Aircraft Flight Manual

Pages affected by the current revision are indicated by an asterisk (*) following the re- vision code. 3rdEdition, Rev.0 ….................. .... June 20th 2012 3rdEdition, Rev. 1 ….................. .... December 20th2012 3rdEdition, Rev. 2 ….................. .... June 10th2013 3rdEdition, Rev. 3 ….................. .... February 28th2014 3rdEdition, Rev. 4 ….................. July26th2015 3rdEdition, Rev. 5 ….................. July27th2015 3rdEdition, Rev. 6 ….................. February 02th2016 3rdEdition, Rev. 7 ….................. May 19th2017 3rdEdition, Rev. 8 ….................. July 28th 2017 Section Pages Revision Section 0 Pages 1,5 and 6 Rev 8 Page 4 Rev 5 Pages 2,3,7,8 Rev 0 Section 1 Pages 1 thru 14 Rev 0 Section 2 Page 5,11 Rev 4 Pages 1 thru 4, 6 thru 10, 12 thru 22 Rev 0 Section 3 Page8,9,10 Rev 2 Pages 1 thru 7, 11 thru 18 Rev 0 Section 4 Pages 9,11 Rev 0 Pages 1 thru 8 Rev 0 Section 5 Pages 1 thru 20 Rev 0 Section 6 Pages 1 thru 11 Rev 0 Page 12,13, 14 Rev 7 Section 7 Pages 1 thru 14 Rev 0 Section 8 Pages 1 thru 8 Rev 0 Supplements Section 9 Page 3 Rev 8 Page 4 Rev 7 Pages 1,2 Rev 0 Supplements LOEP: make reference to the Supplements Cover Pages 3rd Edition - Rev. 0 Aircraft Flight Manual FOREWORD Page 0 - 7 3. FOREWORD The P2002-JF is a twin seat, single engine aircraft with a tapered, low wing. fixed main landing gear and steerable nose wheel. Section 1 supplies general information and it contains definitions, symbols explana- tions, acronyms and terminology used. Before using the airplane, you are recommended to read carefully this manual: a deep knowledge of airplane features and limitations will allow you for operating the airplane safely. For further information, please contact: COSTRUZIONI AERONAUTICHETECNAMs.r.l. Via MAIORISE CAPUA (CE) - ITALY +39 (0)823.62.22.97airworthiness@tecnam.com 3rd Edition - Rev. 0 Aircraft Flight Manual SECTIONS LIST Page 0 - 8 4. SECTIONS LIST General Section 1(a non-approved Chapter) Limitations Section 2- EASA Approved Chapter Emergency Procedures Section 3- EASA Approved Chapter Normal Procedures Section 4- EASA Approved Chapter Performances Section 5- EASA Approved Chapter (partially) Weight and Balance Section 6 (a non-approved Chapter) Systems Section 7 (a non-approved Chapter) Ground Handling, Servicing and Maintenance Section 8 (a non-approved Chapter) Supplements Section 9 (*) (*) EASA approved parts, if any, are reported on the supplements Page 1 - 1 Section 1 – General INDEX 3rd Edition, Rev 0 SECTION 1 - GENERAL INDEX 1 INTRODUCTION ............................................................................... 2 Certification Basis ........................................................................ 2 1.1 Warning – Caution – Note ............................................................. 2 1.2 2 THREE-VIEW AND DIMENSIONS ..................................................... 3 Three View .................................................................................... 3 2.1 Dimensions ................................................................................... 4 2.2 3 GENERAL FEATURES ...................................................................... 5 Control Surfaces Travel Limits .................................................... 5 3.1 Engine ........................................................................................... 5 3.2 Propeller........................................................................................ 5 3.3 Fuel ............................................................................................... 6 3.4 Lubrication .................................................................................... 6 3.5 Cooling .......................................................................................... 6 3.6 weights ......................................................................................... 6 3.7 Standard weights ......................................................................... 6 3.8 Specific loadings .......................................................................... 7 3.9 4 ACRONYMS AND TERMINOLOGY ................................................... 8 General Airspeed Terminology And Symbols .............................. 8 4.1 Meteorological terminology ......................................................... 9 4.2 Engine Power terminology ........................................................... 9 4.3 Aircraft performance and flight planning terminology ............. 10 4.4 Weight and balance terminology ............................................... 11 4.5 5 UNIT CONVERSION CHART........................................................... 12 6 LITRES / US GALLONS CONVERSION CHART .............................. 13 Page 1 - 2 Section 1 – General INTRODUCTION 3rd Edition, Rev 0 1 INTRODUCTION The Aircraft Flight Manual has been implemented to provide the owners with in- formation for a safe and efficient use of the aircraft TECNAM P2002JF. The P2002-JF is a twin seat, single engine aircraft with a tapered, low wing. fixed main landing gear and steerable nose wheel. This Flight Manual has been prepared to provide pilots and instructors with in- formation for the safe and efficient operation of this very light aeroplane. CERTIFICATION BASIS 1.1 This type of aircraft has been approved by the European Safety Aviation Agency in accordance with CS-VLA dated 14 November 2003, and the Type Certificate No. A.006, 27th May 2004. Category of Airworthiness: Normal Noise Certification Basis: EASA CS-36 1stedition dated 17th October 2003, with reference to ICAO/Annex 16 3rdedition dated 1993, Vol.1 Chapter 10. WARNING – CAUTION – NOTE 1.2 Following definitions apply to warnings, cautions and notes used in the Aircraft Flight Manual. WARNING The non-observation of the corresponding procedure can lead, as immediate effect, to a significant reduction of the flight safety. CAUTION The non-observation of the corresponding procedure can lead to an equipment damage which leads to a reduction of the flight safe- ty in a short or longer time interval. Draws the attention to a procedure not directly related to safety of flight. . NOTE Page 1 - 3 Section 1 – General THREE-VIEW AND DIMENSIONS 3rd Edition, Rev 0 2 THREE-VIEW AND DIMENSIONS THREE VIEW 2.1 Fig. 1.1 – General views  Dimensions shown refer to normal operating tire pressure.  Propeller ground clearance 320mm  Propeller ground clearance with deflated front tire and nose wheel shock ab- sorber compressed by 102mm  Minimum ground steering radius 5.5m Page 1 - 4 Section 1 – General THREE-VIEW AND DIMENSIONS 3rd Edition, Rev 0 DIMENSIONS 2.2 Overall dimensions Wingspan 8.6 m Length 6.61 m Overall height 2.43 m Wing Wing surface 11.5 m2 Taper Ratio 0.6 Dihedral 5° Aspect ratio 6.4 Main Landing Gear Track 1.85 m Wheelbase 1.62 m Tire (Air Trac) 5.00-5 Wheel hub and brakes (Cleveland) 199-102 Nose Landing Gear Tire (Sava) 4.00 – 6 Optionally: Air Trac 5.00-5 Page 1 - 5 Section 1 – General GENERAL FEATURES 3rd Edition, Rev 0 3 GENERAL FEATURES CONTROL SURFACES TRAVEL LIMITS 3.1 Ailerons Up 20° Down 15 ° ( 2°) Stabilator (refer to Trailing Edge) Up 3° Down 15° ( 1°) Stabilator trim tab (refer to Trailing Edge) Up 2°; Down 9° ( 1°) Rudder RH 30° LH 30° ( 2°) Flaps 0°; 40° ( 1°) ENGINE 3.2 Manufacturer Bombardier-Rotax GmbH Model 912 S2 Certification basis FAR 33 - Amendment 15 Austrian T.C. No. TW 9-ACG dated 27th November 1998 Engine type 4 cylinder horizontally-opposed twins with overall displacement of 1352 c.c., mixed cooling, (water-cooled heads and air-cooled cylinders), twin carburetors, integrated reduction gear with torque damper. Maximum power (at declared rpm) 73.5kW (98.5hp) @5800rpm (max.5’) 69.0kW (92.5hp) @5500rpm (cont.) PROPELLER 3.3 Manufacturer Hoffmann Propeller Certification Basis CAR Part 14 Type Certificate SO/E 30 dated 10 December 1999 Model HO17GHM A 174 177 C Number of blades: 2 Diameter 1740 mm (no reduction allowed) Type Fixed pitch – wood Page 1 - 6 Section 1 – General GENERAL FEATURES 3rd Edition, Rev 0 FUEL 3.4 Approved fuel: MOGAS ASTM D4814 MOGAS EN 228 Super/Super Plus (Min RON 95) AVGAS 100LL (ASTM D910) (see also Section 2) Fuel tanks Two wing tanks integrated within the wing’s leading edge. Equipped with finger strainers outlet and with drain fittings. Capacity of each wing tan 50 litres Tanks overall capacity 100 litres Overall usable fuel 99 litres Overall unusable fuel 1 litre LUBRICATION 3.5 Lubrication system Forced type with external reservoir Oil Lubricant specifications and grade are detailed into the “Rotax Operators Manual” and in its re- lated documents. Oil capacity Max. 3.0 litres – min. 2.0 litres COOLING 3.6 Cooling system Mixed air and liquid pressurized closed circuit system Coolant liquid Coolant type and specifications are detailed into the “Rotax Operator’s Manual” and in its related documents. WEIGHTS 3.7 See Section 2. STANDARD WEIGHTS 3.8 Empty Weight: see weighing record on Section 6 Page 1 - 7 Section 1 – General GENERAL FEATURES 3rd Edition, Rev 0 SPECIFIC LOADINGS 3.9 MTOW 580 kg MTOW 600 kg MTOW 620 kg Wing Loading 50.4 kg/m2 52.2 kg/m2 53.9 kg/m2 Power Loading 5.9 kg/hp 6.1 kg/hp 6.3 kg/hp Reference is made to each MTOW: 580 kg, 600 kg (if Supplement A11 Increased MTOW @600kg is applicable) and 620 kg (if Sup- plement A12 Increased MTOW @620kg is applicable). NOTE Page 1 - 8 Section 1 – General ACRONYMS AND TERMINOLOGY 3rd Edition, Rev 0 4 ACRONYMS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 4.1 KCAS Calibrated Airspeed is the indicated airspeed expressed in knots, corrected taking into account the errors related to the instrument itself and its installation. KIAS Indicated Airspeed is the speed shown on the airspeed indicator and it is expressed in knots. KTAS True Airspeed is the KCAS airspeed corrected taking into ac- count altitude and temperature. VA Design Manoeuvring speed is the speed above the which it is not allowed to make full or abrupt control movement. VFE Maximum Flap Extended speed is the highest speed permissible with flaps extended. VNO Maximum Structural Cruising Speed is the speed that should not be exceeded, except in smooth air and only with caution. VNE Never Exceed Speed is the speed limit that may not be exceeded at any time. VS Stall Speed. VS0 Stall Speed in landing configuration (flaps and landing gear ex- tended). VS1 Stall speed in the given flap and landing gear configuration. VX Best Angle-of-Climb Speed is the speed which allows best ramp climb performances. VY Best Rate-of-Climb Speed is the speed which allows the best gain in altitude over a given time. VR Rotation speed: is the speed at which the aircraft rotates about the pitch axis during takeoff Page 1 - 9 Section 1 – General ACRONYMS AND TERMINOLOGY 3rd Edition, Rev 0 METEOROLOGICAL TERMINOLOGY 4.2 ISA International Standard Atmosphere: is the air atmospheric standard condition at sea level, at 15°C (59°F) and at 1013.25hPa (29.92inHg). QFE Official atmospheric pressure at airport level: it indicates the air- craft absolute altitude with respect to the official airport level. QNH Theoretical atmospheric pressure at sea level: is the atmospheric pressure reported at the medium sea level, through the standard air pressure-altitude relationship, starting from the airport QFE. OAT Outside Air Temperature is the air static temperature expressed in degrees Celsius (°C). TS Standard Temperature is 15°C at sea level pressure altitude and decreased by 2°C for each 1000 ft of altitude. HP Pressure Altitude is the altitude read from an altimeter when the barometric subscale has been set to 1013 mb. ENGINE POWER TERMINOLOGY 4.3 RPM Revolutions Per Minute: is the number of revolutions per minute of the propeller, multiplied by 2.4286 yields engine RPM. Page 1 - 10 Section 1 – General ACRONYMS AND TERMINOLOGY 3rd Edition, Rev 0 AIRCRAFT PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY 4.4 Crosswind Velocity is the velocity of the crosswind component for the which adequate control of the air- plane during takeoff and landing is assured. Usable fuel is the fuel available for flight planning. Unusable fuel is the quantity of fuel that cannot be safely used in flight. G is the acceleration of gravity. TOR is the takeoff distance measured from actual start to wheel liftoff point. TOD is total takeoff distance measured from start to 15m obstacle clearing. GR is the distance measured during landing from actual touchdown to stop point. LD is the distance measured during landing, from 15m obstacle clearing to actual stop. S/R is the specific range, that is the distance (in nautical miles) which can be expected at a specific power setting and/or flight configu- ration per kilogram of fuel used. Page 1 - 11 Section 1 – General ACRONYMS AND TERMINOLOGY 3rd Edition, Rev 0 WEIGHT AND BALANCE TERMINOLOGY 4.5 Datum “Reference datum” is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. Arm is the horizontal distance of an item meas- ured from the reference datum. Moment is the product of the weight of an item mul- tiplied by its arm. C.G. Center of Gravity is the point at which the airplane, or equipment, would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the aircraft. Standard Empty Weight is the weight of the aircraft with engine flu- ids and oil at operating levels. Basic Empty Weight is the standard empty weight to which it is added the optional equipment weight. Useful Load is the difference between maximum takeoff weight and the basic empty weight. Maximum Takeoff Weight is the maximum weight approved to perform the takeoff. Maximum Landing Weight is the maximum weight approved for the landing touchdown (for P2002-JF it is equivalent to the Maximum Takeoff Weight). Tare is the weight of chocks, blocks, stands, etc. used when weighing an airplane, and is in- cluded in the scale readings. Tare is de- ducted from the scale reading to obtain the actual (net) airplane weight. Page 1 - 12 Section 1 – General UNIT CONVERSION CHART 3rd Edition, Rev 0 5 UNIT CONVERSION CHART MOLTIPLYING BY  YIELDS TEMPERATURE Fahrenheit [°F]   5 9 32   F Celsius [°C] Celsius [°C] 9 5 32         C Fahrenheit [°F] FORCES Kilograms [kg] 2.205 Pounds [lbs] Pounds [lbs] 0.4536 Kilograms [kg] SPEED Meters per second [m/s] 196.86 Feet per minute [ft/min] Feet per minute [ft/min] 0.00508 Meters per second [m/s] Knots [kts] 1.853 Kilometres / hour [km/h] Kilometres / hour [km/h] 0.5396 Knots [kts] PRESSURE Atmosphere [atm] 14.7 Pounds / sq. in [psi] Pounds / sq. in [psi] 0.068 Atmosphere [atm] LENGTH Kilometres [km] 0.5396 Nautical miles [nm] Nautical miles [nm] 1.853 Kilometres [km] Meters [m] 3.281 Feet [ft] Feet [ft] 0.3048 Meters [m] Centimetres [cm] 0.3937 Inches [in] Inches [in] 2.540 Centimetres [cm] VOLUME Litres [l] 0.2642 U.S. Gallons [US Gal] U.S. Gallons [US Gal] 3.785 Litres [l] AREA Square meters [m2] 10.76 Square feet [sq ft] Square feet [sq ft] 0.0929 Square meters [m2] Page 1 - 13 Section 1 – General LITRES / US GALLONS CONVERSION CHART 3rd Edition, Rev 0 6 LITRES / US GALLONS CONVERSION CHART Litres US Gallons US Gallons Litres 5 1.3 1 3.8 10 2.6 2 7.6 15 4.0 3 11.4 20 5.3 4 15.1 25 6.6 6 22.7 30 7.9 8 30.3 35 9.2 10 37.9 40 10.6 12 45.4 45 11.9 14 53.0 50 13.2 16 60.6 60 15.9 18 68.1 70 18.5 20 75.7 80 21.1 22 83.3 90 23.8 24 90.9 100 26.4 26 98.4 110 29.1 28 106.0 120 31.7 30 113.6 130 34.3 32 121.1 140 37.7 34 128.7 150 39.6 36 136.3 160 42.3 38 143.8 170 44.9 40 151.4 180 47.6 45 170.3 190 50.2 50 189.3 200 52.8 55 208.2 Page 1 - 14 Section 1 – General 3rd Edition, Rev 0 INTENTIONALLY LEFT BLANK Section 2 – Limitations INDEX Page 2 - 1 3rd Edition, Rev. 0 SECTION 2 – LIMITATIONS INDEX 1. Introduction ...................................................................... 2 2. Speed limitations .............................................................. 3 3. Airspeed indicator markings ............................................ 4 4. Powerplant limitations ..................................................... 5 5. Lubricant........................................................................... 6 6. Coolant liquid.................................................................... 7 7. Propeller ........................................................................... 8 8. Maximum operating altitude ............................................ 9 9. Ambient temperature ..................................................... 10 10. Powerplant instruments markings ................................. 11 11. Other instruments markings .......................................... 12 12. Weights ........................................................................... 13 13. Center of gravity range .................................................. 13 14. Approved maneuvers ...................................................... 14 15. Maneuvers load factor limits ......................................... 14 16. Flight crew ...................................................................... 15 17. Maximum passenger seating ......................................... 15 18. Kinds of Operation Equipment List ................................ 16 19. Fuel ................................................................................. 17 20. Demonstrated Cross Wind Safe Operations................... 18 21. Limitation Placards ........................................................ 20 Page 2 - 2 3rd Edition, Rev. 0 Section 2 – Limitations INTRODUCTION 1. INTRODUCTION Section 2 includes operating limitations, instrument markings and basic placards necessary for safe operation of P2002-JF aircraft, its engines and standard systems and equipment. Page 2 - 3 3rd Edition, Rev. 0 Section 2 – Limitations SPEED LIMITATIONS 2. SPEED LIMITATIONS The following table addresses the airspeed limitations and their operational signifi- cance: SPEED KIAS KCAS REMARKS VNE Never exceed speed 138 135 Do not exceed this speed in any operation. VNO Maximum Structural Cruising Speed 110 106 Do not exceed this speed except in smooth air, and only with caution. VA Design Manoeuvring speed 96 94 Do not make full or abrupt control movement above this speed, because under certain conditions the air- craft may be overstressed by full control movement. VFE Maximum flaps extended speed FULL 67 69 Do not exceed this speed for indicated flaps setting. T.O. 97 95 3rd Edition, Rev. 0 Section 2 – Limitations AIRSPEED INDICATOR MARKINGS Page 2 - 4 3. AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. MARKING KIAS EXPLANATION White arc 30 – 67 Positive Flap Operating Range (lower limit is VSO, at specified maximum weight and upper limit is the maximum speed permissi- ble with landing flaps extension). Green arc 40 – 110 Normal Operating Range (lower limit is VS1 at specified maximum weight and most for- ward c.g. with flaps retracted and upper limit is maximum structural speed VNO). Yellow arc 110 – 138 Manoeuvres must be conducted with caution and only in smooth air. Red line 138 Maximum speed for all operations. 3rd Edition, Rev. 4 Section 2 – Limitations POWERPLANT LIMITATIONS Page 2 - 5 4. POWERPLANT LIMITATIONS Following table reports the operating limitations for aircraft engine installed: ENGINE MANUFACTURER: Bombardier Rotax GmbH. ENGINE MODEL: 912 S2 MAXIMUM POWER: Max Power kW (hp) Max rpm. Prop. rpm (engine) Time max. (minutes) Max. T.O. 73.5 (98.5) 2388 (5800) 5 Max. Cont. 69 (92.5) 2265 (5500) - With full throttle, at fixed point in no wind conditions, the maxi- mum propeller’s rpm should be 2100  100. Temperatures: Max CHT* 135° C Max CT 120° C Min/Max Oil 50° C / 130° C Oil normal operating range (approx.) 90° C / 110° C  applicable for Engines up to serial no. 4924543(included) and repaired engine which doesn’t change the cylinder head n°3 with new one (part no. 413195) Oil Pressure: Minimum 0.8 Bar / 12psi (below 1400 rpm prop) Normal 2 – 5 Bar / 29-73psi (above 1400 rpm prop) Maximum 7 Bar / 102 psi (above 1400 rpm prop) Engine starting: allowable temperature range OAT Min -25° C OAT Max +50° C WARNING In event of cold starting operation, it is permitted a maximum oil pressure of 7 bar for a short period. Fuel pressure: Minimum 2.2 psi (0.15 Bar) Maximum 5.8 psi (0.40 Bar) or 7.26 psi* (0.5 Bar) *only applicable for fuel pump part no. 893110 and 893114 NOTE Page 2 - 6 3rd Edition, Rev. 0 Section 2 – Limitations LUBRICANT 5. LUBRICANT Use viscosity grade oil as specified in the following table: WARNING Use of Aviation Grade Oil with or without additives is not per- mitted Page 2 - 7 3rd Edition, Rev. 0 Section 2 – Limitations COOLANT LIQUID 6. COOLANT LIQUID Coolant type and specifications are detailed into the “Rotax Operator’s Manual” and in its related documents. Page 2 - 8 3rd Edition, Rev. 0 Section 2 – Limitations PROPELLER 7. PROPELLER MANUFACTURER: Hoffmann Propeller GmbH MODEL: HO17GHM A 174 177 C TYPE: Wood twin blade fixed pitch DIAMETER: 1740 mm (no reduction permitted) 3rd Edition, Rev. 0 Section 2 – Limitations MAXIMUM OPERATING ALTITUDE Page 2 - 9 8. MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 14000 ft (4260 m) MSL. CAUTION At altitudes above 12500 ft (3810 m) up to and including 14000 ft (4260 m), flight must be limited to 30 minutes, unless the required mini- mum flight crew is provided with and uses supplemental oxygen for that part of the flight at those altitudes that is of more than 30 minutes dura- tion. 3rd Edition, Rev. 0 Section 2 – Limitations AMBIENT TEMPERATURE Page 2 - 10 9. AMBIENT TEMPERATURE Ambient temperature: from -25°C to +50°C. WARNING Flight in expected and/or known icing conditions is forbidden. 3rd Edition, Rev. 4 Section 2 – Limitations POWERPLANT INSTRUMENTS MARKINGS Page 2 - 11 10. POWERPLANT INSTRUMENTS MARKINGS Powerplant instrument markings and their colour code significance are shown be- low: INSTRUMENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Propeller rpm ---- 580 - 2265 2265 - 2388 2388 Oil temp. °C 50 90 - 110 50 - 90 110 - 130 130 CHT(4) °C ---- 0 - 135 ---- 135 CT °C 0 - 120 120 Oil pressure bar 0.8 2 - 5 0.8 - 2 5 - 7 (1) 7 Fuel press. psi 2.2 2.2-5.8 or 7.26(3) ---- 5.8 or 7.26(3) Fuel Q.ty litres 0(2) ---- ---- ---- 1- In event of cold starting operation, it is permitted a maximum oil pressure of 7 bar for a short period. 2 - “0” indication shows the unusable fuel quantity (0,5 litres). 3 – when fuel pump part no. 893110 and 893114.is installed 4 - Applicable for Engines up to serial no. 4924543(included) and repaired engine which doesn’t change the cylinder head n°3 with new one (part no. 413195) Page 2 - 12 3rd Edition, Rev. 0 Section 2 – Limitations OTHER INSTRUMENTS MARKINGS 11. OTHER INSTRUMENTS MARKINGS INSTRUMENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Voltmeter 10,5 Volt 12 - 14 Volt ---- ---- Suction Gage 4,0 inHg 4,5 – 5,5 inHg ---- ---- Section 2 – Limitations WEIGHTS 3rd Edition, Rev. 0 Page 2 - 13 12. WEIGHTS Condition Weight Maximum take-off weight 580 kg Maximum landing weight 580 kg Maximum zero wing fuel weight 580 kg Maximum baggage weight (2.26 m aft from datum): 20 kg 13. CENTER OF GRAVITY RANGE Datum Propeller support flange without spacer Levelling Seat track supporting trusses (ref. to sect.6 for the procedure) Forward limit 1.693 m (26.0% MAC) aft of datum for all weights Aft limit 1.782 m (32.5% MAC) aft of datum for all weights WARNING The pilot is responsible for ensuring that the airplane is properly loaded. Refer to Section 6 for appropriate instruc- tions. Section 2 – Limitations APPROVED MANEUVERS 3rd Edition, Rev. 0 Page 2 - 14 14. APPROVED MANEUVERS The aircraft is certified in normal category in accordance with EASA CS-VLA regula- tion. Non aerobatic operations include:  Any manoeuvre pertaining to “normal” flight  Stalls (except whip stalls)  Lazy eights  Chandelles  Turns in which the angle of bank is not more than 60° Recommended entry speeds for each approved manoeuvre are as follows: Manoeuvre Speed [KIAS] Lazy eight 96 Chandelle 110 Steep turn (max 60°) 96 Stall Slow deceleration (1 kts/s) WARNING Acrobatic manoeuvres, including spins and turns with angle of bank of more than 60°, are not approved for such a category. WARNING imit load factor could be exceeded by moving abruptly flight controls at their end run at a speed above VA (Manoeuvring Speed: 96 KIAS). 15. MANEUVERS LOAD FACTOR LIMITS Maneuver load factors limits are as follows: Positive Negative + 3.8 g - 1.9 g Maneuver load factors limits with flaps extended are as follows: Positive + 1.9 g Negative 0 g Section 2 – Limitations FLIGHT CREW 3rd Edition, Rev. 0 Page 2 - 15 16. FLIGHT CREW Minimum crew for flight is one pilot seated on the left side. 17. MAXIMUM PASSENGER SEATING With the exception of the pilot, only one passenger is allowed on board of this aircraft. Section 2 – Limitations KINDS OF OPERATION EQUIPMENT LIST 3rd Edition, Rev. 0 Page 2 - 16 18. KINDS OF OPERATION EQUIPMENT LIST This paragraph reports the KOEL table, concerning the equipment list required on board under CS-VLA regulations to allow flight operations in VFR Day. Flight in VFR Day is permitted only if the pre-scribed equipment is installed and operational. Additional equipment, or a different equipment list, for the intended operation may be required by national operational requirements and also depends on the airspace classification and route to be flown.  Altimeter  Airspeed Indicator  Heading Indicator  Fuel Gauges  Oil Pressure Indicator  Oil Temp. Indicator  Cylinder Heads Temp. Indicator  Outside Air Temp. indicator  Tachometer  Chronometer  First Aid Kit  Hand-held fire extinguisher  Emergency hammer WARNING Flight in expected and/or known icing conditions, in proximity of storms or in turbulence is forbidden. Additional equipment can be required to fulfill national or specific operational requirements. The owner is responsible for fulfilling these requirements. Equipment list is addressed in Section 6. NOTE NOTE Section 2 – Limitations FUEL 3rd Edition, Rev. 0 Page 2 - 17 19. FUEL TWO TANKS: 50 liters each TOTAL FUEL CAPACITY: 100 liters. USABLE FUEL Q.TY: 99 liters UNUSABLE FUEL Q.TY: 0.5 liters each (1.0 litres total) Compensate uneven fuel tank levels by acting on the fuel selector valve located into the cabin. APPROVED FUEL:  MOGAS ASTM D4814  MOGAS EN 228 Super/Super plus (min. RON 95)  AVGAS 100 LL (ASTM D910) CAUTION Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits inside cylinders due to higher lead content. Make reference to Rotax Maintenance Manual which prescribes dedicated checks due to the prolonged use of Avgas. Section 2 – Limitations DEMONSTRATED CROSS WIND SAFE OPERATIONS 3rd Edition, Rev. 0 Page 2 - 18 20. DEMONSTRATED CROSS WIND SAFE OPERATIONS The aircraft controllability during take-offs and landings has been demonstrated with a cross wind components of 22 kts.