Pilot’s Operating Handbook Supplement DR400/135CDI

Issue 3 – July 2014 Page vii 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 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page - viii Issue 3 – July 2014 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 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page ix 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 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page -x Issue 3 - July 2014 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page xi 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. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page -xii Issue 3 – July 2014 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 0 - 1 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. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 0 - 2 Issue 3 – July 2014 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 1 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. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 2 Issue 3 – July 2014 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 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 3 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 B- FADEC 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. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 4 Issue 3 – July 2014 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 ELE CTRONICS INTERNATIONAL C RDO & inst. Cabin Figure 1-1 Simplified block diagram Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 5 Figure 1-2 Simplified Block Diagram with FADEC backup battery installed Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 6 Issue 3 – July 2014 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. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 7 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 thermostat- controlled 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. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 8 Issue 3 – July 2014 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. 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 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. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 9 FUEL TANK (110 Litres) 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 ON OFF Option.fuel quantity CED 6 8 10 12 14 16 FUEL F ½ E FUEL 2 1 3 WESTACH Fuel low-level Fuel temperature Optional switch Optional tank 50 litres Engine-driven fuel pump F U E L F IL T E R Excess from fuel injectors Excess from fuel pump ENGINE VOLTS FUEL F ½ ½ E E FUEL FUEL 2 1 3 4 WESTACH F FADEC Figure 1-3/1 fuel system simplified diagram (Instrument panel models #1 and #2) Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 10 Issue 3 – July 2014 FUEL TANK (110 Litres) 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 ON OFF Option.fuel quantity F U E L F IL T E R CED Excess from fuel injectors Excess from fuel pump 6 8 10 12 14 16 FUEL F ½ E FUEL 2 1 3 WESTACH Fuel low-level Fuel temperature Optional switch Optional tank 50 litres VOLTS FUEL °C ½ E OAT FUEL 2 1 3 4 WESTACH F ENGINE FADEC Figure 1-2 Fuel system simplified diagram (Instrument panel model #3) Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 11 GMA340 KMD150 VHF/VOR KX155-42 1 5 6 8 10 11 12 13 15 2 7 9 16 17 18 19 29 28 27 26 25 24 24 30 31 32 34 36 35 37 42 39 20 22 22 23 23 33 3 4 38 40 41 43 44 R PM OP OT 23 6 50 140 bar C LO AD % tr /m in 2300 60 105 120 C C CT GT 100 O F F L R B O T H S T 2 0 7070 7 07 0 7060 4 0 40 20 21 14 5 1 45 QUARTZ-CHRONOME TE R LC - 2 RST ST /SP MODE SET DT / V TI ME R CL OCK 36 36 Figure 1-5 Instrument panel model #1  Note: The avionics instrument panel is shown as an example only. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 12 Issue 3 – July 2014 Instrument panel model #1 Pos Fonction Pos Fonction Pos Fonction 1 Airspeed indicator 16 Warning lights 31 Fuel tank valve 2 Gyro horizon 17 Lights test & day/night dimmer switch 32 Elevator trim control valve 3 Altimeter 18 Instrument panel light 33 Elevator trim position indicator 4 Turn coordinator 19 Safety switches: landing light, taxi light, strobe light, navigation light, pitot heat 34 Cabin heat / windshield defrost control 5 Directional gyro 20 Circuit breakers 35 Cabin heat 6 Rate of climb indicator 21 Electric throttle control 36 Instrument cut-off 7 Vacuum gauge 22 ANR jacks 37 VOR/LOC indicator 8 Engine indicator CED-125 23 Mike and headset jacks 38 Hourmeter 9 Parking brake control knob 24 Fresh air vent 39 Outside air temperature (OAT) 10 Westach triple indicator 25 Battery safety switch 40 Clock / chronometer 11 FADEC & alternator excitation battery 26 Key starter 41 Stall warning 12 Electrical fuel pump control 27 Glow light 42 Music jack 13 Alt. Induction air 28 FADEC test button 43 Auxiliary 12V 14 Force FADEC B 29 CED test / warning switch off 44 Avionics Master switch 15 Magnetic compass 30 CED-125 lighting knob 45 Alternator relay breaker Table 1-2 Instrument panel #1 description Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 13 1 5 6 8 10 11 12 13 14 15 2 7 9 16 17 18 19 29 28 27 26 25 24 24 30 31 32 34 36 35 37 42 39 20 22 22 23 23 33 3 4 38 40 41 43 44 RPM OP OT 23 6 50 140 bar C LOAD % tr/m in 2300 60 105 120 C C CT GT 100 O F F L R B O T H S T 20 7070 7070 7060 40 40 20 21 45 5 CHRONOMETER LC- 6 RST ST/SP MODE SET A DV 46 47 GMA340 KMD150 KX155-38 ELT AUTO MANUAL 46 Figure 1-6 Instrument panel model #2  Note: The avionics instrument panel is shown as an example only. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 14 Issue 3 – July 2014 Instrument panel model #2 Pos Fonction Pos Fonction Pos Fonction 1 Airspeed indicator 17 Lights test & day/night dimmer switch 33 Elevator trim position indicator 2 Gyro horizon 18 Instrument panel light 34 Cabin heat / windshield defrost control 3 Altimeter 19 Safety switches: landing light, taxi light, strobe light, navigation light, pitot heat 35 Cabin heat 4 Turn coordinator 20 Circuit breakers 36 Interphone on board 5 Directional gyro 21 Electric throttle control 37 VOR/LOC indicator 6 Rate of climb indicator 22 ANR jacks 38 Hourmeter 7 Vacuum gauge 23 Mike and headset jacks 39 Outside air temperature (OAT) 8 Engine indicator CED-125 24 Fresh air vent 40 Clock / chronometer 9 Parking brake control knob 25 Battery safety switch 41 Instrument cut-off 10 Westach triple indicator 26 Key starter 42 Instrument cut-off 11 FADEC & alternator excitation battery 27 Glow light 43 Auxiliary 12V 12 Electrical fuel pump control 28 FADEC test button 44 Avionics Master switch 13 Alt. Induction air 29 CED test / warning switch off 45 Alternator relay breaker 14 Force FADEC B 30 CED-125 lighting knob 46 ELT control 15 Magnetic compass 31 Fuel tank valve 47 Music jack 16 Warning lights 32 Elevator trim control valve Table 1-3 Instrument panel #2 description Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 15 1 5 6 12 11 9 10 13 15 28 2 7 22 27 26 29 30 20 18 17 16 8 37 37 19 25 23 33 43 32 42 34 36 47 47 48 48 24 3 4 44 46 40 RPM OP OT 23 6 50 140 bar C LOAD % tr /min 2300 60 105 120 C C CT GT 100 O F F L R B O T H S T 20 7070 7070 7060 40 40 20 21 14 5 CHRONOMETER LC- 6 RST S T/SP MODE SET AD V GMA340 KMD150 KX155-38 OAT °c ise i 35 45 41 49 GT X330 Figure 1-7 Instrument panel model #3  Note: The avionics instrument panel is shown as an example only. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 16 Issue 3 – July 2014 Instrument panel model #3 Pos Fonction Pos Fonction Pos Fonction 1 Airspeed indicator 17 Glow light 34 Clock / chronometer 2 Gyro horizon 18 FADEC test button 35 Hourmeter 3 Altimeter 19 CED-125 lighting knob 36 Circuit breakers 4 Turn coordinator 20 CED test / warning switch off 37 Fresh air vent 5 Directional gyro 21 Electric throttle control 40 Avionics Master switch 6 Rate of climb indicator 22 Parking brake control knob 41 Avionics circuit breakers 7 Vacuum gauge 23 Elevator trim control 42 VOR/LOC indicator 8 Battery safety switch 24 Elevator trim position indicator 43 ELT (optional) 9 FADEC & alternator excitation battery 25 Fuel tank valve 44 Instrument cut-off 10 Electrical fuel pump control 26 Lights test & day/night dimmer switch 45 Instrument cut-off 11 Westach quad indicator 27 Warning lights 46 Auxiliary 12V 12 Engine indicator CED-125 28 Magnetic compass 47 ANR jacks 13 Alt. Induction air 29 Instrument panel light 48 Mike and headset jacks 14 Alternator relay breaker 30 Safety switches: landing light, taxi light, strobe light, navigation light, pitot heat 49 Music jack 15 Force FADEC B 32 Cabin heat 56 Transfer valve control (optional) 16 Key starter 33 Cabin heat / windshield defrost control 57 Tank fuel T°C & level display select push-button (optional) Table 1-4 Instrument panel #3 description Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 17 1 5 6 12 11 9 10 13 15 28 2 7 22 27 26 29 30 20 18 17 16 8 37 37 19 25 23 33 43 32 42 34 36 47 47 48 48 24 3 4 44 46 40 RPM OP OT 23 6 50 140 bar C LOAD % tr /min 2300 60 105 120 C C CT GT 100 O F F L R B O T H S T 20 7070 7070 7060 40 40 20 21 31 14 5 CHRONOMETER LC- 6 RST S T/SP MODE SET AD V GMA340 KMD150 KX155-38 OAT °c ise i 35 45 41 49 GT X330 Figure 1-8 Instrument panel model #4  Note: The avionics instrument panel is shown as an example only. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 18 Issue 3 – July 2014 Instrument panel model #4 Pos Fonction Pos Fonction Pos Fonction 1 Airspeed indicator 17 Glow light 33 Cabin heat / windshield defrost control 2 Gyro horizon 18 FADEC test button 34 Clock / chronometer 3 Altimeter 19 CED-125 lighting knob 35 Hourmeter 4 Turn coordinator 20 CED test / warning switch off 36 Circuit breakers 5 Directional gyro 21 Electrical throttle control 37 Fresh air vent 6 Rate of climb indicator 22 Parking brake control knob 40 Avionics Master switch 7 Vacuum gauge 23 Elevator trim control 41 Avionics circuit breakers 8 Battery safety switch 24 Elevator trim position indicator 42 VOR/LOC indicator 9 FADEC & alternator excitation battery 25 Fuel tank valve 43 ELT (optional) 10 Electrical fuel pump control 26 Lights test & day/night dimmer switch 44 Instrument cut-off 11 Westach quad indicator 27 Warning lights 45 Instrument cut-off 12 Engine indicator CED-125 28 Magnetic compass 46 Auxiliary 12V 13 Alt. Induction air 29 Instrument panel light 47 ANR jacks 14 Alternator relay breaker 30 Safety switches: landing light, taxi light, strobe light, navigation light, pitot heat 48 Mike and headset jacks 15 Force FADEC B 31 Optional tank fuel T°C qty display select. 49 Music jack Table 1-5 Instrument panel #4 description Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 19 ”Three-display“ and “four-display“ instruments Example Of the Westach triple indicator installed on models #1 and #2 Example of the Westach quad indicator installed on model #3 Compact Engine Display CED-125 Figure 1-4 CED-125 detail Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 20 Issue 3 – July 2014 HEATING AND VENTILATION 2 3 4 5 1 1 1 1 6 9 10 1 7 7 8 8 Figure 1-5 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 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 1 - 21 Heating Control Settings Function Pulled Pushed Control 0 - Button Lock Heat ON/OFF ON OFF Control 1 Heating ON/OFF ON 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) Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 1 - 22 Issue 3 – July 2014 Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Issue 3 – July 2014 Page 2 - 1 SECTION 2 LIMITATIONS APPROVED OPERATION AIRSPEED LIMITATIONS km/h kt Vne, never exceed 270 146 Vno, normal operation 260 140 Va, maneuvering speed 215 116 Vfe, flaps extended limit speed 170 92 Table 2-1 Airspeed Limitations AIRSPEED INDICATOR MARKINGS km/h kt 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 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. Supplement POH DR400/120D, DR400/140B, DR400/180R, DR400/200R, DR400/RP Page 2 - 2 Issue 3 – July 2014 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 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) 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