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VL-3E-1 Pilot Operating Handbook

date of issue:

30/40

5.3

Additional information

5.3.1

Cruise

Regime

Economy
Cruise

Max.
Continuous
Power

Max. Take-Off
Power

Time
limitation

unlimited

unlimited

max. 5 min.

Engine speed

4300

5500

5800

Manifold
pressure
[inHg]

24

27

27.5

IAS
[km/h]

210

260

280

5.3.2

Demonstrated crosswind performance

Max. permitted cross wind velocity for take-off and landing

5 m/s (10 kts)

Max. permitted head wind velocity for take-off and landing

8 m/s (15 kts)

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Содержание Evolution VL-3E-1

Страница 1: ...Pilot Operating Handbook for aeroplane VL 3E 1 Registration number Serial number VL 3 Date ...

Страница 2: ...4 3 Emergency procedures 15 3 1 Introduction 15 3 2 Engine failure 15 3 2 1 Engine failure during take off run 15 3 2 2 Engine failure immediately after take off 15 3 2 3 Engine failure in flight Forced landing 15 3 2 4 In flight engine start 15 3 3 Smoke and fire 16 3 3 1 Fire on ground 16 3 3 2 Fire during take off 16 3 3 3 Fire in flight 16 3 4 Glide 16 3 5 Landing emergencies 17 3 5 1 Emergenc...

Страница 3: ...8 Emergency rescue system 27 4 3 19 Flight in rain 27 5 Performance 28 5 1 Introduction 28 5 2 Performance 28 5 2 1 Airspeed indicator system calibration 28 5 2 2 Stall speeds 29 5 2 3 Take off performance 29 5 2 4 Landing 29 5 2 5 Climb performance 29 5 3 Additional information 30 5 3 1 Cruise 30 5 3 2 Demonstrated crosswind performance 30 6 Weight and balance 31 6 1 Introduction 31 6 2 Permitted...

Страница 4: ... 37 8 1 Introduction 37 8 2 Aeroplane inspection periods 37 8 3 Aeroplane alterations or repairs 37 8 4 Ground handling Road transport 37 8 4 1 Towing 37 8 4 2 Parking 37 8 4 3 Tying Down 38 8 4 4 Lifting 38 8 4 5 Road transport 38 8 4 6 Aeroplane disassembly and assembly 38 9 Supplements 39 9 1 Introduction 39 9 2 List of inserted supplements 39 9 3 Supplements inserted 40 ...

Страница 5: ...ing Handbook provides information useful for the safe and efficient operation of VL 3E 1 Evolution aeroplane It also contains supplemental data supplied by the aeroplane manufacturer 1 2 Warnings cautions and notes The following definitions apply to warnings cautions and notes in the flight manual ...

Страница 6: ... shell with carbon kevlar seats integrated The wing is a monospar construction with a sandwich skin composed of two layers of carbon and special foam Control surfaces and empennage is of the same construction The aeroplane is controlled by dual push pull control system rudder drive is controlled by cables and on the right elevator is trim connected by 2 cables with trim lever The ailerons and elev...

Страница 7: ... 46 kg m2 Ailerons area 0 207 m2 Flaps area 0 8 m2 Fuselage length 6 2 m width 1 15 m height 1 5 m Horizontal tail unit span 2 68 m area 1 69 m2 elevátor area 0 73 m2 Vertical tail unit height 1 03 m area 0 876 m2 rudder area 0 309 m2 Landing gear wheel track 1 83 m wheel base 1 285 m main wheel diameter 0 35 m nose wheel diameter 0 3 m ...

Страница 8: ...VL 3E 1 Pilot Operating Handbook date of issue 8 40 1 4 Two view drawing ...

Страница 9: ...er certain conditions the aircraft may be overstressed by full control movement VNO Maximum structural cruising speed 235 Do not exceed this speed except in smooth air and then only with caution VFE Maximum flap extension speed 120 Do not exceed this speed with flaps extended VLE Maximum landing gear extension speed 150 Do not exceed this speed with undercaridge extended 2 3 Airspeed indicator mar...

Страница 10: ... Continuous 5500 RPM Cruising 4800 RPM Idling 1400 RPM Cylinder head temperature Minimum 60 C Maximum 120 C Oil temperature Minimum 50 C Maximum 130 C Operating 90 C 100 C Fuel pressure if the fuel gauge and sensor are instaled Minimum 0 15 bar Maximum 0 40 bar Fuel see chapter 2 13 Oil refer to engine Operator s Manual Warning This engine has not been certified as an aircraft engine and its failu...

Страница 11: ...ater contacts the upper wall of the tank before the tanks is filled full From this reason the following states of fuel in the tanks are recognised Left tank Right tank Liter US gallon Liter US gallon Full tank 59 15 6 59 15 6 Upper indicating limit 40 10 5 40 10 5 Individual fuel level gauges separate instruments on instrument panel The following colour ranges are marked in EMS diagrams for both t...

Страница 12: ...gravity Empty aeroplane C G position undercarriage retracted xxxx MAC Empty aeroplane C G position undercarriage extended xxxx MAC Operating C G range 21 34 MAC 2 9 Approved manoeuvres Aeroplane Category NORMAL The aeroplane is approved for Normal and Manoeuvres listed below Steep turn not exceeding 60 bank 2 10 Manoeuvring load factors Warning Aerobatics intentional spins and stalls are prohibite...

Страница 13: ...f ethanol These fuels have not been tested by ROTAX company and are not permited for use Recommended fuels Automotive premium grade gasoline leaded according to DIN 516000 Ö NORM C 1103 EUROSUPER RON 95 unleaded accord to DIN 51607 Ö NORM 1100 AVGAS 100 LL Due to higher lead content in AVGAS the wear of valve seats and deposits in the combustion chamber will increase Therefore use AVGAS only if ot...

Страница 14: ...G MIN CREW WEIGHT 65 0 KG MAX BAGGAGE WEIGHT 15 0 KG 15 KG Caution The owner aeroplane operating agency of this aeroplane is responsible for placards readability during aeroplane service life NEVER EXCEED SPEED VNE 305 KM H MANOEUVRING SPEED VA 165 KM H DESIGN CRUISING SPEED VC 235 KM H MAX FLAPS EXTENSION SPEED VFE 120 KM H STALL SPEED VS0 57 KM H Power RPM manifold pressure 1 min in Hg Take off ...

Страница 15: ...m 165 ft choose landing area 3 Wind evaluate direction and velocity 4 Landing area choose free area without obstacles into wind 5 Flaps extend as needed 6 Fuel valve off 7 Ignition off 8 Safety harness tighten 9 Master switch switch off before landing 10 Land 3 2 3 Engine failure in flight Forced landing 1 Speed gliding at 100km h 55 kts 2 Altitude below 50 m 165 ft land in take off direction over...

Страница 16: ...tinguish fire if possible or call fire department 3 3 3 Fire in flight 1 Fuel valve off 2 Throttle full 3 Ignition off after using up fuel in carburetors and engine stopping 4 Master switch off 5 Choose of area heading to the nearest airport or choose emergency landing area 6 Emergency landing perform according to par 3 6 1 7 Abandon the aeroplane 8 Extinguish fire if possible or call fire departm...

Страница 17: ... the chosen area with flaps extended to the take off position at a speed of 60 kts to thoroughly inspect the area 4 Perform flight around the chosen area 5 Landing gear go to the down position see 4 3 8 If landing gear can not be extended or field is not acceptable for landing with open landing gear do not extend the landing gear 6 Perform an approach at increased idling with fully extended flaps ...

Страница 18: ...opening system and find a cause of the defect If after reset of Landing gear controler you don t see the three green lights you must use the hand pump for Emergency releace of gears see chapter 7 3 pos 22 for manuel opening of landing gears follow next steps 1 Check fuel level for estimating the time you have for an emergency landing 2 Airspeed 120 km h 65 kts 3 Switch 5 of Landing gear controler ...

Страница 19: ...ttor icing mostly occurs when getting into an area of ice formation The carburettor icing shows itself through a decrease in engine power and an increase of engine temperatures To recover the engine power the following procedure is recommended 1 Speed 110km h 60 kts 2 Throttle set for 1 3 power 3 If possible leave the icing area 4 Gradually increase the engine power to cruise condition after 1 2 m...

Страница 20: ... of radio communication failure follow next steps 1 Check power supply status of fuse 2 Check communication with another ATC 3 In the case of no communication set tranceiver to 7600 ICAO worldwide emergency code to inform ATC that your transceiver is out of order 4 To land soonest on the nearest airport ...

Страница 21: ...llowing pre flight inspection procedure is recommended by the aeroplane manufacturer Before pre flight inspection check in the cockpit if ignition box is switched off 1 Wing Wing surface condition Leading edge condition check if the flap and aileron controls are correctly connected pitot static tube condition 2 Wing tips Surface condition Check of tips attachment Condition and attachment of positi...

Страница 22: ...ion Engine mount condition Engine attachment check Oil quantity check after 1 minute engine run Fuel and Electrical system visual check Hydraulic system visual check quantity of hydraulic fluid Fuel system draining 15 Propeller Propeller attachment Blades Hub Spinner condition 16 Cockpit Ignition box off and key pull out Master switch off Instruments check of condition Fuel gauge check fuel quanti...

Страница 23: ...nd starting of engine 1 Fuel valve on 2 Switch box turn the key 3 Circuit breakers on 4 Propeller minimum propeller pitch 5 Throttle set for idling 6 Choke according to engine temperature 7 Control stick fully pulled 8 Check free area clear 9 Master switch on 10 Ignition box on both circuit by turning the key in two steps to the right 11 Brakes fully applied 12 Start by turning the key to the righ...

Страница 24: ... COMM within limits frequency set Safety harness secured and tightened Cockpit canopy condition lock take off Gradually increase the throttle max power to set the aeroplane into motion The direction of take off run can be controlled by steer able nose wheel and rudder Slightly pull the stick to lift the nose wheel The aeroplane takes off at a speed above 70km h 38 kts then slightly push forward th...

Страница 25: ... 4 start shining and hydraulic power unit start to extends or retracts landing gears 3 If the three red lights 2 three green lights 3 appears on the Landing gear controler landing gears reached the required end position retracted extended To avoid landing with recracted landing gears are landing flaps connected with landing gears If the landing gears are closed and pilot open landing flaps three r...

Страница 26: ...idge 150 km h 80 kts Propeller minimum propeller pitch Brakes check function Trim adjust as required Landing area check runway Base leg 4 3 12 On base leg Speed 110 km h 60 kts Flaps extend to 38 position Trim adjust as required Throttle as necessary Instruments within limits 4 3 13 On final 1 Speed 90 100 km h 50 55 kts 2 Flaps 55 position 3 Trim adjust as required 4 Throttle as necessary 5 Instr...

Страница 27: ...position 4 3 16 After landing Engine speed set as necessary for taxiing Flaps retracted and locked Trim neutral position 4 3 17 Engine shut down 1 Engine speed idling 2 Instruments engine instruments within limits 3 COMM intercom off 4 Ignition off 5 Circuit breakers off 6 Avionic master switch off 7 Ignition box turn the key to switch off 8 Fuel valve off 4 3 18 Emergency rescue system 1 Rescue s...

Страница 28: ...ndition and using average piloting techniques If not stated otherwise the performance data given in this section is valid for max takeoff weight and under International Standard Atmosphere ISA conditions 5 2 Performance 5 2 1 Airspeed indicator system calibration IAS EAS IAS EAS km h km h kts kts 57 65 31 35 70 78 38 42 80 87 43 47 100 108 54 58 120 125 65 67 140 142 76 77 160 160 86 86 180 179 97...

Страница 29: ...mance Take off distances stated in the following table are valid at sea level Take off run distance m Take off distance over 15 m obstacle m Grass 150 280 5 2 4 Landing Landing distances stated in the following table are valid at sea level Landing distance over 15 m obstacle m Landing run distance full braking m Grass 270 100 5 2 5 Climb performance Best Rate of climb speed is 140 km h 75 kts IAS ...

Страница 30: ...er Max Take Off Power Time limitation unlimited unlimited max 5 min Engine speed 4300 5500 5800 Manifold pressure inHg 24 27 27 5 IAS km h 210 260 280 5 3 2 Demonstrated crosswind performance Max permitted cross wind velocity for take off and landing 5 m s 10 kts Max permitted head wind velocity for take off and landing 8 m s 15 kts ...

Страница 31: ...ange 21 34 M A C 6 2 2 CG calculation Empty weight see 2 7 mpr kg Pilot weight mp1 kg Copilot weight mp2 kg Fuel quantity vp litr Baggage weight mz kg C G of empty aeroplane see 2 8 xbsat Wing leading edge position xNH 540 mm M A C displacement xSAT 68 mm M A C bSAT 1236 mm Weight m mpr mp1 mp2 vp 0 725 mz C G position m m vp m m b x m x z p2 p1 sat bsat pr 1467 215 0 725 682 682 100 xt x bSAT 100...

Страница 32: ...erating Handbook date of issue 32 40 C G position m m vp m m b x m x z p2 p1 sat bsat pr 1467 215 0 725 682 682 100 mm x 346 443 6 1467 10 215 0 725 45 682 0 682 100 100 1236 17 1 301 xt x bSAT 100 346 1236 100 28 bSAT ...

Страница 33: ...oque construction For more information see VL 3 aeroplane Maintenance Manual 7 2 1 Fuselage All composite sandwich construction For more information see VL 3 aeroplane Maintenance Manual 7 2 2 Wing The composite wing has one main spar with carbon flanges no ribs the stressed skin is of sandwich construction with a foam core For more information see VL 3 aeroplane Maintenance Manual 7 2 3 Horizonta...

Страница 34: ... 5 Transponder 18 Hobbs engine run hours 31 Trim lever 6 Autopilot control GMC 307 19 Avionic master switch 32 Parking brake control 7 Low fuel indicator 20 Master switch 33 Throttle control 8 Batery charge indicator 21 Ignition box 34 Wing flaps lever 9 Low oil pressure indicator 22 Ventilation control 35 PTT switch 10 Turn and band indicator 23 Heating control 36 Autopilot disc switch 11 Switche...

Страница 35: ...e skeleton covered with upholstery Four points safety harness with a central lock 7 6 Baggage compartment Baggage compartment is space behind seats 7 7 Canopy Canopy is made from the clear Plexiglas The canopy frame is formed by a composite profile The canopy is tilted forward 7 8 Engine There is installed Rotax 912 engine in VL 3 evolution aeroplane Rotax 912 is 4 stroke 4 cylinder horizontally o...

Страница 36: ...ct level of hydraulic liquid Maintenance of hydraulic system is mentioned in Maintenance Manual VL 3 In case of problems with the hydraulic system immediately contact VL 3 service center 7 12 Pitotstatic system The pitot static system consists of a Prandtl tube under the wing pressure lines plastic pipes for connection with airspeed indicator altimeter and avionic pressure transducer For more info...

Страница 37: ...he empty weight of this aeroplane is relatively low Suitable surfaces to hold the aeroplane airframe are the rear part of the fuselage before the fin and wing roots You can also use hand towing bar for aeroplane moving 8 4 2 Parking It is advisable to park the aeroplane inside a hangar or eventually inside other weather proof space such as a garage with a stable temperature good ventilation low hu...

Страница 38: ...age on the lower side of engine frame and 1 point back on the underside of the fuselage Procedure of lifting 1 Prepare 3 suitable jacks for aeroplane support 2 Press down the rear of the fuselage in front of the fin lift the nose of the aeroplane and support under the firewall by 2 jacks 3 To lift the rear of the fuselage grab the fuselage near the auxiliary tail skid lift it upward and support en...

Страница 39: ...ction This section contains the appropriate supplements necessary to safely and efficiently operate the aeroplane when equipped with various optional systems and equipment not provided with the standard aeroplane 9 2 List of inserted supplements Date Title of inserted supplement ...

Страница 40: ...VL 3E 1 Pilot Operating Handbook date of issue 40 40 9 3 Supplements inserted ...

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