Flight manual DR400 Equipped with TAE 125-02-099

PRECAUTIONARY LANDING ............................................................. 3-9 FIRE .................................................................................................. 3-10 Engine fire on the ground, during start-up .......................................... 3-10 Engine fire in flight ............................................................................. 3-10 Cabin fire ........................................................................................... 3-11 Electrical fire ...................................................................................... 3-11 ENGINE MALFUNCTION .................................................................. 3-13 Oil pressure too low (<2·3 bar in cruise or <1·2 bar at idle power) ..... 3-13 Oil temperature is too high ................................................................. 3-14 Coolant temperature too high ............................................................ 3-15 “Coolant level” warning light illuminates ............................................. 3-15 Gearbox temperature too high ........................................................... 3-15 Fuel temperature too low ................................................................... 3-15 Propeller rpm too high ....................................................................... 3-16 Fluctuations in propeller speed .......................................................... 3-16 ICING ................................................................................................ 3-17 ELECTRICAL POWER MALFUNCTION............................................ 3-18 ELECTRICAL SYSTEM MALFUNCTION .......................................... 3-19 INADVERTENT SPIN ........................................................................ 3-19 LOSS OF ELEVATOR CONTROL ..................................................... 3-19 LOSS OF ELEVATOR TRIM CONTROL ........................................... 3-20 LOSS OF FLAP CONTROL ............................................................... 3-20 SECTION 4 : NORMAL PROCEDURES........................................................4-1 NORMAL OPERATING SPEEDS ........................................................ 4-1 Optimal climb speed ............................................................................ 4-1 Maximum operating speed in turbulent air ........................................... 4-1 Never exceed speed ............................................................................ 4-1 Maximum speed with flaps................................................................... 4-1 Landing speed (final approach) ........................................................... 4-1 PRE-FLIGHT INSPECTION................................................................. 4-2 CABIN INTERIOR CHECK PRIOR TO START-UP ............................. 4-7 ENGINE STARTING ............................................................................ 4-8 AFTER ENGINE START.................................................................... 4-10 FADEC BACKUP BATTERY TEST: .................................................. 4-10 WARM UP ......................................................................................... 4-10 TAXIING ............................................................................................ 4-11 BEFORE TAKE OFF ......................................................................... 4-12 TAKE-OFF ......................................................................................... 4-15 Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 Revision 1 page ix Short take-off ..................................................................................... 4-15 Crosswind take-off ............................................................................. 4-15 CLIMB ............................................................................................... 4-16 Normal climb (flaps up) ...................................................................... 4-16 Best angle of climb ............................................................................ 4-16 CRUISE ............................................................................................. 4-16 DESCENT ......................................................................................... 4-17 Final approach or downwind .............................................................. 4-17 Short final .......................................................................................... 4-17 LANDING .......................................................................................... 4-18 Short field landing .............................................................................. 4-18 Normal landing .................................................................................. 4-18 Landing in crosswind or strong gusts ................................................. 4-19 Landing distances calculation example:............................................. 4-20 Going around..................................................................................... 4-21 AFTER LANDING .............................................................................. 4-21 ENGINE SHUT-DOWN...................................................................... 4-21 After engine shut-down ...................................................................... 4-21 STALLS ............................................................................................. 4-22 USE OF THE PARKING BRAKE ....................................................... 4-23 To apply the brakes ........................................................................... 4-23 To release the brakes ........................................................................ 4-23 SECTION 5 : PERFORMANCES....................................................................5-1 NOISE LIMITATION ............................................................................ 5-1 CALIBRATION OF THE AIRSPEED INSTALLATION.......................... 5-1 STALL SPEEDS .................................................................................. 5-2 WIND COMPONENT ........................................................................... 5-3 TAKE-OFF PERFORMANCE .............................................................. 5-4 Take-off distances, 980 kg (CAT N) ..................................................... 5-6 Take-off distances, 880 kg................................................................... 5-7 CLIMB PERFORMANCE ..................................................................... 5-8 Climb speeds....................................................................................... 5-8 Rate of climb, flaps retracted, 980 kg .................................................. 5-9 Rate of climb, flaps retracted, 880 kg ................................................ 5-10 Climb time, flaps retracted, 980 kg .................................................... 5-11 Climb time, flaps retracted, 880 kg .................................................... 5-12 Maximum angle of climb, flaps in take-off position ............................. 5-13 Glide performance ............................................................................. 5-13 CRUISE PERFORMANCE ................................................................ 5-14 At the maximum take-off mass of 980 kg (2161 lb) ............................ 5-15 LANDING PERFORMANCE .............................................................. 5-17 Flight manual DR400 Equipped with TAE 125-02-099 Page x 1002879 Edition 0 Revision 1 SECTION 6 : MASS AND BALANCE ............................................................6-1 USE OF THE NOMOGRAM ................................................................ 6-3 EXAMPLE of loading calculation (dotted lines on the diagram)............ 6-3 SECTION 7 : DESCRIPTION OF THE AIRCRAFT AND ITS SYSTEMS ....7-1 Airframe ............................................................................................... 7-1 Flap control switch ............................................................................... 7-1 Elevator system ................................................................................... 7-2 Aileron system ..................................................................................... 7-2 Rudder control ..................................................................................... 7-2 Control lock.......................................................................................... 7-2 Elevator trim ........................................................................................ 7-2 Roll compensation ............................................................................... 7-2 Yaw compensation .............................................................................. 7-3 Cabin layout......................................................................................... 7-3 Panel and centre console .................................................................... 7-4 Canopy ................................................................................................ 7-8 Seats ................................................................................................... 7-8 Seat belts ............................................................................................ 7-9 Luggage compartment ....................................................................... 7-10 Landing gear...................................................................................... 7-11 Braking system .................................................................................. 7-11 Parking brake .................................................................................... 7-12 Use of the brakes............................................................................... 7-12 Engine ............................................................................................... 7-13 Propeller ............................................................................................ 7-14 Electrical system ................................................................................ 7-14 Electrical circuit .................................................................................. 7-15 Re-initialisation of FADEC ................................................................. 7-17 Fuel / Fluids ....................................................................................... 7-18 Engine Oil .......................................................................................... 7-19 Fuel system ....................................................................................... 7-19 Fuel level gauges .............................................................................. 7-21 Tank selector ..................................................................................... 7-21 Heating and ventilation ...................................................................... 7-23 Lighting (optional) .............................................................................. 7-25 Stall warning system .......................................................................... 7-25 Pitot and static systems ..................................................................... 7-25 Avionics and navigation ..................................................................... 7-25 Headset and microphone installation ................................................. 7-25 Flight recorder (optional equipment) .................................................. 7-26 Emergency locator transmitter ........................................................... 7-26 Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 Revision 1 page xi Hour meter ........................................................................................ 7-26 External power socket ....................................................................... 7-27 SECTION 8 : MAINTENANCE OPERATIONS ............................................ 8-1 Introduction.......................................................................................... 8-1 Publications for the user ...................................................................... 8-1 Maintenance publications .................................................................... 8-1 Towing ................................................................................................. 8-1 Parking ................................................................................................ 8-1 Long-term parking ............................................................................... 8-2 Cleaning .............................................................................................. 8-3 SECTION 9 : REGISTER OF SUPPLEMENTS............................................ 9-1 List of installed supplements ................................................................ 9-2 Flight manual DR400 Equipped with TAE 125-02-099 Page xii 1002879 Edition 0 Revision 1 ABREVIATIONS sq ft .................................Square foot ft ......................................Foot In .....................................Inch Nm ..................................Nautical mile Km ..................................Kilometre M .....................................Metre cm ...................................Centimetre Kt.....................................Knot m/s ..................................Metres per second tr/mn ou rpm ..................Revolutions per minute Va....................................Manoeuvring speed VC ...................................Design cruise speed Vfe...................................Maximum flap extended speed Vne .................................Never exceed speed Vno .................................Maximum cruising speed Vso..................................Stall speed in landing configuration Vs1..................................Stall speed with flaps retracted VI.....................................Indicated airspeed Vlof ............................. Lift-off speed KIAS ........................... Knot Indicated AirSpeed (Indicated airspeed in knots) KTAS .......................... Knot True AirSpeed (True airspeed in knots) TAS ............................ True AirSpeed Km/h ...............................Kilometre par heure HP ...................................Horse Power HPa ................................Hectopascal In.Hg ...............................Inches of mercury Mbar................................Millibar Zp ....................................Pressure altitude I ......................................Litre Imp. gal ...........................Imperial gallon Us gal..............................US gallon Psi ...................................Pound per square inch Lb ....................................Pound Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 Revision 1 page xiii Kg ...................................Kilogram °C ....................................Degree Celsius °F ....................................Degree Fahrenheit V......................................Volt A......................................Amp TAE ............................ Thielert Aircraft Engines. FADEC ....................... Full Authority Digital Engine Control (Electronic engine management system) CED............................ Compact Engine Display Multifunction instrument for displaying the parameters of the CENTURION 2·0S engine. ISA ............................. International Standard Atmosphere COM ........................... Communication Transceiver ELT Emergency Locator Transmitter IFR ............................. Instrument Flight Rules NAV ............................ Navigation Indicator and Receiver AUDIO ........................ Audio Control Panel VFR ............................ Visual Flight Rules VHF ............................ Very High Frequency CPF ............................ Firewall LS6 ............................. Service Letter n°6 Flight manual DR400 Equipped with TAE 125-02-099 Page xiv 1002879 Edition 0 Revision 1 STANDARD ATMOSPHERE TABLE Example : Temperature = 20°C Pressure altitude = 1600ft Standard temperature = 12°C Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 Revision 1 page xv CONVERSION FACTORS nautical mile ............... x1·852 = ........ kilometres feet ............... x0·305 = ........ metres inches ............... x0·0254 = ........ metres inches ............... x25·4 = ........ millimetres feet/minute ............... x0·00508 = ........ metres/second gallons (US) ............... x3·785 = ........ litres gallons (imp.) ............... x4·546 = ........ litres quarts (US) ............... x0·946 = ........ litres knots ............... x1·852 = ........ km/h psi ............... x0·0689 = ........ bar in. Hg ............... x33·86 = ......... mbar lb ............... x0·453 = ........ kg (°F – 32) ............... x5/9 -32 = ........ °C kilometres ............... x0·539 = ........ nautical mile metres ............... x3·281 = ........ feet metres ............... x39·37 = ........ inches millimetres ............... x0·03937 = ........ inches metre/second ............... x197 = ........ feet/minute litres ............... x0·264 = ........ gallons (US) litres ............... x0·220 = ........ gallons (imp) litres ............... x1·057 = ........ quarts (US) km/h ............... x0·539 = ........ knots bar ............... x14·51 = ........ psi mbar ............... x0·02953 = ......... in. Hg kg ............... x2·205 = ........ lb °C ............... x9/5 + 32 = ........ °F Flight manual DR400 Equipped with TAE 125-02-099 Page xvi 1002879 Edition 0 Revision 1 Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 0-1 SECTION 0: GENERAL CONVENTIONS This document uses the following conventions and warnings. They must be strictly followed in order to avoid injuries to persons, damage to equipment, decreased operational safety of the aircraft or breakdowns that may result from abnormal operation. ▲ WARNING: Failure to observe these safety rules can result in injury or even death.  CAUTION: Failure to observe these particular notes and safety procedures may result in damage to the engine or to other equipment.  Note: Additional information for a better understanding of an instruction. THIS DOCUMENT IS FOR DR400 AIRCRAFT FROM AND INCLUDING SERIAL NUMBER 2669 AND IS VALID ONLY WHEN THE TAE 125-02- 099 POWERTRAIN IS INSTALLED. UPDATE AND REVISION OF THE DOCUMENT ▲ WARNING: Only an up to date flight manual allows safe operation. The current editions and revisions of this manual are available in the LS6 C.E.A.P.R  Note: The edition of this manual is indicated on the first page. Flight manual DR400 Equipped with TAE 125-02-099 Page 0-2 1002879 Edition 0 Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 1-1 SECTION 1 : DESCRIPTION GENERAL DIMENSIONS Maximum span ....................................................... (28 ft 7·3 in) 8·72 m Total length........................................................... (23 ft 8·66 in) 7·20 m Total height............................................................. (7 ft 3·79 in) 2·23 m Propeller ground clearance.......................................... (10·2 in) 0·26 m Flight manual DR400 Equipped with TAE 125-02-099 Page 1-2 1002879 Edition 0 Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 1-3 CABIN INTERIOR DIMENSIONS Length ...................................................................... (5 ft 3·8 in) 1·62 m Width (at shoulders) ................................................ (3 ft 11·2 in) 1·20 m Width (at armrests) ..................................................... (3 ft 7·3 in) 1·10 m Height ....................................................................... (4 ft 0·4 in) 1·23 m 4 places, accessible from both sides via the sliding canopy. WING Surface area ...................................................... (146·40 sq. ft.) 13·6 m² Profile ............................................................ NACA 43013.5 amended Aspect ratio .................................................................................... 5·35 Dihedral at the wingtips .................................................................... 14° AILERONS Surface area (per aileron) ......................................... (6·13 sq ft) 0·57 m² Span (per aileron) ..................................................... (5 ft 3·8 in) 1·62 m The ailerons are statically balanced. FLAPS Surface area (per flap) ............................................. (3·55 sq ft) 0·33 m² Span (per flap) ...................................................... (6 ft 7·72 in) 2·025 m HORIZONTAL TAILPLANE Surface area (stabilator) ............................................. (31 sq ft) 2·88 m² Total surface area including trim tab ......................... (2·8 sq ft) 0·26 m² Span .......................................................................... (10 ft 6 in) 3·20 m VERTICAL TAILPLANE Total surface area .................................................. (17·55 sq ft) 1·63 m² Surface area of the fin ................................................ (10·76 sq ft) 1 m² Surface area of the rudder ........................................ (6·78 sq ft) 0·63 m² Flight manual DR400 Equipped with TAE 125-02-099 Page 1-4 1002879 Edition 0 Landing gear Fixed tricycle Track ........................................................................ (8 ft 5·6 in) 2·58 m Wheelbase ................................................................... (5 ft 5 in) 1·65 m Tyre size ................................................................. 380 x 150 or 500 - 5 Shock absorber oil: ...................................................... MIL. H. 5606 - A NORME AIR 3520 Nose landing gear Tyre pressure ................................................................ (26 psi) 1·8 bar Shock absorber pressure ................................................... (72 psi) 5 bar Main landing gear Tyre pressure .................................................................... (29 psi) 2 bar Shock absorber pressure .................................................. (87 psi) 6 bar BRAKES The disc brakes are operated by independent hydraulic circuits on each main landing gear wheel. Hydraulic circuit oil ......................................................... MIL.H.5606 - A Norme AIR 3520 POWERPLANT Number of engines .............................................................................. 1 Number of cylinders ............................................................................. 4 Engine manufacturer: ............................. Technify Motors GmbH (TAE) Engine model:.............................................................. TAE 125-02-099 Configuration .................. Cylinders in-line, double overhead camshafts Power .................................................................... 135 HP at 2300 rpm Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 1-5 PROPELLER  Note : All performances in this manual are given with the MTV- 6-A-187/129 propeller. For other approved propellers, report to the documentation associated with the propeller. Manufacturer : .................................... MT Propeller Entwicklung Gmbh Model MTV-6-A-187/129 Diameter 1·87 m Number of blades 3 Type Constant Speed FUEL Total capacity .................................... 110 litres / 29 US gal / 24·2 Imp gal Total usable fuel volume .................... 109 litres / 28·7 US gal / 24 Imp gal Unusable fuel volume ........................... 1 litre / 0·26 US gal / 0·22 Imp gal Approved fuel types are described in SECTION 2 of this manual. The total capacity of the tanks may be extended to 160 l (42·24 US gal / 35·2 Imp gal) (159 l usable (42 US gal / 35 Imp gal)) by the installation of the optional supplementary 50 l (13·2 US gal / 11 Imp gal) tank. Main tank : Total capacity .................................... 110 litres / 29 US gal / 24·2 Imp gal Optional tank: Total capacity ...................................... 50 litres / 13·2 US gal / 11 Imp gal OIL The quantity of engine oil between the minimum and the maximum marks on the dipstick is 1 litre. Total engine capacity: Including the filters and the oil cooler: ......................................... 6·7 litres Approved types: ............................................. See Section 2 - Limitations  CAUTION: Only use an approved oil of the exact denomination! The approved grades of oil are described in SECTION 2 of this manual. Flight manual DR400 Equipped with TAE 125-02-099 Page 1-6 1002879 Edition 0 Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 2-1 SECTION 2 : LIMITATIONS CERTIFICATION STANDARDS The DR 400/140 B aircraft has been certified under 09.11.75 in the "NORMAL" and "UTILITY" categories conforming to the following technical conditions. - General Conditions of regulation AIR 2052 updated 6 June 1966. - Additional Conditions for conformity with FAR Part 23 Amendment 7. - Special conditions for the canopy release. The installation of the Technify engine is certified in the "NORMAL" and "UTILITY" categories conforming to the following technical conditions: JAR 23 Amendment 1 Initial Issue. TYPE OF USE The aircraft is approved for the following usage: - VFR by day in non-icing conditions; - VFR by night in non-icing conditions with optional supplementary equipment. (See Section 9) - IFR by day and night in non-icing conditions with optional supplementary equipment. (See Section 9) NOTE All speeds are indicated speeds unless otherwise indicated. Flight manual DR400 Equipped with TAE 125-02-099 Page 2-2 1002879 Edition 0 AUTHORISED USE LIMITING SPEED km/h KIAS Vne, never exceed 270 146 Vno, maximum in normal use 260 140 Va, maximum manoeuvering 215 116 Vfe, maximum with flaps extended 170 92 Table 2-1 - Limiting speeds AIRSPEED INDICATOR MARKINGS km/h KIAS Red line (never exceed) Vne 270 146 Yellow arc (Operate with caution and only in calm air) Vno-Vne 260-270 140-146 Green arc (Normal operation range) Vs1-Vno 99-260 53-140 White arc (Range with flaps extended) Vso-Vfe 87-170 47-92 Table 2-2 - Airspeed indicator markings PRACTICAL CEILING The DR400 with the TAE 125-02-099 engine is certified to 16,500 ft. (5,029 m). ▲ WARNING: You must comply with current regulations regarding maximum flight altitudes and take into account that high altitude flight can cause problems due to lack of oxygen. Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 2-3 LOAD FACTOR LIMITS AT THE MAXIMUM AUTHORISED MASS (2095 lb) 910 kg (category “U") : Flaps retracted ....................................................... n entre – 2·2 et + 4·4 Flaps extended .............................................................................. n = + 2 (2425 lb) 980 kg (category “N") : Flaps retracted ........................................................ n entre – 1·9 et + 3·8 Flaps extended .............................................................................. n = + 2 ▲ WARNING : Voluntary flight under negative g-loads is prohibited. Prolonged negative g-loads (a few seconds) may damage the propeller control and the engine by loss of oil pressure.  Note : The load factor limitations of the engine must also be respected. See the engine « Operation & Maintenance Manual » MAXIMUM AUTHORISED MASSES Cat. “U” Cat. “N” At take-off (2006 lb) 910 kg (2161 lb) 980 kg At Landing (2006 lb) 910 kg (2161 lb) 980 kg Table 2-3 - Maximum authorised masses Flight manual DR400 Equipped with TAE 125-02-099 Page 2-4 1002879 Edition 0 MASS AND BALANCE Figure 2-1 Mass and balance envelope Normal Category Front limit (12 % ref.): 0·205 m behind the reference plane at 720 kg Intermediate limit (24 % ref.): 0·410 m behind the reference plane at 980 kg Rear limit (33 % ref.): 0·564 m behind the reference plane at 980 kg Utility Category Front limit (12 % ref.): 0·205 m behind the reference plane at 720 kg Intermediate limit (27 % ref.): 0·462 m behind the reference plane at 910 kg Rear limit (33 % ref.): 0·564 m behind the reference plane at 910 kg Levelling ............................................................. upper fuselage longeron Reference plane (datum) ...................leading edge of the rectangular part of the wing. Reference chord .............................................................. (67·3 in) 1·71 m 500 550 600 650 700 750 800 850 900 950 1000 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 Masse (kg) % corde de reference Masse et CG DR400 / 135CDI CAT N CAT U Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 2-5 LOAD PLANNING (See the nomogram, SECTION 6) The mass of the engine oil in the sump and the mass of the unusable fuel must be included in the unladen mass of the aircraft. Mass kg (lb) Lever 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 tank 88 (194) 1·12 (44) Fuel, supplementary tank (if installed) 36 (79) 1·61 (63,4) Luggage (*) 40 (88) 1·9 (75) Table 2-4 - Loading * The position of the luggage has a very important influence on the balance because of the length of its lever arm. Be careful to assess the mass and balance accurately. LOAD LIMITS Number of occupants: Front seats .......................................................................................... 2 Rear seats ........................................................................................... 2 Luggage compartment : Maximum authorised mass ................................................. (88 lb) 40 kg Flight manual DR400 Equipped with TAE 125-02-099 Page 2-6 1002879 Edition 0 ENGINE LIMITS Manufacturer .............................................. Technify Motors GmbH (TAE) Model.............................................................................. TAE 125-02-099 Maximum take-off and continuous power......................... 99 kW (135 HP) Maximum take-off and continuous rotational speed ................... 2300 rpm Maximum recommended cruise ......................................................... 85%  Note : Unless otherwise specified, in this document all the values of rpm refer to the rotational speed of the propeller. Engine operational limits for take-off and continuous operation ▲ WARNING: It is not permitted to start the engine below the temperature limits specified below.  Note : The operating temperature limit is lowest temperature at which the engine can be started but not run at take- off speed. The required warming-up regime is described in section 4 of this supplement. OIL Oil temperature Minimum temperature for engine starting........................................ -32 °C Minimum operating temperature ...................................................... 50 °C Maximum operating temperature ....................................................140 °C Oil pressure Minimum oil pressure ..................................................................... 1·2 bar Minimum oil pressure (at take-off power) ....................................... 2·3 bar Minimum oil pressure during flight ................................................. 2·3 bar Maximum oil pressure .................................................................... 6·0 bar Maximum oil pressure (cold start < 20sec)..................................... 6·5 bar Maximum oil consumption ............................................................. 0·1 l/h Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 2-7 Types of approved oil* ▲ WARNING: ........ Only use oil that conforms to the exact specification. Engin oil: ........................................................... AeroShell Oil Diesel Ultra .............................................. AeroShell Oil Diesel 10W-40 ...................................................... Shell Helix Ultra 5W-30 ...................................................... Shell Helix Ultra 5W-40 Gearbox oil: ............................................... CENTURION Gearbox Oil N1 ..................... Shell Spirax S6 GXME 75W-80, API GL-4 ............................. Shell Spirax S4 G 75W-90, API GL-4 ................................................. Shell Spirax S6 ATF ZM *Refer to the latest version of Technify Motors instruction OM-02-02. COOLANT Coolant temperature Minimum temperature for engine starting ....................................... -32 °C Minimum operational temperature .................................................... 60 °C Maximum operational temperature ................................................. 105 °C Approved types of coolant* Coolant: .......................................... Water/antifreeze in the ratio of 50:50 Antifreeze: ......................................... BASF Glysantin Protect plus / G48 ................................... Mobil Antifreeze Extra / G48 ......... Comma Xstream Green – Concentrate / G48 .............................. Valvoline/Zerex Glysantin / G48 ........................... BASF Glysantin Alu Protect / G30 .............................. Valvoline/Zerex Glysantin / G30 ................................. BASF Glysantin Protect / G05 .............................. Valvoline/Zerex Glysantin / G05 Flight manual DR400 Equipped with TAE 125-02-099 Page 2-8 1002879 Edition 0 *Refer to the latest version of Technify Motors instruction OM-02-02. GEARBOX Gearbox temperature Minimum operating temperature ..................................................... -30 °C Maximum operating temperature ....................................................120 °C Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 2-9 FUEL Minimum temperatures for fuel in the tanks: Carburant Minimum acceptable temperature in the tank before take-off. Minimum acceptable temperature in the tank during flight. Jet A-1, JET A, Fuel n°3 JP-8, JP-8+100, TS-1 - 30 °C - 35 °C Diesel Above 0 °C - 5 °C Table 2-5 - Temperature limits for fuel in the tank ▲ WARNING : The above applies to mixtures of diesel and Jet-A1 in the tank: If the proportion of diesel in the tank exceeds 10%, the temperature limitations for diesel fuel alone must be respected. If there is any doubt about the composition of the fuel in the tank then it should be assumed to be diesel. Flight manual DR400 Equipped with TAE 125-02-099 Page 2-10 1002879 Edition 0 Approved fuel types ▲ WARNING: The use of unapproved fuels and additives can cause a dangerous engine malfunction. Main tank * Fuel .........................................................................JET-A1 (ASTM 1655) Alternative fuel .......................................................... Diesel (DIN EN 590) Additives for diesel fuel: Liqui Moly, « Diesel Fliess Fit » n° 5130 ...........................................................JET-A (ATSM 1655) ....................................................... JP-8 (MIL-DTL-83133) ............................................. JP-8+100 (MIL-DTL-83133E) ............................................. Jet Fuel n°3 (GB 6537-2006) ..................................................... TS-1 (GOST 10227-86) .................................. TS-1 (GSTU 320.00149943.011-99) Optional tank (50 litres) : Fuel .............................................................. JET-A1 (ASTM 1655) ONLY *Refer to the latest version of the Technify Motors instruction OM-02-02. Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 2-11 ENGINE INSTRUMENT MARKINGS The engine parameters of the TAE 125 system that must be monitored appear on the CED-125 (Compact Engine Display: the multifunction instrument for the display of engine parameters) The operational ranges of the various engine parameter are shown in the following table: Instrument Red zone Yellow zone Green zone Yellow zone Red zone Tachometer (rpm) 0 - 2300 > 2300 Oil pressure (bar) 0 – 1·2 1·2 – 2·3 2·3 – 5·2 5·2 – 6·0 > 6·0 Coolant temperature (°C) < -32 -32… +60 60 - 101 101 - 105 > 105 Oil temperature (°C) < -32 -32… +50 50 - 125 125 - 140 > 140 Gearbox temperature (°C) < 115 115 - 120 > 120 Power (%) 0 - 100 Table 2-6 - Engine instrument markings  Note : If an engine parameter enters the yellow or red range, the CED warning light illuminates. The light can be extinguished by pressing the « CED-Test/Ack » (‘Ack’ = ‘acknowledge’) button. Pressing the button for more than one second triggers an automatic test of the instrument. EARTHING BEFORE AND DURING TANK FILLING Ground the exhaust system to eliminate electrostatic charges. Flight manual DR400 Equipped with TAE 125-02-099 Page 2-12 1002879 Edition 0 OPERATIONAL LIMITS IN THE "U" CATEGORY Within the limits of this category, the following manoeuvres are permitted: - Steep turns (60°) - Lazy eights - Chandelles - Stalls (maximum pitch 20°, wings horizontal, balanced flight) These manoeuvres must be carried out under the following conditions: - Rear seats unoccupied - Entry and exit speeds must be within the normal range - Maximum recommended entry speed: 116 kt (215 km/h) ▲ WARNING: Intentional spins are prohibited! ▲ WARNING: Intentional negative g manœuvres are prohibited! RUNWAY SURFACE This aircraft can take-off and land on any runway surface.  CAUTION: unprepared or rough runways may have holes, bumps or stones that could damage the propeller, the fairings or other projecting parts. Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 2-13 MARKING The diagrams below represent the markings that must be displayed. These markings can be placards or directly printed on the desk. The shape, size, typeface and colours may vary. Figure 2-2 - Near the cap of the main tank: 110 litres JET/DIESEL Figure 2-3 - Near the cap of the supplementary tank, if installed Figure 2-4 - On the inside of the oil-filler access hatch Flight manual DR400 Equipped with TAE 125-02-099 Page 2-14 1002879 Edition 0 Figure 2-5 - Near the distress beacon Figure 2-6 - On the access hatch of the ground power socket (if installed) on the starboard side of the aircraft.  Note : The socket is non-reversible to prevent polarity inversion. NO HOLD NO STEP Figure 2.7 - On the stabilator trim tabs On the flaps Figure 2-8 - Annunciator panel Figure 2-9 - Near the cabin heating controls Flight manual DR400 Equipped with TAE 125-02-099 1002879 Edition 0 page 2-15 Figure 2-10 - Next to the respective switches Figure 2.11 - Next to the respective indicator or gauge Figure 2-12 - Nest to the CED Figure 2-13 - Next to the respective buttons Figure 2-14 - Near the alternate air plunger Figure 2-15 - Near the gauge of the optional fuel tank, if installed. Flight manual DR400 Equipped with TAE 125-02-099 Page 2-16 1002879 Edition 0 Figure 2-16 - Near the transfer plunger of the supplementary fuel tank if installed. Figure 2-17 - On the central console, near the appropriate switches Figure 2-18 - Near the parking brake knob Figure 2-19 - On the right side of the cabin.