Flight and operational manual TL 3000 SIRIUS

Main wheel‐spacing 2.17 m Wheelbase 1.53 m Undercarriage wheel dimensions 400 X 100 Atmospheric pressure in the tyres 2.0 kPa Nose wheel rebound Coil spring Main undercarriage rebound Tyres, undercarriage leg resilience Brakes Hydraulic disc brakes Fuel tank volume 130 lit res Empty aircraft weight kg Wing mean aerodynamic chord length (MAC) MAC = 1230 mm Engine Rotax 912 ULS, a boxer type four‐stroke four‐cylinder, the heads of cylinders are liquid‐cooled and the cylinders are air‐cooled. The engine is integrated with a reducer and two carburettors. It is equipped with a double contactless condenser ignition. Propeller The aircraft is equipped with a three‐blade, DUC ground adjustable pitch propeller. Rescue system GRS 473 Flight and operational manual TL 3000 SIRIUS Page 10 1.6 Three‐view drawing Flight and operational manual TL 3000 SIRIUS Page 11 Section 2 Operational limitations 2.1 Introduction 12 2.2 Operating speeds 12 2.3 Speed indicator 13 2.4 Power plant 13 2.5 Power plant instruments markings 15 2.6 Other instruments markings 16 2.7 Weight 16 2.8 Centre of gravity position 17 2.9 Approved manoeuvres 19 2.10 Flight multiples 19 2.11 Aircrew 19 2.12 Types of operation 20 2.13 Fuel 20 2.14 Other limitations 20 2.15 Limitation placards 20 Flight and operational manual TL 3000 SIRIUS Page 12 2.1 Introduction Section 2 includes operational limitations, instruments markings, and basic placards (labels), necessary to ensure safe operating of the aircraft, its engine, standard systems and equipment. 2.2 Flight speeds Speed IAS(km/ h) NOTE VNE Maximum never exceed speed 253 Do not exceed this speed in any flight regime VH Maximum speed of horizontal flight at max. steady engine power 226 Engine RPM 5400 per min VOPT Optimal cruising speed 178 Engine RPM 4500 per min VA Design manoeuvring speed 150 Above this speed use 1/3 rudder deflection and do not make sudden steering interventions – it could result in aircraft overload. Maximum speed with the elevated flaps Flaps position 1 140 Flaps position 2 120 VFE Flaps position 3 105 Do not cross this speed with the flaps elevated in positions 1, 2, and 3 Flight and operational manual TL 3000 SIRIUS Page 13 2.3 Speed indicator markings Speed indicator markings and colour code significance are shown in the table: Marking Value or range [IAS km/h] Significance White arch 58‐140 Operating range with the elevated flaps Green arch 66‐200 Normal operational range. The upper limit is the maximum structural cruising speed Yellow arch 200‐253 Increased caution regime! Manoeuvres must be performed with caution and only in a calm atmosphere Radial red line 230 Maximum speed in all flight phases 2.4 Power plant Engine manufacturer: BOMBARDIER‐Rotax‐GmbH (Austria) Engine model: Rota x‐912UL Rota x‐912ULS Engine type: four‐stroke four‐cylinder boxer type Maximum power : 80 hp 100 hp Full take‐off power limit 5800 rpm 1/min (5 m in) Max. permanent rotation speed 5500 rpm 1/m in Idle run rotation speed approx. 1400 rpm 1/ min Maximum cylinder head temperature at the measuring point 150 ºC (300 ºF) 135 ºC (284 ºF) Oil temperature:‐ operating ‐ minimum ‐ ma xim um 90‐110 ºC (190‐250 ºF) 50 ºC (120 ºF) 140 ºC (285 ºF) 90‐110 ºC (190‐250 ºF) 50 ºC (120 ºF) 130 ºC (266 ºF) Flight and operational manual TL 3000 SIRIUS Page 14 Exhaust fume temperature: ‐ maximum starting ‐ ma xi mum ‐ operating, at the distance of 70 mm from the cylinder 880 ºC (1620 ºF) 850 ºC (1560 ºF) 800 ºC (1470 ºF) Oil pressure: ‐ operating ‐ minimum ‐ ma ximum 2,0‐5,0 bar (29‐73 psi) over 3500 RPM 0,8 bar (12 psi) under 3500 RPM 7 bar (100 psi); max. pressure is short‐time tolerable during a cold engine start Fuel pressure: ‐ operating ‐ ma ximum 0,15‐0,4 bar (2,2‐5,8 psi ) 0,4 bar (5,8 psi ) Fuel: (European norm) EN 228 super min. 90 octanes EN 228 super min. 95 oct. Oil: According to API „SG“ or higher (Castrol GTX 3) Minimum engine starting temperature ‐25 C Maximum engine starting temperature +50 C Propeller manufacturer : DUC Hélices, Len till y‐Fr an ce Propeller type: DUC three‐blade, ground adjustable pitch propeller Caution: This engine type is not certified as an aviation engine. In spite of the maximum attention paid to its manufacturing, the engine can fail anytime and the pilot is fully responsible for the consequences of such failure. Flight and operational manual TL 3000 SIRIUS Page 15 2.5 Power plant instrument markings Instrument Red arch ‐ lower limit Yellow arch Green arch Yellow arch Red arch ‐ upper limit Tachometer 1400‐5500 5500‐5800 5800 Fuel pressure 0 – 0,7 0,7‐2,5 2,5‐5,8 5,8‐6,5 6,5‐7,3 Filling pressure (INHG) 0 ‐ 31 31 ‐ 32 32 – 33,3 Oil pressure (PSI) 0 ‐ 15 15 ‐ 20 20 ‐ 90 90 ‐ 95 95 ‐ 99 Oil temperature (°C) 0 ‐ 50 50 ‐ 90 90 ‐ 110 110 ‐ 140 Cylinder temperatur e (°C) 30 ‐ 40 40 ‐ 50 50 ‐ 122 122 ‐ 130 130 ‐ 140 Exhaust fume temperature (°C) 150 ‐ 205 205 ‐ 815 815 ‐ 870 870 NOTE: Green arch ‐ normal operation Yellow arch –increased attention range Red arch – lower and upper limits Flight and operational manual TL 3000 SIRIUS Page 16 2.6 Other instrument markings Fuel level indicator Minimum start fuel volume 10 litres Inexhaustible volume 2x1 litres 2.7 Weight Maximum take‐off weight 472,5 kg Maximum fuel weight 93,5 kg Maximum one seat load 90 kg Maximum load weight behind the seats 25 kg Minimum crew weight 60 kg Flight and operational manual TL 3000 SIRIUS Page 17 2.8 Centre of gravity position Empty aircraft weight determined by weighing kg Instructions for aircraft centre of gravity determination from the diagram hereunder: 1) Subtract the centre of gravity position shift increment for each individual item (crew, luggage, fuel) on the graduated scale. 2) Sum up so determined increments and add them to the empty aircraft centring. 3) The total gives the aircraft centre of gravity position at the chosen payload of each item given in MAC % and must fit within the allowed centre of gravity position range. CAUTION: Aircraft centre of gravity determination from the diagram is only approximate. Precise centre of gravity determination requires aircraft weighing connected with the calculation stated in the chapters 6.3 and 6.4 of this manual. Flight and operational manual TL 3000 SIRIUS Page 18 Flight and operational manual TL 3000 SIRIUS Page 19 2.9 Approved turns This aircraft is approved for the ultra light category. Any turns necessary for the normal flight, stall training up to 30° stalling over the horizon and sharp turns u p t o 6O° tilt. WARNING: This aircraft category is allowed only for non‐acrobatic operations. Intended spins and drops are forbidden! 2.10 Flight multiples 2.11 Crew The crew consists of 1 o r 2 pilots. Minimum crew weight is 60kg. In case this condition is not met, it is necessary to attach appropriate weight to the second seat. Maximum one seat payload is 90 kg. Flight and operational manual TL 3000 SIRIUS Page 20 WARNING: Watch the maximum take‐off weight of 472.5 kg 2.12 Types of operations The aviation regulations and aircraft equipment limit this aircraft operating only to the VFR flights during the daytime. WARNING: IFR flights and flights in the icing conditions are forbidden. This aircraft is minimally equipped with the following flight and navigation instruments – airspeed indicator, altimeter, compass, relative pitch indicator – and engine control instruments ‐ manometer, thermometer, tachometer a fuel level indicator for each fuel tank. 2.13 Fuel This aircraft is equipped with 2 fuel tanks; one tank in each wing. Each fuel tank volume is 65 litres. The total fuel volume is 130 litres. Minimum start fuel volume is 2x10 litres Inexhaustible volume 2x1 litres Used fuel BA 95 Nat ural 2.14 Other restrictions It is forbidden to open the cabin door when airborne and smoke onboard. In case that the aircrarft is being operated while OAT is more than 20 °C dismount the carbon heating cover and hot airintake hose of the cabin heating which is placed in the engine compartment on the radiator (it the aircraft is equipped with it). 2.15 Restriction placards Flight and operational manual TL 3000 SIRIUS Page 21 Flight and operational manual TL 3000 SIRIUS Page 22 Section 3 Emergency procedures 3.1 Introduction 23 3.2 Engine failure 23 3.3 In‐flight engine restart 24 3.4 Engine on fire, smoke in the cabin 24 3.5 Descending flight 25 3.6 Emergency landing 25 3.7 Unintentional spin recovery 25 3.8 Other emergency cases 26 Flight and operational manual TL 3000 SIRIUS Page 23 3.1 Introduction Section 3 provides the procedures and special processes in case of emergency that can occur. If the pre‐flight preparation and maintenance are properly conducted, the aircraft and engine emergency cases will be exceptional. To cope with emergency, the basic procedures described in this section can be executed. 3.2 Engine failure 3.2.1 Engine failure during take‐off 1. Engine control lever ‐ turn down to idle run 2. Brake intensively 3. Ignition ‐ switch off 3.2.2 Engine failure during the flight at the altitude up to 200m 1. Speed glide at the speed of 120 km/h 2. Altitude up to 50 m land in the take‐off direction 50 m and above choose an appropriate area without obstacles 3. Flaps as necessary 4. Fuel tap close 5. Ignition 2x switch off 6. Main switch switch off 7. Balancing as necessary 8. Safety belts fasten 3.2.3 Engine failure during the flight at the altitude above 200m and above 1. Start up the engine see section 3.3 2. If the engine fails to start running follow the procedure provided in the paragraph 3.2.2 WARNING: Never allow the instrument airspeed to drop under 70 km/ h Flight and operational manual TL 3000 SIRIUS Page 24 3.3 In‐flight engine restart 1. Speed glide at the speed of 140 km/h 2. Altitude min. 200m 3. Ignition 2 x switched on 4. Main switch switched on 5. Fuel level indicator check the fuel level 6. Fuel tap open Left or Right fuel tank 7. Gas lever set to ¼ of the throttle 8. Balancing as necessary 9. Starter push the starter button If the engine fails to restart, follow the procedure provided in the paragraph 3.2.2 3.4 Engine on fire, smoke in the cabin 3.4.1 A fire on the ground with the engine running 1. Fuel tap close 2. Gas lever full throttle 3. Ignition 2x switch off 4. Main switch switched off 5. Leave the aircraft and extinguish the fire 3.4.2 Inflight fire 1. Heating close 2. Fuel tap close 3. Gas lever full throttle 4. Ignition 2x switch off after stopping the engine 5. Main switch switched off 6. Area selection land at the closest airfield, if the airfield is too distant, choose an emergency landing area 7. Emergency landing the procedure is described in the paragraph 3.6.1 8. Leave the aircraft and extinguish the fire NOTE: Do not start up the engine after fire extinguishing. Flight and operational manual TL 3000 SIRIUS Page 25 3.5 Descending flight 1. Airspeed 140 km /h 2. Flaps closed 3.6 Emergency landing 3.6.1 Emergency landing 1. Emergency landing area suitable area selection 2. Wind direction and strength choose the optimal landing direction 3. Fuel tap close 4. Ignition switch off 5. Main switch switched off 6. Flaps as necessary 7. Balancing as necessary 8. Safety belts fasten 3.6.2 Landing with the damaged undercarriage 1. In case of main undercarriage leg failure, land on the undamaged leg side; hold the aircraft on this side above the ground as long as possible by using the elevators. 2. In case of nose gear damage hold the fuselage front elevated as long as possible. NOTE: In order to decrease the landing speed as much as possible, try to land in a suitable area and against the wind. 3.7 Unintentional spin recovery 1. Gas lever idle run 2. Pitch controls set to the neutral position 2. Rudder step on the pedal against the rotation direction 3. Roll controls push and hold till the rotation stops 4. Rudder set the rudder to the neutral position as soon as the rotation stops 5. Roll controls pull and recover from the dive Flight and operational manual TL 3000 SIRIUS Page 26 WARNING: Intentional spins are forbidden! 3.8 Other emergency cases 3.8.1 Ultimate aircraft control loss In case that all previous procedures fail use the rescue system. In general, it is recommended to use the rescue system in case of ultimate aircraft control loss, for example in the event of its destruction. 3.8.2 Vi br ations 1. Gas lever set the engine regime with the lowest vibration level 2. Landing at the closest airfield or emergency landing according to paragraph 3.6.1 3.8.3 Carburettor icing 1. Airspeed 140 km /h 2. Gas lever set to ¼ of the throttle 3. Icing area leave 4. After leaving the icing area, increase the engine power output gradually. If the engine power output loss still occurs, land at the closest airfield or choose emergency loading according to paragraph 3.6.1 CAUTION: Carburettor icing is indicated by the temperature increase or engine power output decrease. 1. Activation handle pull 2. Safety belts fasten 3. Fuel tap close 4. Other switches Switch off Flight and operational manual TL 3000 SIRIUS Page 27 Section 4 Normal procedures 4.1 Introduction 28 4.2 Pre‐flight inspection 28 4.3 Normal procedures and action list 30 4.3.1 Cockpit post‐boarding actions 30 4.3.2 Pre‐start actions and starting up 31 4.3.3 Engine test 31 4.3.4 Taxiing 32 4.3.5 Pre‐takeoff actions 32 4.3.6 Take‐off 32 4.3.7 Climb 32 4.3.8 En route flight 33 4.3.9 Descent 33 4.3.10 Pre‐landing actions 33 4.3.11 Landing 34 4.3.12 Repeated landing 34 4.3.13 Post‐landing actions 34 4.3.14 Engine stopping 34 Flight and operational manual TL 3000 SIRIUS Page 28 4.1 Introduction Section 4 provides an action list and recommended procedures. 4.2 Pre‐flight inspection Execute the inspection systematically so that nothing is omitted. It is recommended to conduct inspection as shown in the picture and further according to the procedure hereunder. The inspection starts with the engine and continues clockwise around the aircraft. 1. Engine Dismount the engine cowling upper art Engine cowling inspection Engine bedding attachment status Fuel and electrical systems inspection Air and fuel filters inspection Flight and operational manual TL 3000 SIRIUS Page 29 Oil and cooling liquid cooler tightness inspection Sparkling plug tightness inspection Carburettor and suction silencer interconnection inspection Exhaust attachment status inspection Motor oil level inspection Expansion flask cooling liquid level inspection Fuel filter defecation Assemble engine cowling 2. Propeller: Attachment and blades status inspection Propeller cone attachment inspection In case the engine is cold, conduct several rotations in its rotation sense. WARNING: Rotate the propeller only when both ignition circuits and main switch are switched off 3. Undercarriage: ƒ Dismounting the aerodynamic cover lower part and nose gear inspection ƒ Inspection of the main undercarriage wheels self ‐fusing nut and the brake stirrup self ‐fusing nut above it and their paint securing ƒ Main undercarriage aerodynamic covers inspection ƒ Inspection of the atmospheric pressure of 25kPa (2.5 kp/cm 2 ) in the tyres and their status 4. Right wing: ƒ Surface and leading edge status inspection ƒ Centroplane node points and wing struts inspection ƒ Landing and positioning lights inspection ƒ Flap and aileron attachments inspection ƒ Fuel tank cap closure inspection. 5. Airframe right hand side: ƒ Surface, airframe or paint cracks inspection ƒ Static pressure sensors status and cleanliness inspection Flight and operational manual TL 3000 SIRIUS Page 30 6. Tail‐plane: ƒ Surface inspection ƒ Attachment inspection ƒ Tailplane and rudder swivel pins clearance inspection ƒ Trim tab controls inspection 7. Airframe left hand side: The same as for the airframe right hand side. 8. Left wing: The same as for the right wing ƒ Pitot tube – cleanliness of the openings 9. Cabin: ƒ Ignition – switched off ƒ Main switch – switched on ƒ Instruments inspection ƒ Steering correct function and clearance inspection ƒ Mutual flaps lifting inspection ƒ Cleanliness inspection ƒ Remove or fix the loose objects ƒ Safety belts inspection ƒ Door and locking inspection 4.3 Normal procedures and action list 4.3.1. Cockpit post‐boarding actions 1. Foot controls clearance inspection 2. Hand controls clearance inspection 3. Balancing freedom of action 4. Gas lever freedom of action 5. Fuel tap closed 6. Fuel level indicators fuel level check 7. Instruments status inspection 8. Ignition switched off 9. Main switch switched off 10. Other switches switched off 11. Activation handle check 12. Activation handle fuse remove Flight and operational manual TL 3000 SIRIUS Page 31 NOTE: Release the flag‐fitted rescue system activation handle operational fuse – turn the handle towards both sides approximately 45° around the rotation axis and ensure there is a sliding contact between the handle and console casing 4.3.2 Pre‐start actions and starting up 1. Fuel tap open 2. Main switch switch on 3. Ignition 2x switch on 4. Instruments switch on 4. Gas lever idle run, eventually 10 % of power output 5. Balancing on the centre 6. Choke according to the engine temperature 7. Area in front of the propeller check clearance 8. Starter push 9. After start‐up idle run 10. Other instruments switch on 11. Choke push in 12. Engine heating see paragraph 4.3.3 Caution: Continue starting during maximum 10 sec., cool down for 2 min after that. 4.3.3 Engine test The engine warm up procedure, and engine and ignition tests are in detail described in the engine manual. Continue engine warming up for approximately 2 min. at 2000 rpm and continue at 2500 rpm until the oil temperature of 50 ° C is achieved. ƒ Ignition test at 4.000 rpm, each loop rotation speed drop cannot exceed 300 rpm; the rotation speed difference between the loops cannot exceed 120 rpm. ƒ Gas lever at 5.000 rpm during 30 seconds 3x and smoothly transit from the idle run to the maximum rotation speed (5.800 rpm) ƒ Set idle run Flight and operational manual TL 3000 SIRIUS Page 32 Caution: Watch engine pressure and temperature; they must fall within the operating values at all points. 4.3.4 Taxiing 1. ICOM Radio station switch on Maximum speed 15 km/h. Execute the turns by the main undercarriage wheels braking. Caution: Never taxi with the door open, it could result in the door hinge damage. Caution: While taxiing and systematicly applied brakes could decrease the brake effectivity due to the hydraulic liquid overheating. 4.3.5 Pre‐takeoff actions 1. Brakes brake 2. Balancing on the centre 3. Flaps Level 1 – 10.5° 4. Instruments at operating values 5. Safety belts buckled and fastened 4.3.6 Take‐off 1. Brakes release 2. Gas lever smoothly to the maximum ƒ Maintain the straight direction by the foot pressure on the rudder pedals ƒ relieve the nose wheel slowly at the airspeed of 50 km ƒ the aircraft starts to rise at the airspeed of 75 km/hour, push and hold till the airspeed of 130 km/hour is achieved ƒ transit smoothly to ascent at the airspeed of 120 km/hour ƒ set the engine rotation speed 3. Main undercarriage wheels brake 4. Flaps 50m close 4.3.7 Climb 1. Gas lever permanent maximum power output 2. Airspeed 120 km /hour Flight and operational manual TL 3000 SIRIUS Page 33 3. Balancing equilibrate 4. Instruments values checking 4.3.8 En route flight 1. Gas lever cruising regime 2. Balancing equilibrate WARNING: Do not execute sharp turns while flying at a low airspeed under 130 km/hour, Do not execute rapid aircraft controls motions while flying at a high airspeed above 150 km/hour and use maximum 1/3 of their scale. 4.3.9 Descend 1. Gas lever idle run 2. Balancing equilibrate 3. Airspeed 150 km /h 4. Instruments at the operating values CAUTION: To prevent engine overcooling when descending from higher flight levels, do not decrease to idle run but descend with a moderate engine thrust at the airspeed of 150 km/ hour. 4.3.10 Pre‐landing actions 4.3.10.1 Tailwind position actions 1. Safety belts 2. Fuel level indicators fasten check 3. Fuel tap Shift to the tank with the higher fuel level 4. Brakes check 5. Space between the round turns 3 and 4 check 6. Landing area check 4.3.10.2 Actions after third turn 1. Airspeed 140 km /h 2. Flaps grade 1 ‐ 10.5° 3. Balancing equilibrate 4. Final area check Flight and operational manual TL 3000 SIRIUS Page 34 4.3.10.3 Actions for the final 1. Airspeed 120 km /h 2. Flaps grade 2 ‐ 28° 3. Balancing equilibrate Decision altitude 4. Airspeed 105 km /h 5. Flaps grade 3 ‐ 45° 4.3.11 Landing At the speed of 75 km /hour, touchdown with the main undercarriage. H old the aircraft only on the main undercarriage by pulling as long as possible. The nose wheel will ground by itself at the speed of 60 km /hour. 4.3.12 Repeated landing 1. Gas lever full throttle 2. Flaps grade 1 – 10.5° 3. Balancing equilibrate 4. Airspeed 130 km /h 5. Flaps retract 4.3.13 Post‐landing actions 1. Gas lever as needed 2. Flaps retracted 3. Balancing on the centre 4.3.14 Engine stopping 1. Gas lever idle run 2. ICOM radio station switch off 3. Instruments switch off 4. Ignition switch off 5. Other switches switch off 6. Main switch switch off 7. Fuel tap close WARNING: Secure the rescue system before leaving the cockpit. Flight and operational manual TL 3000 SIRIUS Page 35 Section 5 Performances 5.1 Introduction 36 5.2 Specified data 36 5.2.1 Airspeed indication system error correction 36 5.2.2 Stall speed 37 5.2.3 Take‐off 37 5.2.4 Landing 37 5.2.5 Climb 38 5.2.6 Cruising flight 38 5.2.7 Endurance 38 5.2.8 Wind effect during the take‐off and landing 39 Flight and operational manual TL 3000 SIRIUS Page 36 5.1 Introduction Section 5 provides the airspeed indication system calibration data, stall speed, performances and other information. The data contained in this section have been calculated from the results of aircraft and power plant flight tests conducted in a good technical status and using usual piloting techniques. If not specified otherwise, the performances presented in this section are valid for the aircraft maximum take‐off weight and calculated for the conditions of the International Standard Atmosphere (ISA). 5.2 Specified values 5.2.1 Airspeed indication system error correction IAS (km/h) Cruising configuration (flaps closed ) Take‐off configuration (flaps to 10.5°) Landing configuration (flaps to 45°) CAS (km/ h) 50 58 55 60 67 66 70 76 76 80 85 86 86 90 93 95 97 100 102 105 107 110 110 114 117 120 119 124 127 130 128 134 140 136 144 150 146 160 155 170 164 180 174 190 183 200 193 210 203 220 213 230 223 240 234 250 244 Flight and operational manual TL 3000 SIRIUS Page 37 5.2.2 Stall speeds Warning speed Stall speed Drop Flaps position Engine power IAS (km/ h) CAS (km/ h) IAS (km/ h) CAS (km/ h) Closed Idle run 68 75 60 69 Take‐off (10.5° ) Idle run 67 73 56 63 Horizontal flight Landing (45°) Idle run 66 72 53 59 NOTE: The stall is indicated by aircraft pitching down, the aircraft is fully under control and horizontal flight can be resumed without a significant altitude loss. 5.2.3 Take‐off Take‐ off run distance (m) Take‐off distance over a 15‐metre obstacle (m) Grass 103 283 NOTE: The take‐off distance stated in the table above is valid in the sea level and International Standard Atmosphere conditions and for the specified runway type. 5.2.4 Landing Landing distance over a 15‐metre obstacle (m) Of this landing run distance with the brakes braking Grass 246 85 NOTE: The landing distance stated in the table above is valid in the sea level and International Standard Atmosphere conditions and for the specified runway type. Flight and operational manual TL 3000 SIRIUS Page 38 5.2.5 Climb Optimal climb speed (km/ h) Rate of climb (m/ s) 120 4,82 NOTE: The climb stated in the table above is valid in the sea level and International Standard Atmosphere conditions and for the specified runway type. 5.2.6 Cruising flight Regime Economical cruise Maximum permanen Maxi mum Take‐off Time limitation unlimited unlimited 5 minutes max. Engine rotations 4500 5500 5800 Flight altitude (ft) IAS (km/ h) IAS (km/ h) IAS (km/ h) 2000 178 22 227 4000 181 22 228 5000 180 22 229 5.2.7 Endurance Re gime Maximum permanent Economical cruising Engine rotations (rpm) 5500 4500 IAS (km/ h) 221 178 Airspeed CAS (km/ h) 214 172 Consumption (litres per hour ) 19 11 Range (km) 1400 2000 NOTE: The consumption and range values are valid for the aircraft maximum take‐off weight and flight altitude of 2000 ft ISA. Flight and operational manual TL 3000 SIRIUS Page 39 5.2.8 Wind effect during the take‐off and landing Headwind 10 m / s Crosswind 5,5 m/ s Tailwind 2 m/ s