heating 9 Aft Heating 10 Heating Controls

Figure 1-5 Heating and Ventilation

Page 1 - 20 Issue 3 – July 2014

Page 37

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Heating Control Settings

Function

Pulled

Pushed

Control 0

- Button Lock

Heat ON/OFF

OFF

Control 1

Heating ON/OFF

OFF

Control 2

Defrost / Heating

FRONT

HEATING

WINDSHIELD

DEFROST

Control 3

Front / Rear select.

REAR

FRONT

Table 1-6 Heating Control Settings

Figure 1-6 Heat Control Placard, Right Cabin Side Wall

This STC installation has a fourth control (Control 0 in table above). It must be OFF (Push) when cabin heat is not required (hot outside air temperature)

Issue 3 – July 2014 Page 1 - 21

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Page 1 - 22 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

AIRSPEED LIMITATIONS

km/h

Vne, never exceed

270

146

Vno, normal operation

260

140

Va, maneuvering speed

215

116

Vfe, flaps extended limit speed

170

AIRSPEED INDICATOR MARKINGS

km/h

Red line (never exceed)

Vne

270

146

Yellow arc (operate with caution and only in "smooth air")

Vno-Vne

260 - 270

140 - 146

Green arc (normal operating range)

Vs1-Vno

99 - 260

53 - 140

White arc

Vso-Vfe

87 - 170

47 - 92

APPROVED OPERATION

Table 2-1 Airspeed Limitations

SECTION 2

LIMITATIONS

Table 2-2 Airspeed Indicator Markings

MAXIMUM ALTITUDE

The DR400 with TAE 125-01 or TAE 125-02-99 engine installation has been qualified up to 16.500 ft.

Issue 3 – July 2014 Page 2 - 1

Page 40

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Cat. “U“

Cat. “N“

On Take off

2006 lb (910 kg)

2161 lb (980 kg)

On Landing

2006 lb (910 kg)

2161 lb (980 kg)

FLIGHT LOAD FACTOR LIMITS AT MAXIMUM WEIGHT

(2006 lb) 910 kg (category “U“):

Flaps up ............................................................ n between -2.2 and +4.4

Flaps down .................................................................................... n = +2

(2161 lb) 980 kg (category "N"):

Flaps up ............................................................ n between -1.9 and -3.8

Flaps down ................................................................................... n = + 2

 CAUTION: Avoid extended negative g-loads duration.

Extended negative g-loads can cause propeller control

and engine problems.

 Note: The load factor limits for the engine must

also be observed. Refer to the Operation & Maintenance

Manual for the engine.

MAXIMUM AUTHORIZED WEIGHTS

Table 2-3 Maximum Authorized Weights

WEIGHT AND BALANCE

Levelling ........................................................... upper fuselage longeron

Datum .........................................wing leading edge, rectangular section

Reference Chord ............................................................ (67.3 in) 1.71 m

Page 2 - 2 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Weight

kg (lb)

Arm

m (in)

Front Seats

2 x 77

(2 x 170)

0.36 - 0.46 (14 - 18)

Rear Seats (*)

2 x 77

(2 x 170)

1.19 (47)

Fuel, main fuselage tank

(194)

1.12 (44)

Baggage (**)

(88)

1.9

(75)

LOAD PLANNING

(Refer also to weight and balance chart, section 6) The weight of the engine oil, as well as the unusable fuel must be

included in the empty weight of the aircraft.

Table 2-4 Load Planning

* The carriage on the rear seats of more than two passengers (whose total weight remain below or equal to the maximum indicated) is authorized, provided that passenger seat belts are installed for each passenger and that weight and balance are kept within the authorized limits.

** Within the authorized weight and balance limits.

ENGINE OPERATING LIMITS

Engine manufacturer ........................................... Technify Motors GmbH

Engine model .......................................... TAE 125-01 or TAE 125-02-99

Takeoff and max. continuous power .............................. 99 kw (135 HP)

Takeoff and max. continuous RPM ................................................. 2300

 Note: In the absence of any other explicit

statements, all of the information on RPM in this supplement to the Pilot´s Operating Handbook are propeller RPM.

Issue 3 – July 2014 Page 2 - 3

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Engine operating limits for takeoff and continuous operation

▲ WARNING: It is not allowed to start the engine outside of these

temperature limits.

 Note: The operating limit temperature is a

temperature limit below which the engine may be started, but not operated at the takeoff RPM. The warm-up RPM to be selected can be found in Section 4 of this supplement.

Oil temperature:

Minimum engine starting temperature: ........................................ -32 °C

Minimum operating limit temperature: .............................................50 °C

Maximum operating limit temperature: ..........................................140 °C

Coolant temperature:

Minimum engine starting temperature: ........................................ -32 °C

Minimum operating limit temperature: .............................................60 °C

Maximum operating limit temperature: ..........................................105 °C

Gearbox temperature:

Minimum operating limit temperature: ........................................... -30 °C

Maximum operating limit temperature: ..........................................120 °C

Oil pressure:

Minimum oil pressure ................................................................... 1.2 bar

Minimum oil pressure (at take-off power)..................................... 2.3 bar

Minimum oil pressure in flight ...................................................... 2.3 bar

Maximum oil pressure .................................................................. 6.0 bar

Maximum oil pressure (cold start <20 sec.) ................................. 6.5 bar

Maximum oil consumption ............................................................. 0.1 l/h

Page 2 - 4 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Fuel

Minimum permissible fuel temperature in the fuel tank before takeoff

Minimum permissible fuel temperature in the fuel tank during the flight

Jet A-1, JET A, Fuel No.3 JP-8, JP-8+100, TS-1

- 30°C

- 35°C

Diesel

Greater than 0°C

- 5°C

Minimum fuel temperature limits in the fuel tanks:

Table 2-5 Min. Fuel Temperature Limits in the fuel tank

▲ WARNING: The following applies to Diesel and Jet A-1 mixtures in

the tank: As soon as the proportion of Diesel in the tank is more than 10%, the fuel temperature limits for Diesel operation must be observed. If there is uncertainty about which fuel is in the tank, the assumption should be made that it is Diesel.

Issue 3 – July 2014 Page 2 - 5

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Instrument

Red

Range

Amber Range

Green

Range

Amber Range

Red

Range

Tachometer [rpm]

0-2300

> 2300

Oil Pressure [bar]

0-1.1

1.2-2.2

2.3-5.2

5.3-6.0

> 6.0

Coolant temperature [°C]

< -32

-32... +59

60-100

101-

105

> 105

Oil Temperature [°C]

< -32

-32... +49

50-124

125-

140

> 140

Gearbox Temperature [°C]

< 115

115-

120

> 120

Load [%]

0-100

ENGINE INSTRUMENT MARKINGS

The engine data of the TAE 125 installation to be monitored are integrated in the combined engine instrument CED-125. The ranges of the individual engine monitoring parameters are shown in the following table.

Table 2-6 Markings of the Engine Instruments

 Note: If an engine reading is in the yellow or red

range, the "Caution" lamp is activated. It only extinguishes when the "CED-Test / confirm" button is pressed. If this test button is pressed longer than one second, a self-test of the instrument is initiated.

GROUNDING (EARTHING) BEFORE AND DURING FUELING

Use the engine exhaust pipe for draining static charge.

Page 2 - 6 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

PERMISSIBLE FUEL GRADES

 CAUTION: Using non-approved fuels and additives

can lead to dangerous engine malfunctions.

Fuel: ..................................................................... JET A-1 (ASTM 1655)

Alternative: ............................................................. Diesel (DIN EN 590)

Fuel additive for Diesel: .............. Liqui Moly “Diesel Fliess Fit” No. 5130

..................................... JP-8 (MIL-DTL-83133E)

............................. JP-8+100 (MIL-DTL-83133E)

................................. Fuel No.3 (GB 6537-2006)

Only TAE 125-02-99 (C2.0):

...................................... TS-1 (GOST 10227-86)

.................. TS-1 (GSTU 320.00149943.011-99)

MAXIMUM FUEL QUANTITIES

Standard tank:

Total capacity ......................................... 110 l / 29 US gal / 24.2 imp gal

Total usable fuel ..................................... 109 l / 28.7 US gal / 24 imp gal

Total unusable fuel .................................. 1 l / 0.26 US gal / 0.22 imp gal

Optional extended range tank (JET A-1 fuel only)

The total fuel capacity can be increased to 160 l / 35.2 imp gal / 42.24 US gal (159 l / 35 imp gal / 42 US gal usable) by installing an optional fuel tank of 50 l / 11 imp gal / 13.2 US gal, which flows into the main tank on command, most safely when the main tank can receive 50 liters. The fuel level in the optional tank may be displayed on the instrument panel fuel gauge indicator by pressing on the push-button switch.

Issue 3 – July 2014 Page 2 - 7

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

PERMISSIBLE OIL GRADES

 CAUTION: Use approved oil with exact designation only!

Engine oil: ........................................................ AeroShell Oil Diesel Ultra

......................................................... Shell Helix Ultra 5W-30

......................................................... Shell Helix Ultra 5W-40

.................................................AeroShell Oil Diesel 10W-40

Gearbox oil: .......................................... Shell Spirax S6 GXME 75W-80

.................................................. Shell Spirax S4 G 75W-90

............................... Shell Getriebeöl EP 75W-90 API GL-4

...................................................... Shell Spirax EP 75W-90

.......................................... Shell Spirax GSX 75W-80 GL-4

PERMISSIBLE COOLING LIQUID

Coolant: ............................ Water/Radiator Protection at a ratio of 50:50

Radiator Protection: .......................... BASF Glysantin Protect Plus/G48

..................................... Mobil Antifreeze Extra/G48

.................................... ESSO Antifreeze Extra/G48

........... Comma Xstream Green - Concentrate/G48

............................................... Zerex Glysantin G48

LOAD LIMITS

No change

OPERATIONAL LIMITATIONS IN THE “U” CATEGORY

 CAUTION: Intentionally initiating negative G maneuvers is

prohibited! Refer to original Pilot‘s Operating Handbook. Intentionally initiating spins and negative G maneuvers is prohibited.

Page 2 - 8 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

JET A1 (ASTM 1655)

DIESEL (EN590)

24.2 imp / 29 US Gal

110litres

JET A1 (ASTM 1655)

ONLY

11 imp / 13.2 US Gal

50litres

HUILE DR 400/135 CDI

OIL DR 400/CDI

PLACARDS

Figure 2-1 Near the Fuel Tank Caps: 110 liters JET/Diesel Fuel

Figure 2-2 Optional Extended Range Tank

Figure 2-3 On the oil funnel or at the engine cowling access door

Issue 3 – July 2014 Page 2 - 9

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

FUEL

E = 0

¼ = 25

½ = 50

¾ = 75

F = 100

( LITERS )

TE ST / AC K

ENGINE

CAUTION

ALT

FUEL LOW

LEVEL

FADECAFADECBFLAPS

DOWN

PITOT

HEATING

COOLANT

LEVEL

PRISE DE

PARC

AUSSENBORD

STROMANSCHLUSS

EXTERNAL

POWER

12 V

Figure 2-4 Near the CED

Figure 2-5 Near their respective gauges or switches

Figure 2-6 Annunciator Lights at the Top of the Instrument Panel

Figure 2-7 If installed, at the access door to the external power receptacle behind the wing on the aircraft's right side.

 Note: The receptacle has "one way only" feature for polarity

protection.

Page 2 - 10 Issue 3 – July 2014

Page 49

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

FUEL T(°C) indicated

MAIN TANK

OPT. TANK

FUEL QTY (litres)

Figure 2-8 If optional extended range fuel tank is installed, placard must be placed near to the fuel gauge.

Figure 2-9 If optional extended range fuel tank is installed, placard must be placed near the fuel transfer control.

Issue 3 – July 2014 Page 2 - 11

Page 50

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 3

EMERGENCY PROCEDURES

INDEX OF CHECKLISTS

ENGINE FAILURE OR LOSS OF POWER ........................................... 3-2

During takeoff roll ................................................................................... 3-2

Immediately after takeoff ....................................................................... 3-2

During flight ............................................................................................ 3-3

LANDING WITHOUT ENGINE POWER ............................................... 3-4

Restart after engine failure .................................................................... 3-5

FADEC malfunction in flight ................................................................... 3-6

ENGINE SHUT-DOWN IN FLIGHT ....................................................... 3-9

FIRE .....................................................................................................3-10

Engine fire on the ground, during starting ...........................................3-10

Engine fire in flight ..............................................................................3-10

Electrical fire.........................................................................................3-11

ROUGH ENGINE OPERATION ..........................................................3-12

Oil pressure too low .............................................................................3-12

Oil temperature too high ......................................................................3-13

Coolant temperature too high ..............................................................3-13

“Cool level” light illuminates .................................................................3-14

Gearbox temperature too high .............................................................3-14

Fuel temperature too low .....................................................................3-14

Propeller RPM too high ........................................................................3-15

Fluctuations in propeller RPM ..............................................................3-15

ICING ...................................................................................................3-16

ELECTRICAL POWER SUPPLY MALFUNCTION .............................3-17

If the “ALT” light is lit or the ammeter shows battery discharge during

normal engine operation for more than 5 minutes ...............................3-18

INADVERTENT SPIN ..........................................................................3-19

LOSS OF ELEVATOR CONTROL ......................................................3-19

Issue 3 – July 2014 Page 3 - 1

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

ENGINE FAILURE OR LOSS OF POWER During takeoff roll

1) Thrust Lever .............................................................................. IDLE

2) Apply brakes and hold direction. Avoid obstructions.

3) Engine Master switch ................................................................ OFF

4) Battery and ALT CB .................................................................. OFF

5) Fuel selector.............................................................................. OFF

6) Emergency ground egress ............................................. As required

Immediately after takeoff

1) Establish glide

Speed (flaps retracted) ..................................... (78 KIAS) 144 km/h

Speed (flaps T/O position) ............................... (75 KIAS) 139 km/h

2) Land straight ahead, with only small direction changes to avoid obstructions.

3) If complete engine failure:

FADEC A/B Switch .............................................................. Force B

4) Battery and ALT switch .................................................... Check ON

When landing inevitable:

5) Engine Master ........................................................................... OFF

6) Battery and ALT CB .................................................................. OFF

7) Fuel selector.............................................................................. OFF

8) Wing flaps ........................................ T/O or Landing recommended

9) Touch down with minimum speed

10) When aircraft has stopped ..................... Emergency ground egress

▲ WARNING: Never try to turn back to the runway, as altitude just after

takeoff is seldom sufficient.

Page 3 - 2 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

During flight

1) Establish glide:

Flaps retracted .................................................. (78 KIAS) 144 km/h

(In these conditions, without wind, the aircraft covers approx. 8 times its height above ground). Locate suitable field.

If altitude is sufficient to restart:

2) Electric fuel pump ........................................................................ ON

3) FADEC A/B switch .............................................................. Force B

if this doesn't improve engine operation, return switch to "Auto"

4) If no restart ......................... Reset Engine Master (OFF then to ON)

5) Battery and ALT CB ......................................................... Check ON

6) Engine and fuel level gauges /alarm panel

................................................................. Check for cause of failure

7) FADEC A, B circuit breakers ........................................... Check ON

8) In case the tank has been run to empty with still some fuel available

in the auxiliary tank

(if so equipped) ................................. Open aux. tank transfer valve

If the propeller does not turn:

9) Starter .......................................................................................... ON

The propeller will normally continue to turn as long as the airspeed is above 120 km/h (65 KIAS). Should the propeller stop at airspeed of more than 120 km/h or more, the reason for this should be found out before attempting a restart. If it is obvious that the engine or propeller is blocked, do not use the Starter.

If power is not restored, prepare for "landing without engine power". If the tank has been run to empty, both FADEC lights will be flashing.

▲ WARNING: The engine high pressure pump must be checked before

the next flight.

Issue 3 – July 2014 Page 3 - 3

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

LANDING WITHOUT ENGINE POWER

Look for a suitable landing area:

1) Airspeed .................................... 144 km/h (78 KIAS) flaps retracted

139 km/h (75 KIAS) flaps T/O

2) Seat belts and harness ............................................................. Tight

Before landing:

3) Electric pump ............................................................................ OFF

4) Fuel selector.............................................................................. OFF

5) Engine master switch ................................................................ OFF

6) Battery + Alternator switches .................................................... OFF

7) Flaps, when field can easily be reached: ................. T/O or Landing

8) Touch down with minimum speed

9) Brakes ............................................................................ As required

10) When aircraft has stopped ..................... Emergency ground egress

Page 3 - 4 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Restart after engine failure

 Note: If altitude permits and a restart is possible.

1) Airspeed ................................. Flaps retracted (78 KIAS) 144 km/h

[max. 100 KIAS, min. 70 KIAS]

2) Reliable restart altitude ......................................... Below 13 000 ft

3) Battery and ALT CB ....................................................... Check ON

4) Fuel selector ......................................................................... OPEN

5) Electric fuel pump ...................................................................... ON

6) Power lever .................................................................. max. power

7) Engine master switch............................................... OFF, then ON

if the propeller does not turn, the starter may be used.

 CAUTION: If the propeller is jammed, operate the starter briefly.

If it is obvious that the engine or propeller is blocked (speed has been maintained above 70 KIAS all the time), do not use the starter.

8) Engine parameters ............................................................... Check

9) Power lever, once engine runs

smoothly at idle ..................................................................... Adjust

10) Engine operation ...................................... Check available power /

engine parameters

 Note: If the engine still does not start, prepare for

"Landing without Engine Power". Refer to page 3-4.

Issue 3 – July 2014 Page 3 - 5

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

FADEC malfunction in flight

 Note: The FADEC consists of two components

that are independent of each other: FADEC A and FADEC B. In case of malfunctions in the active FADEC, it automatically switches to the other.

a) One FADEC Lamp is flashing

(1) Press FADEC-Test knob at least 2 seconds (2) FADEC Lamp extinguished (LOW category warning):

a) Continue flight normally b) Inform service center after landing.

(3) FADEC Lamp steady illuminated (HIGH category warning):

a) Observe the other FADEC lamp, b) Land as soon as practical, c) Airspeed should be below 100 KIAS (185 km/h), d) Inform service center after landing.

Page 3 - 6 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

b) Both FADEC Lamps are flashing

 Note: The load display may not correspond to the current

value.

(1) Press FADEC-Test knob at least 2 seconds (refer to section 1

“FADEC Reset”)

(2) FADEC Lamps extinguished (LOW):

a) Continue flight normally, b) Inform service center after landing.

(3) FADEC Lamps steady illuminated (HIGH):

a) Check the available engine power, b) Expect engine failure. c) Flight can be continued, however the pilot should

i) Select an airspeed below 100 KIAS (185 km/h) ii) Land as soon as possible iii) Be prepared for an emergency landing.

(4) Inform service center after landing.

Issue 3 – July 2014 Page 3 - 7

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

c) Abnormal engine behavior

 Note: The FADEC system normally switches

automatically between FADEC A and B in case of malfunction, in order to select the "healthiest" component. If this automatic switching doesn't work, it is possible to manually force the system to switch to FADEC B only, and check for improvement in engine behavior.

1) Maximum airspeed ........................................ (100 KIAS) 185 km/h

2) "FADEC A/B" switch........................................................FORCE B

3) If no engine operation improvement ......... Return switch to "Auto"

 Note: The switching from one FADEC to the other

one is usually accompanied by a short RPM fluctuation.

Page 3 - 8 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

ENGINE SHUT-DOWN IN FLIGHT

 Note: If it is necessary to shut down the engine in

flight (for instance, abnormal engine behavior does not allow continued flight, fuel leak, fire, etc.):

1) Reduce speed .................................... Below (100 KIAS) 185 km/h

2) Engine master switch............................................................... OFF

3) Fuel selector valve ................................................................... OFF

4) Electric fuel pump .................................................... OFF (if in use)

5) If the propeller has also to be stopped (for instance, due to

excessive vibrations) ..................................... Reduce airspeed to

60 - 65 KIAS, flaps T/O

6) When the propeller is stopped ......................... Continue to glide at

70 - 75 KIAS, flaps T/O

Issue 3 – July 2014 Page 3 - 9

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

FIRE

Engine fire on the ground, during starting

1) Engine master switch .............................................................. OFF

2) Fuel selector ............................................................................ OFF

3) Electric fuel pump.................................................................... OFF

4) Battery + alternator switch ...................................................... OFF

5) Emergency ground egress ........................................... As required

Extinguish the flames with a fire extinguisher, wool blankets or sand. Have fire damage thoroughly examined and appropriate repairs made before the next flight.

Engine fire in flight

1) Power lever ...................................................................... Reduce

2) Reduce speed .................................. Below (100 KIAS) 185 km/h

3) Engine master switch ............................................................ OFF

4) Fuel selector .......................................................................... OFF

5) Electric fuel pump .................................................. OFF (if in use)

6) Battery + alternator switch (after radio calls) ........................ OFF

7) Cabin heat ............................................................................. OFF

8) Glide speed ................................................... (78 KIAS) 144 km/h

9) Adjust cabin ventilation for lowest smoke in the cabin

10) Fire extinguisher (if available) ............................. Use as required

 Note: Proceed with "landing without engine power".

Page 3 - 10 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Electrical fire

 Note: In case of an electrical fire (smell of fumes

indicating wire insulation burning):

1) All electrical equipment and c (after brief call) ....................... OFF

leave Alternator, Battery and Engine Master ON

2) Cabin ventilation .................................................................... OFF

3) Cabin heat .............................................................................. OFF

4) Fire extinguisher (if available) ............................. Use as required

▲ WARNING: After the fire extinguisher has been used, make sure that

the fire is extinguished before exterior air is used to remove smoke from the cabin

5) If there is evidence of continued electrical fire, consider turning OFF Battery and Alternator

▲ WARNING: If both Battery and Alternator are turned OFF, the engine

will continue to operate using the FADEC backup battery for limited time (TAE 125-02-99 installation).

- Perform emergency landing. Refer to page 3-4.

- do not switch the “FORCE-B” switch, this will shut down the engine!

If the fire has been extinguished:

6) Cabin ventilation ...................................................................... ON

7) Check circuit breakers, do not reset if open

8) Avionics Master Switch ............................................................ ON

9) Turn ON only electrical equipment required to continue flight depending on the situation and land as soon as practical. Do only switch ON one at a time, with delay after each.

Issue 3 – July 2014 Page 3 - 11

Page 62

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

ROUGH ENGINE OPERATION

Oil pressure too low (< 2.3 bar in cruise or <1.2 bar at idle power)

(1) Reduce power as quickly as possible (2) Check oil temperature: If the oil temperature is high or near operating limits,

i) Land as soon as possible ii) Be prepared for an emergency landing iii) Expect engine failure

 Note: During warm-weather operation or longer

climb outs at low airspeed engine temperatures could rise into the amber range and trigger the "Caution" light. This warning allows the pilot to avoid overheating of the engine as follows:

(3) Increase the climbing airspeed, reduce angle of climb (4) Reduce power, if the engine temperatures approach the red area.

Page 3 - 12 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Oil temperature too high

(1) Increase airspeed and reduce power as quickly as possible (2) Check oil pressure. If the oil pressure is lower than normal (<2.3 bar in cruise or <1.2 bar at idle),

i) Land as soon as possible ii) Be prepared for an emergency landing iii) Expect engine failure

(3) If the oil pressure is in the normal range

i) Land as soon as practical

 Note: During hot weather operation or prolonged

climbs at low airspeed, engine temperatures could rise into the yellow range and trigger the caution light. This warning allows the pilot to avoid overheating of the engine as follows:

1. Increase the climbing airspeed

2. Reduce power if the engine temperature approaches the red area.

Coolant temperature too high

1) Check coolant level light

2) Increase airspeed and reduce the power.

3) Check cabin heat ................................................................... OFF

If coolant level light is on, or an obvious malfunction is suspected (because airspeed was maintained above Vy, non-hot weather conditions, cabin heat OFF) or if this does not cause the coolant temperature to drop,

i) Land as soon as practical ii) Be prepared for an emergency landing iii) Expect an engine failure

Issue 3 – July 2014 Page 3 - 13

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

“Cool level” light illuminates

1) Increase airspeed and reduce the power

2) Cabin heat ............................................................................. OFF

3) Monitor coolant temperature

4) Monitor oil temperature

5) If coolant temperature and/or oil temperature are rising into amber and towards red range:

i) Land as soon as practical ii) Be prepared for an emergency landing iii) Expect an engine failure

Gearbox temperature too high

1) Reduce power ............................................................. 55% - 75%

2) Land as soon as practical

Fuel temperature too low

1) Change to altitude with higher outside air temperature

2) If the fuel temperature remains too low:

i) land as soon as practical

Page 3 - 14 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Propeller RPM too high

 Note: If propeller RPM above 2300 (red range):

1) Reduce power

2) Reduce airspeed below 100 KIAS (185 km/h) or as appropriate to prevent propeller overspeed

3) Set power as required to maintain altitude and land as soon as practical.

 Note: If the propeller speed control fails, climb

flights can be performed at 120 km/h (65 KIAS) and a power setting of 100%. In case of over speed the FADEC will reduce the engine power at higher airspeeds to avoid propeller speeds above 2500 rpm.

Fluctuations in propeller RPM

If the propeller RPM fluctuates by more than ± 100 RPM with a constant power lever position:

1) Change the power setting and attempt to find a power setting

where the propeller RPM no longer fluctuates.

2) If unsuccessful power lever full forward at airspeed < 185 km/h

(100 KIAS) until propeller speed stabilizes

3) If normal operation is resumed, continue the flight

4) If problem continues, select a power setting where the propeller

RPM fluctuations are minimum. Fly at airspeed below 185 km/h (100 KIAS) and land as soon as practical.

Issue 3 – July 2014 Page 3 - 15

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

ICING

▲ WARNING: It is prohibited to fly in known icing conditions.

Icing has a very strong negative effect on the aerodynamic characteristics of the aircraft. Stalling speed increases.

Proceed as follows when inadvertently encountering icing:

1) Pitot heat switch ....................................................... ON (if installed)

If no pitot heat installed, expect airspeed indications to become unreliable

2) Immediately leave the region in which the icing occurred. If possible change the altitude to obtain an outside air temperature that is less conductive to icing

3) Cabin heat / defrost ........................................................ As required

4) Alternate induction air ............................................................ OPEN

5) Increase power; make quick power changes from time to time to try to clear ice from the propeller blades.

Plan to land at the nearest airfield. If the build-up of ice is extremely fast, execute an off-airfield forced landing.

 Note: A layer of 0.5 cm (0.2 in) on the leading

edge of the wing substantially increases the stalling speed. If needed, use a higher than normal approach speed: 145 km/h (78 KIAS). Do not use flaps.

Page 3 - 16 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

ELECTRICAL POWER SUPPLY MALFUNCTION

 Note: The TAE 125 requires an electrical power source for its

operation. If the alternator fails, the only power source will be provided by the battery. The time the engine can run on battery alone will depend on total electrical consumption supported by the battery, i.e. the load of the electrical equipment kept in use. The pilot should turn off all non-essential items and supply power only to equipment which is absolutely necessary for continued flight depending upon the

situation. If the FADEC back-up battery is installed (TAE 125-02-99 installation): ▲ WARNING: When both main battery and alternator have failed, the

engine will continue to operate using the FADEC backup

battery for limited time. In this case, all electrical

equipment will not operate:

- land immediately

- do not switch the “FORCE-B” switch, this will shut down

the engine!

The failure of the alternator is indicated by:

 "ALT" light is ON  Voltmeter shows too low or too high voltage (red range)  Ammeter (if installed) shows battery discharge for more than

5 min

Issue 3 – July 2014 Page 3 - 17

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

If the “ALT“ light is lit or the ammeter shows battery discharge during normal engine operation for more than 5 minutes

1) Alternator circuit breaker .................................................. Check ON

 CAUTION: If the FADEC was supplied by battery only

until this point, the RPM can momentarily drop, when the alternator will be switched on. In any case: leave the alternator switched ON!

2) Check "ALT" light and voltmeter indications

3) If normal operation has not resumed:

Alternator ................................................................................... OFF

4) Switch OFF all electrical equipment not essential for continuation of flight

5) Land as soon as possible

Page 3 - 18 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

INADVERTENT SPIN

Should a spin occur, apply the following procedure:

1) Power Lever ....................................................................... Idle (pull)

2) Rudder ..................................... Full opposite to direction of rotation

3) Elevator ................................................................................. Neutral

4) Ailerons ................................................................................ Neutral

5) Once the rotation is stopped, bring rudder to neutral position and

recover within flight limitations.

 Note: If flaps are down when spin begins, retract

them immediately.

LOSS OF ELEVATOR CONTROL

No change, refer to original POH

Issue 3 – July 2014 Page 3 - 19

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Page 3 - 20 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 4

NORMAL PROCEDURES

NORMAL OPERATING SPEEDS

The speeds listed below are indicated airspeeds recommended for normal operation of the aircraft. These speeds are based on a standard aircraft, operated at max. takeoff weight, in standard atmosphere and at sea level. They may vary from one aircraft to another depending on the equipment installed, the conditions of the aircraft and of the engine, the atmospheric conditions and the skills of the pilot.

Best rate of climb speed

Flaps in takeoff position (1st notch) ............................ (76 KIAS) 141 km/h

Flaps up ...................................................................... (78 KIAS) 144 km/h

Best angle of climb speed

Flaps in takeoff position (1st notch) ............................ (65 KIAS) 120 km/h

Flaps up ...................................................................... (65 KIAS) 120 km/h

Maximum operating speed in turbulent air

Flaps up .................................................................... (140 KIAS) 260 km/h

Maximum speed

Flaps in landing position (2nd notch) .......................... (92 KIAS) 170 km/h

Landing speed, final approach

Flaps in landing position (2nd notch) .......................... (62 KIAS) 115 km/h

Issue 3 – July 2014 Page 4 - 1

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

PRE-FLIGHT INSPECTION

To be performed before each flight. This inspection may be shortened for intermediate landings on route.

Figure 4-1 Pre-flight inspection

Page 4 - 2 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Master engine switch ...........................................................................OFF

Avionics master switch (if equipped) ...................................................OFF

Controls ............................................................................ Free and correct

Battery switch ........................................................................................ ON

▲ WARNING: When turning on the battery switch, using an external

power source, or pulling the propeller through by hand, treat the propeller as if the Engine Master switch was on.

Flaps ................................................................................ Check operation

Fuel quantity................................................................................. Checked

Fuel temperature .......................................................................... Checked

Water level .................................................................................. Light OFF

Battery switch .......................................................................................OFF

Aircraft documents ....................................................................... On board

Baggage ........................................................................... Securely stowed

Check flight controls displacements, then make an aircraft walk around inspection starting at the fuselage left side. See Figure 4-1.

(1)

a) Fuel filler cap .................................................... in place, secured

b) Static vent ..................................................... clean, unobstructed

c) Main tank drain valve ..................................................... actuated

d) Optional tank (when installed) drain valve ..................... actuated

 Note: Left or right depending on airplane bank

attitude. Check for water, sediment and the right type of fuel (Diesel or JET A-1 versus Avgas [should not be blue!])

Issue 3 – July 2014 Page 4 - 3

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

(2)

a) Horizontal stabilizer ...................................... Surface condition,

hinge wear in tolerance

b) Rudder ........................................ Check hinge wear in tolerance

(3)

a) Static vent .................................................... Clean, unobstructed

(4)

a) Flap and aileron ............................... Check condition and hinges

b) Wing tip and navigation lights (optional) ... Check condition

(5)

a) Stall warning ............................................ Clean, check actuation

b) Right main landing gear.......................... Check, oil cap secured,

Panel closed, Normal shock absorber compression, Tire inflated

(6)

a) Fuel drain valve ............................................................. Actuated

b) Oil level ......................... Checked, oil cap secured, panel closed

c) Exhaust pipe ........................................................................ Rigid

d) Engine cowl attachments................................................... Check

e) Propeller ............................................... Clean, in good condition

f) Propeller spinner ............................................................. No play

g) Air inlets ....................................................... Clean, unobstructed

h) Gear box oil level ............................................................... Check

 Note: The oil has to cover at least half of the

inspection glass

Page 4 - 4 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

(7)

a) Nose gear ............................. Check attachment and condition of

fairing, normal shock absorber compression, tire inflated, tow bar removed

b) Canopy cleanliness ............................................................Check

(8)

a) Left main landing gear ............................. Check attachment and

condition of fairing, normal shock absorber compression, tire inflated

b) Pitot ............................................................. Clean, unobstructed

c) Lights (optional) ........................................................ Glass clean

(9)

a) Wing tip and navigation light (optional) .............. Check condition

b) Flap and aileron............................... Check condition and hinges

CABIN INTERIOR CHECK BEFORE START-UP

1) Canopy ............................................................... Closed and locked

2) Parking brake........................................................................ Locked

3) Front seats ....................................................... Adjusted and locked

4) Belts and harnesses ..................................... Adjusted and fastened

5) Flight controls .................... Free, without play or excessive friction,

correct action (check rudder during taxiing)

6) Elevator trim ................. Check travel, then return to takeoff position

7) Battery switch .............................................................................. ON

8) CED lights autotest ............................................................... Monitor

9) ALT CB ........................................................................................ ON

10) Alarm panel .......................... Test, set DAY / NIGHT as appropriate

Issue 3 – July 2014 Page 4 - 5

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

11) Circuit breakers ........................................................................... ON

 Note: The electronic engine control needs an

electrical power source for its operation. For normal operation, battery switch and alternator circuit breaker have to be ON. Separate switching is only allowed for tests and in event of emergencies.

12) All electrical switches and avionics ........................................... OFF

 CAUTION: The avionics power switch must be off

during engine start to prevent possible damage to avionics.

STARTING THE ENGINE

1) Canopy .................................................................................. Closed

2) Strobe light .................................................................................. ON

3) Fuel level / fuel temperature ................................................. Check

4) Fuel selector.................................................... Check operation, ON

5) Alternate induction air ........................................................... Closed

6) Electric pump .............................................................................. ON

7) Thrust Lever .............................................................................. IDLE

8) Propeller area........................................................................... Clear

9) Master Engine switch ................................................................. ON,

10) FADEC lights.................................................................. Check OFF

11) Glow Control light ...................................................... Wait until OFF

12) Starter ......................................................................................... ON

 Note: Release when engine starts, leave Thrust

Lever in idle position

 CAUTION: It is not allowed to start up the engine using

external power!

Page 4 - 6 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

13) Check ................................................... Oil pressure / Idle RPM 890

 CAUTION: If after 3 seconds the minimum oil pressure

of 1 bar is not indicated, shut down the engine immediately!

14) “Engine“ resp. “CED“ Caution light ............................. Acknowledge

15) ALT light ......................................................................... Check OFF

16) Ammeter (if installed) ................ Check for positive charging current

17) FADEC lights ................................................................. Check OFF

18) Vacuum gauge........................................................................ Check

AFTER ENGINE START

1) Electrical fuel pump ................................................................... OFF

If FADEC Backup battery installed (TAE 125-02-99 installation):

a) Alternator ..................................OFF, engine must operate normally

b) Battery ...................................................... OFF, for min. 10 seconds;

engine must operate normally, the red FADEC lamps must not be

illuminated

c) Battery .......................................................................................... ON

d) Alternator ..................................................................................... ON

▲ WARNING: It must be ensured that both battery and alternator are

ON!

2) Avionics power switch (if equipped) ............................................ ON

3) COM / NAV, navigation instruments .................................... ON, set

4) Altimeter ....................................................................................... Set

5) Horizon / Directional gyro ............................................................ Set

Issue 3 – July 2014 Page 4 - 7

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

WARM UP

1) Cabin heat can be pulled to facilitate quicker coolant warming.

2) Let the engine warm up about 2 minutes at idle

3) Increase to not more than 1400 RPM until oil temperature minimum 50 °C, coolant temperature minimum 60 °C

(All CED LEDs....................................................................... green).

TAXIING

1) Parking brakes ...................................................................Unlocked

2) Brakes ........................................................................................ Test

3) Do not exceed 1400 RPM when CED shows yellow LED for oil and coolant temperature

4) During taxi / turns:

a) Turn and bank indicator / Horizon (option) ........................ Check

b) Directional gyro (option) ................................... Check operation

c) Standby compass .............................................................. Check

BEFORE TAKEOFF

1) Parking brake ............................................................................. SET

2) Canopy ...................................................... CLOSED AND LOCKED

3) Flight controls ......................................................... Free and correct

4) Flight and navigation instruments ............................. Check and Set

5) Cabin heat ................................................................ Set as required

(OFF if heating is not desired)

6) Fuel selector valve ...................................................................... ON

7) Fuel quantity............................................... Verify sufficient for flight

8) Elevator trim ............................................................... Set for takeoff

Page 4 - 8 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

9) (FADEC self-check:

a) Thrust Lever ......................................... IDLE (both FADEC lamps

should be OFF)

b) FADEC test button ............................... PRESS and HOLD button

for entire test

c) Both FADEC lamps ........................................ ON, RPM increases

 Note: If the FADEC test does not start, verify if the

thrust lever is in IDLE position. If not, set to IDLE position and try again to start FADEC test

▲ WARNING: If the FADEC lamps do not come on at this point, it

means that the test procedure has failed and takeoff should not be attempted.

d) The FADEC automatically switches to B-component (only

FADEC B light is on). e) The propeller control is excited, RPM decreases momentarily f) The FADEC automatically switches to channel A (only FADEC A

light is ON) g) The propeller control is excited, RPM decreases momentarily h) FADEC A lamp goes off, RPM goes back to idle RPM, and the

test is completed.

i) FADEC test button ........................................................ RELEASE

▲ WARNING: If there are prolonged engine misfires or the engine

shuts down during the test, takeoff must not be attempted.

Issue 3 – July 2014 Page 4 - 9

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

▲ WARNING: The whole test procedure has to be performed without

any discrepancy. In case the engine shuts down or the FADEC lamps are flashing, takeoff is PROHIBITED. This applies even if the engine seems to run without failure after the test.

 Note: If the test button is released before the self-test is fully

completed, the FADEC immediately resumes normal operation.

 Note: While switching from one FADEC to

another, it is normal to hear and feel a momentary surge in the engine.

10) Thrust Lever ........................................................ FULL FORWARD,

RPM must be stabilized load display minimum 94% RPM 2240 - 2300

 Note: The power check should be performed at a

place which is free of debris to minimize risk of damage to propeller or other parts.

11) Thrust Lever .............................................................................. IDLE

12) Engine instruments and Voltmeter ...................................... CHECK

13) Vacuum gauge ..................................................................... CHECK

14) Flaps .................................. Full down, then back to takeoff position

15) Electrical fuel pump ..................................................................... ON

16) Radios and avionics ............................................................. ON, set

17) Thrust Lever friction control ..................................... SET as desired

18) Brakes .............................................................................. RELEASE

19) CED ......................................................... CHECK all LEDs GREEN

Page 4 - 10 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

TAKEOFF Normal takeoff

1) Thrust lever ........................................................ FULL FORWARD

2) Takeoff RPM before rotation ......................................... 2300 RPM

3) Takeoff speed ................................................. 106 km/h (57 KIAS)

4) Initial climb speed ........................................... 120 km/h (65 KIAS)

5) After obstacles clearance,

Reduce angle of climb to reach ...................... 145 km/h (78 KIAS)

6) Electric pump ........................................................................... OFF

7) Flaps .......................................................................................... Up

Short takeoff

1) Flaps .................................................... (1st notch) takeoff position

2) Apply full power, brakes applied

then release the brakes ................................................. 2300 RPM

before rotation

3) Rotation speed .................................................. 96 km/h (52 KIAS)

4) Lift-off speed ................................................... 106 km/h (57 KIAS)

5) If needed to clear an obstacle,

Proceed at best angle of climb speed ............ 113 km/h (61 KIAS)

Crosswind takeoff

1) Flaps .................................................. (1st notch) take-off position

2) Ailerons ....................................................................... into the wind

 Note: Takeoff at a slightly higher airspeed than

normal. Correct drift in the normal way (max bank angle close to the ground: 15°).

3) Demonstrated crosswind capability ................. (22 KIAS) 40 km/h

Issue 3 – July 2014 Page 4 - 11

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

CLIMB Normal climb (flaps up)

Best rate of climb: 145 km/h (78 KIAS) from 0 to 9 500 ft, 139 km/h (75 KIAS) up to 11 500 ft, 133 km/h (72 KIAS) above 11 500 ft. A climb at higher speed, when best rate is not required, will provide for more forward visibility.

1) Thrust Lever ................................................................. Full forward

Best angle of climb

A better angle of climb is obtained at 120 km/h (65 KIAS), flaps in takeoff position or flaps up.

 Note: In case that oil temperature and/or coolant temperature

are approaching the upper limit:

 Verify that cabin heat is OFF.  Continue at a lower climb angle and higher speed

for better cooling if possible.

CRUISE

 Note: Refer to Section 5 for RPM settings and

cruise performance.

1) Power ............ Maximum load 100 % (maximum continuous power)

Recommended: 75 % or less

2) Elevator trim ........................................................................ADJUST

3) Compliance with limits for oil pressure, oil temperature, coolant

temperature and gearbox temperature

(CED 125 and caution lamp) ......................... MONITOR constantly

4) Fuel quantity and temperature

(display and low level warning lamp) ...............................MONITOR

▲ WARNING: If fuel temperature falls below allowable minimum,

expect engine failure. Fuel in tank is actively heated by the returning injector overflow, so too low fuel temperature is an extreme condition.

5) FADEC warning lamp ......................................................MONITOR

Page 4 - 12 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

DESCENT

1) Power .................. As required to maintain the desired descent path

2) Pull cabin heat to keep the coolant warm if power setting is low. If coolant temperature in amber range and engine caution lamp illuminated, increase power to recover green coolant temperature range.

Approach or down wind

1) Electric fuel pump ........................................................................ ON

2) Cabin (seats, belts) ................................................................. Check

3) Flaps ...................................................... Below (92 KIAS) 170 km/h

(1st notch) in takeoff position

4) Speed ............................................................... (81 KIAS) 150 km/h

5) Elevator trim ............................................................................... SET

Final

1) Flaps ...................................................... Below 150 km/h (81 KIAS)

(2nd notch) landing position

2) Approach speed ............................................... 115 km/h (62 KIAS)

 Note: The approach speed may be increased to 70

KIAS (130 km/h) to improve maneuverability. This can increase the landing distance.

3) Elevator trim ............................................................................... SET

Issue 3 – July 2014 Page 4 - 13

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

LANDING Short landing

1) Flaps .................................................... (2nd notch) landing position

2) Approach speed, with

Thrust Lever setting .......................................... 115 km/h (62 KIAS)

After touchdown, brake heavily keeping nose up with elevator and retracting the flaps.

Overshoot procedure

1) Thrust Lever ..........................................................Full power (push)

2) Speed ................................................................ (65 KIAS) 120 km/h

3) Progressively raise flaps to the "takeoff position" (1st notch), then

establish normal climb speed ........................... (75 KIAS) 140 km/h

AFTER LANDING

1) Electric fuel pump ..................................................................... OFF

2) Wing flaps .................................................................................... UP

3) Navigation instruments ............................................................. OFF

ENGINE SHUT-DOWN

1) Parking brake ............................................................................. SET

2) Thrust Lever .............................................................................. IDLE

3) Wing flaps ............................................................................. DOWN

4) COM/NAV and electrical equipment ........................................ OFF

5) Engine Master switch ................................................................ OFF

After the engine stops

1) Battery ....................................................................................... OFF

2) When wheel chocks in place ................. Release the parking brake

Page 4 - 14 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

PARKING BRAKE USE

Brake on

Press on both pedals. Keep pressure on while pulling the parking brake control. Release the pressure on the pedals, the parking brake control must remain in pulled position.

or Pull the parking brake control.

Press on both pedals, then release the pressure on the pedals. The parking brake control must remain in the pulled position.

Brake off

Push the parking brake control down.

Issue 3 – July 2014 Page 4 - 15

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Page 4 - 16 Issue 3 – July 2014

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Engine idle Weight 980 kg (2161 lb)

km/h (kt)

Bank angle

0°

30°

60°

Flaps up

99 (54)

106 (58)

140 (76)

Flaps 1st notch, take off position

92 (50)

98 (53)

130 (70)

Flaps 2nd notch, landing position

87 (47)

93 (51)

123 (67)

SECTION 5

PERFORMANCE

AIRSPEED INSTALLATION CALIBRATION

No change

STALL SPEEDS

Table 5-1 Stall speeds

Issue 3 – July 2014 Page 5 - 1

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Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Pressure

Altitude

[ft]

Take off distance [m] at 980 kg (2161 lb)

ISA conditions

ISA + 10°C

ISA + 20°C

To lift-off

to 50 ft

height

To lift-off

to 50 ft

height

To lift-off

to 50 ft

height

240

440

260

480

280

520

1000

260

470

270

500

290

540

2000

270

490

290

530

310

570

3000

280

510

300

550

320

590

4000

300

540

320

580

340

630

5000

310

580

330

620

360

670

6000

330

620

350

660

380

720

7000

360

690

380

730

400

790

8000

390

760

410

810

430

880

9000

410

810

430

850

450

930

TAKEOFF PERFORMANCE

At max. take-off weight 980 kg (2161 lb), without wind, flaps in takeoff position, engine full power

Conditions

 No wind, flaps in takeoff position (1

notch), engine full power on

brakes before release

 Level, dry, asphalt runway  Rotation speed v

 Lift off speed Vlof ...................................................... 105 km/h (57 kt)

 Speed at 15 m (50 ft) height obstacle clearance ...... 113 km/h (61 kt)

......................................................... 96 km/h (52 kt)

Table 5-2 Takeoff distance (m) at 980 kg (MTOW)

Page 5 - 2 Issue 3 – July 2014

Page 89

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Pressure

Altitude

[ft]

Take off distance [m] at 880 kg (1940 lb)

ISA conditions

ISA + 10°C

ISA + 20°C

To lift-off

to 50 ft

height

To lift-off

to 50 ft

height

To lift-off

to 50 ft

height

190

350

210

380

220

410

1000

200

370

220

390

230

430

2000

210

390

230

410

250

450

3000

220

400

240

430

260

460

4000

240

430

250

460

270

490

5000

250

450

270

480

290

520

6000

270

490

290

520

310

560

7000

290

540

310

570

330

620

8000

310

590

330

620

350

680

9000

330

630

350

660

370

720

Table 5-3 Takeoff distance (m) at 880 kg

Headwind influence:

 For 10 kt, multiply by 0.85  For 20 kt, multiply by 0.65  For 30 kt, multiply by 0.55

Tailwind influence:

 Add 10% to distance for each additional 2 kt

Dried grass runway:

 Add 15%

Issue 3 – July 2014 Page 5 - 3

Page 90

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Flaps takeoff

Flaps retracted

Best angle of climb

120 km/h (65 KIAS)

Best rate of climb

141 km/h (76 KIAS)

144 km/h (78 KIAS)

CLIMB PERFORMANCE

At sea level

Table 5-4 Climb performance at sea level

Rate of climb, flaps retracted, 980 kg (MTOW):

Climb speeds:

 78 kt from 0 to 9500 ft  75 kt up to 11500 ft  72 kt above.

Page 5 - 4 Issue 3 – July 2014

Page 91

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Pressure

Altitude

[ft]

Rate of climb [ft/min] at 980 kg (2161 lb)

ISA

conditions

ISA+10°C

ISA+20°C

680

660

630

500

680

660

630

1000

680

660

630

1500

675

660

630

2000

675

660

630

2500

675

660

630

3000

670

660

630

3500

660

650

610

4000

650

640

600

4500

630

620

580

5000

620

610

570

5500

600

590

560

6000

580

570

540

6500

570

560

530

7000

550

540

510

7500

540

530

500

8000

520

510

480

8500

490

450

9000

490

480

450

9500

480

450

10 000

370

350

10 500

350

340

11 000

340

330

11 500

320

310

12 000

300

12 500

280

13 000

260

13 500

230

14 000

210

14 500

190

15 000

170

15 500

150

16 000

130

Table 5-5 Rate of climb at 980 kg (MTOW)

Issue 3 – July 2014 Page 5 - 5

Page 92

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Pressure

Altitude

[ft]

Rate of climb [ft/min] at 880 kg (1940 lb)

ISA

conditions

ISA+10°C

ISA+20°C

910

900

860

500

910

900

860

1000

910

900

860

1500

910

900

860

2000

910

900

860

2500

910

900

860

3000

910

900

860

3500

900

890

850

4000

890

880

840

4500

870

860

820

5000

860

850

820

5500

840

830

800

6000

820

810

780

6500

810

800

770

7000

790

780

750

7500

780

770

740

8000

760

750

720

8500

730

720

690

9000

720

690

9500

720

690

10 000

600

580

10 500

580

570

11 000

570

11 500

550

12 000

540

12 500

520

13 000

500

13 500

460

14 000

450

14 500

420

15 000

400

15 500

380

16 000

350

16 500

310

Rate of climb, Flaps retracted, 880 kg

Table 5-6 Rate of climb at 880 kg

Page 5 - 6 Issue 3 – July 2014

Page 93

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Pressure

Altitude

[ft]

Time to climb [min] at 980 kg (2161 lb) (MTOW)

ISA conditions

ISA+10°C

ISA+20°C

500

0.7

0.8

1000

1.5

1.6

1500

2.2

2.3

2.4

2000

2.9

3.0

3.2

2500

3.7

3.8

4.0

3000

4.4

4.5

4.8

3500

5.2

5.3

5.6

4000

5.9

6.1

6.4

4500

6.7

6.9

7.2

5000

7.5

7.7

8.1

5500

8.3

8.5

8.9

6000

9.1

9.3

9.8

6500

10.0

10.2

10.8

7000

10.9

11.1

11.7

7500

11.8

12.0

12.7

8000

12.7

13.0

13.7

8500

13.7

13.9

14.7

9000

14.7

15.0

15.8

9500

15.7

16.0

17.0

10 000

16.8

17.1

18.1

10 500

18.1

18.4

19.5

11 000

19.5

19.8

21.0

11 500

21.0

21.3

22.5

12 000

22.6

22.9

24.1

Time to climb, flaps retracted, 980 kg

Climb speeds:

 78 kt from 0 to 9500 ft  75 kt up to 11500 ft  72 kt above.

Table 5-7 Time to climb (mn) at 980 kg (MTOW), 0 – 12500 ft

Issue 3 – July 2014 Page 5 - 7

Page 94

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Pressure

Altitude

[ft]

Time to climb [min] at 980 kg (2161 lb) (MTOW)

ISA conditions

ISA+10°C

ISA+20°C

12 500

24.2

24.5

25.8

13 000

26.0

26.3

27.5

13 500

27.9

28.2

29.5

14 000

30.1

30.4

31.6

14 500

32.5

32.8

34.0

15 000

35.1

35.4

36.7

15 500

38.1

38.4

39.6

16 000

41.4

41.7

42.9

16 500

45.2

45.5

46.8

Pressure

Altitude

[ft]

Time to climb [min] at 880 kg (1940 lb) (MTOW)

ISA conditions

ISA+10°C

ISA+20°C

500

0.5

0.6

1000

1.1

1.2

1500

1.6

1.7

2000

2.2

2.3

2500

2.7

2.8

2.9

3000

3.3

3.5

3500

3.8

3.9

4.1

4000

4.4

4.5

4.7

4500

5.0

5.3

5000

5.5

5.6

5.9

5500

6.1

6.2

6.5

6000

6.7

6.8

7.1

6500

7.3

7.4

7.7

7000

7.9

8.0

8.4

7500

8.6

8.7

9.1

8000

9.2

9.3

9.7

8500

9.9

10.0

10.4

9000

10.6

10.7

11.1

Table 5-8 Time to climb (mn) at 980 kg (MTOW), 13000 – 16500 ft

Rate of climb, flaps in takeoff position

Table 5-9 Time to climb (mn) at 880 kg (MTOW), 0 – 9000 ft

Page 5 - 8 Issue 3 – July 2014

Page 95

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Pressure

Altitude

[ft]

Time to climb [min] at 880 kg (1940 lb) (MTOW)

ISA conditions

ISA+10°C

ISA+20°C

9500

11.3

11.4

11.9

10 000

11.9

12.1

12.6

10 500

12.8

12.9

13.5

11 000

13.6

13.8

14.3

11 500

14.5

14.6

15.2

12 000

15.4

15.6

16.1

12 500

16.4

16.5

17.1

13 000

17.3

17.4

18.0

13 500

18.3

18.4

19.0

14 000

19.4

19.5

20.1

14 500

20.5

20.6

21.2

15 000

21.7

21.8

22.4

15 500

23.0

23.1

23.7

16 000

24.3

24.4

25.0

16 500

25.7

25.8

26.4

Table 5-10 Time to climb (mn) at 880 kg (MTOW), 9500 – 16500 ft

Rate of climb, flaps in takeoff position

Best rate of climb: Subtract 10% from the flaps retracted rates of climb in the above tables.

Maximum angle of climb:

8.3% at sea level, standard atmosphere, MTOW, and 120 km/h (65 kt).

Glide performance

Engine off, the aircraft glides8 times its altitude above ground (without wind) at 145 km/h (78 kt). Altitude and temperature do not have perceptible influence.

Issue 3 – July 2014 Page 5 - 9

Page 96

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Press.

Alt.

ISA conditions

Standard Tank

109 Liters

Standard and

Auxiliary Tank

159 Liters

Engine

Load

Fuel flow

[ft]

[%]

KCAS

KTAS

[l/h]

Hours

2000

108

111

21.2

496

4.5

758

6.8

2000

104

107

19.6

516

4.8

788

7.4

2000

100

103

18.1

537

5.2

821

8.0

2000

16.7

555

5.7

848

8.7

2000

15.3

562

6.2

859

9.5

2000

13.9

554

6.8

846

10.4 4000

107

114

21.2

508

4.5

776

6.8

4000

103

109

19.6

526

4.8

804

7.4

4000

105

18.1

548

5.2

837

8.0

4000

16.7

564

5.7

862

8.7

4000

15.3

570

6.2

871

9.5

4000

13.9

561

6.8

857

10.4

6000

107

117

21.2

520

4.5

794

6.8

6000

102

112

19.6

537

4.8

821

7.4

6000

107

18.1

559

5.2

854

8.0

6000

101

16.7

576

5.7

880

8.7

6000

15.3

579

6.2

885

9.5

6000

13.9

569

6.8

870

10.4

CRUISE PERFORMANCE

At maximum takeoff weight 980 kg (2161 lb), in standard atmosphere. Range and endurance calculations take into account 45 min. reserve (at 55% load) at destination. Assumption is made that higher consumption for climb is compensated by a cruise descent. Range assumes no wind.

Standard Tank ............................................................... 109 liters usable

Standard and Auxiliary Tanks ....................................... 159 liters usable

Table 5-11 Cruise performance, 2000 – 6000 ft

Page 5 - 10 Issue 3 – July 2014

Page 97

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Press.

Alt.

ISA conditions

Standard Tank

109 Liters

Standard and

Auxiliary Tank

159 Liters

Engine

Load

Fuel flow

[ft]

[%]

KCAS

KTAS

[l/h]

Hours

8000

106

120

21.2

533

4.5

815

6.8

8000

101

114

19.6

548

4.8

838

7.4

8000

109

18.1

571

5.2

872

8.0

8000

103

16.7

582

5.7

890

8.7

8000

15.3

587

6.2

897

9.5

8000

13.9

575

6.8

880

10.4

10000

105

122

21.2

545

4.5

833

6.8

10000

100

116

19.6

560

4.8

856

7.4

10000

112

18.1

582

5.2

890

8.0

10000

106

16.7

601

5.7

918

8.7

10000

15.3

598

6.2

915

9.5

10000

13.9

586

6.8

895

10.4

12000

104

125

21.2

557

4.5

851

6.8

12000

119

16.6

572

4.8

875

7.4

12000

114

18.1

595

5.2

909

8.0

12000

108

16.7

613

5.7

937

8.7

12000

15.3

610

6.2

933

9.5

12000

13.9

596

6.8

912

10.4

Table 5-11 Cruise performance, 8000 – 12000 ft

Issue 3 – July 2014 Page 5 - 11

Page 98

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

Altitude

Temperature

Weight 980 kg (2161 lb)

Ft (m)

°C

°F

Landing Distance

(ground touch)

Landing Distance

from 15 m (50 ft)

(m)

(ft)

(m)

(ft) 0 -5

266

873

479

1570

Std=15

282

925

507

1663

298

976

535

1755

2 000

(610)

-9

277

909

498

1635

294

964

528

1733

310

1018

558

1830

3 000

(914)

-11

284

931

510

1674

301

987

541

1775

318

1043

572

1875

4 000

(1219)

-13

291

953

527

1728

308

1011

559

1833

326

1069

591

1937

LANDING PERFORMANCE

At max. takeoff weight 980 kg (2161 lb) Without wind, flaps in landing position, engine at idle. Concrete, flat and dry runway

Table 5-13 Landing performance

Headwind influence:

 For 10 kt, multiply by 0.85  For 20 kt, multiply by 0.65  For 30 kt, multiply by 0.55

Tailwind influence:

 Add 10 % to distance for each additional 2 kt

Dry grass runway:

 Add 15 %

Page 5 - 12 Issue 3 – July 2014

Page 99

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

SECTION 6

WEIGHT AND BALANCE

The following nomograph is used to determine balance of the DR400. Remember that diesel and JET FUEL are heavier than AVGAS, and they

carry more energy per volume. Because the fuel in the Robin series is in an aft location, fuel consumption shifts the CG forward.

The DR400 delivers greater range and, at altitude, greater speed, than AVGAS-powered Robin of equivalent sea-level power ratings, for a given volume of fuel.

Issue 3 – July 2014 Page 6 - 1

Page 100

Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP

600

500

400

300

100

200

( )

100 150

200

100 150

200

110

600

214

150

922

Figure 6-1 Weight and balance

Page 6 - 2 Issue 3 - July 2014