Aircraft Flight Manual

Aircraft Flight Manual Page 0 - 8 INTENTIONALLY LEFT BLANK Page 0 - 9 Ed. 2, Rev. 0 Aircraft Flight Manual FOREWORD 3. FOREWORD Tecnam P2008 JC is a single-engine two-seat aircraft with a strut braced high wing and fixed landing gear. Section 1 provides 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 AERONAUTICHE TECNAMs.r.l. Via MAIORISE CAPUA (CE) - ITALY +39 (0)823 997538 airworthness@tecnam.com Ed. 2, Rev. 0 Aircraft Flight Manual SECTIONS LIST Page 0 - 10 4. SECTIONS LIST General (*) Section 1 Limitations (**) Section 2 Emergency Procedures (**) Section 3 Normal Procedures (**) Section 4 Performance (***) Section 5 Weight and balance (*) Section 6 Airframe and Systems description (*) Section 7 Ground Handling and Service (*) Section 8 AFM Supplements list (*) Section 9 (*) non-approved Section (**) approved Section (***) approved Section except for pages 5-1 thru 5-4, 5-6, 5-11 thru 5-13 Page 1 - 1 Section 1 – General INDEX Ed. 2, Rev 0 SECTION 1 - GENERAL INDEX 1. INTRODUCTION .................................................................................................. 3 2. CERTIFICATION BASIS ....................................................................................... 3 3. WARNINGS – CAUTIONS – NOTES ...................................................................... 3 4. THREE-VIEW AND DIMENSIONS ......................................................................... 4 5. ENGINE ............................................................................................................... 6 6. PROPELLER ......................................................................................................... 6 7. FLIGHT CONTROL SURFACES TRAVEL .............................................................. 7 8. SPECIFIC LOADINGS........................................................................................... 7 9. ACRONYMS AND TERMINOLOGY ....................................................................... 8 10. UNIT CONVERSION CHART .............................................................................. 13 11. LITRES / US GALLONS CONVERSION CHART .................................................. 14 Page 1 - 2 Section 1 – General Ed. 2, Rev 0 INTENTIONALLY LEFT BLANK Page 1 - 3 Section 1 – General INTRODUCTION Ed. 2, Rev 0 1. INTRODUCTION The Flight Manual has been prepared to provide pilots and instructors with in- formation for the safe and efficient operation of this very light airplane. This manual includes the material required to be furnished to the pilot of CS- VLA. It also contains supplemental data supplied by the airplane manufacturer. 2. CERTIFICATION BASIS This type of aircraft has been approved by the European Aviation Safety Agency in accordance with CS-VLA including Amendment 1 and the Type Certificate No.EASA.A.583 has been issued on (date) 27th September 2013. Category of Airworthiness: Normal Noise Certification Basis: EASA CS 36 Amendment 2. 3. WARNINGS – CAUTIONS – NOTES Following definitions apply to warnings, cautions and notes used in the Aircraft Flight Manual. WARNING means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety. CAUTION means that the non-observation of the corresponding procedure leads to a minor or to a more or less long term degradation of the flight safety. draws the attention to any special item not directly related to safety but which is important or unusual. . NOTE Page 1 - 4 Section 1 – General THREE-VIEW AND DIMENSIONS Ed. 2, Rev 0 4. THREE-VIEW AND DIMENSIONS Figure 1 – General views Section 1 – General GENERAL FEATURES Ed. 2, Rev 0 Page 1 - 5 Dimensions Wing Wing Span 9.00 m (29.5 ft) Wing Area 12.16 m2 (130.9 ft2) Aspect Ratio 6.7 Taper Ratio 0.8 Wing chord 1.373 m (4.5 ft) Fuselage Overall length 6.93 m (22.9 ft) Overall width 1.20 m (3.9 ft) Overall height 2.67 m (8.8 ft) Empennage Stabilator span 2.90 m (9.51 ft) Stabilator area 2.03 m2 (21.8 ft2) Vertical tail area 1.06 m2 (11.4 ft2) Landing Gear Wheel track 1.8 m (5.9 ft) Wheel base 1.94 m (6.4 ft) Main gear tire 5.00-5 Nose Gear tire 5.00-5 Section 1 – General GENERAL FEATURES Ed. 2, Rev 0 Page 1 - 6 5. ENGINE Manufacturer Bombardier-Rotax GmbH Model 912 S2 Engine type 4 cylinders horizontally opposed with 1352 c.c. of overall displacement, liquid cooled cylinder heads, ram-air cooled cylinders, two carburetors, integrated re- duction gear box with torsional shock ab- sorber and overload clutch. Maximum power (at declared rpm) 73.5 kW (98.6hp) @ 5800 rpm –5 minutes maximum. 69.0 kW (92.5hp) @ 5500 rpm (continu- ous) 6. PROPELLER Manufacturer GT Propeller Model GT-2/173/VRR-FW101 SRTC Blades One-piece 2-blade fixed pitch, construct- ed of wood materials, protective layer of laminate. Diameter 1730 mm (no reduction allowed) Type Fixed pitch Section 1 – General GENERAL FEATURES Ed. 2, Rev 0 Page 1 - 7 7. FLIGHT CONTROL SURFACES TRAVEL Ailerons Up 22° Down 14 ° ( 2°) Stabilator (refer to Trailing Edge) Up 4° Down 15° ( 2°) Stabilator trim tab (refer to Trailing Edge) Up 2°; Down 12° ( 1°) Rudder RH 25° LH 25° ( 2°) Flaps 0°; 35° ( 1°) 8. SPECIFIC LOADINGS MTOW 630 kg (1388lb) Wing Loading 51 kg/m2 (10.6 lb/sqft ) Power Loading 6.29 kg/hp (14.09 lb/hp ) Section 1 – General ACRONYMS AND TERMINOLOGY Ed. 2, Rev 0 0 Page 1 - 8 9. ACRONYMS AND TERMINOLOGY 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. VO Operating Manoeuvring speed is the speed above the which it is not allowed to make full or abrupt control movement VS Stall Speed. VS0 Stall Speed in landing configuration (flaps extended). VS1 Stall speed in the given flap 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 Section 1 – General ACRONYMS AND TERMINOLOGY Ed. 2, Rev 0 0 Page 1 - 9 Meteorological terminology 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. Section 1 – General ACRONYMS AND TERMINOLOGY Ed. 2, Rev 0 0 Page 1 - 10 Aircraft performance and flight planning terminology 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. Section 1 – General ACRONYMS AND TERMINOLOGY Ed. 2, Rev 0 0 Page 1 - 11 Weight and balance terminology 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 multiplied 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 mo- ment 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. Section 1 – General Ed. 2, Rev 0 Page 1 - 12 INTENTIONALLY LEFT BLANK Page 1 - 13 Section 1 – General UNIT CONVERSION CHART Ed. 2, Rev 0 10. 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 - 14 Section 1 – General Ed. 2, Rev 0 11. 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 Section 2 – Limitations INDEX Page 2 - 1 Ed. 2, Rev. 0 SECTION 2 – LIMITATIONS INDEX 1. INTRODUCTION ....................................................................................... 3 2. AIRSPEED LIMITATIONS .......................................................................... 5 3. AIRSPEED INDICATOR MARKINGS .......................................................... 6 4. POWERPLANT LIMITATIONS ................................................................... 7 5. FUEL ......................................................................................................... 8 6. LUBRICANT .............................................................................................. 8 7. COOLANT LIQUID ..................................................................................... 8 8. PAINT ....................................................................................................... 8 9. PROPELLER .............................................................................................. 9 10. MAXIMUM OPERATING ALTITUDE .......................................................... 9 11. AMBIENT TEMPERATURE ........................................................................ 9 12. POWERPLANT INSTRUMENTS MARKINGS ............................................ 10 13. OTHER INSTRUMENTS MARKINGS ....................................................... 10 14. WEIGHTS ................................................................................................ 12 15. CENTER OF GRAVITY RANGE ................................................................ 14 16. APPROVED MANOEUVRES ..................................................................... 16 17. MANOEUVRES LOAD FACTOR LIMITS ................................................... 17 18. DEMONSTRATED CROSS WIND SAFE OPERATIONS ............................. 18 19. FLIGHT CREW ........................................................................................ 18 20. KINDS OF OPERATION EQUIPMENT LIST (KOEL) ................................. 19 21. LIMITATIONS PLACARDS....................................................................... 21 22. OTHER PLACARDS ................................................................................. 23 Page 2 - 2 Section 2 – Limitations Ed. 2, Rev. 0 INTENTIONALLY LEFT BLANK Page 2 - 3 Ed. 2, Rev. 0 Section 2 – Limitations INTRODUCTION 1. INTRODUCTION Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the aeroplane, its engine, standard systems and standard equipment. Page 2 - 4 Ed. 2, Rev. 0 Section 2 – Limitations INTENTIONALLY LEFT BLANK Page 2 - 5 Section 2 – Limitations AIRSPEED INDICATOR MARKINGS Ed. 2, Rev. 0 Approved 2. AIRSPEED LIMITATIONS The following table addresses the airspeed limitations and their operational signifi- cance: AIRSPEED KIAS KCAS REMARKS VNE Never exceed speed 145 141 Do not exceed this speed in any operation. VNO Maximum Structural Cruising speed 113 111 Do not exceed this speed except in smooth air, and only with caution. VA Design Manoeuvring speed 99 98 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. VO Operating Manoeuvring speed VFE Maximum flaps extended speed 71 72 Do not exceed this speed for indicated flaps setting. Ed. 2, Rev. 1 Section 2 – Limitations AIRSPEED INDICATOR MARKINGS Approved Page 2 - 6 3. AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. MARKING KIAS EXPLANATION White arc/band 40 – 71 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/band 48 – 113 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/band 113 – 145 Manoeuvres must be conducted with caution and only in smooth air. Red line 145 Maximum speed for all operations. Ed. 2, Rev. 0 Section 2 – Limitations ALTITUDE AND OAT LIMITATIONS Page 2 - 7 Approved 4. POWERPLANT LIMITATIONS Following table reports the powerplant operating limitations: 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 (98.6) 2388 (5800) 5 Max. Cont. 69 (92.5) 2265 (5500) - Temperatures: Max CHT* 135° C Max CT 120°C Min/Max Oil 50° C / 130° 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 12psi (below 1440 propeller rpm) Maximum 102 psi (above 1440 propeller rpm) CAUTION In event of cold starting operation, it is permitted a maximum oil pressure of 7 bar for a short period. Engine starting: allowable temperature range OAT Min -25° C OAT Max +50° C Fuel pressure: Minimum 2.2 psi Maximum 7.26 psi Ed. 2, Rev. 0 Section 2 – Limitations ALTITUDE AND OAT LIMITATIONS Page 2 - 8 Approved 5. FUEL 2 TANKS: 62 litres each one (16.38 US gallons) MAXIMUM CAPACITY: 124 litres (32.76 US gallons) MAXIMUM USABLE FUEL: 120 litres (32 US gallons) APPROVED FUEL: MOGAS ASTM D4814 (min RON 95/AKI 91) MOGAS EN 228 Super/Super plus (min. RON 95/AKI 91) 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. 6. LUBRICANT Recommended by Rotax: BRAND DESCRIPTION SPECIFICATION VISCOSITY CODE SHELL AeroShell Sport Plus 4 API SL SAE 10 W-40 2 Use only oil with API classification “SG” or higher. see Rotax SI-912-016 R4 for list of alternative recommended commercial brands and types 7. COOLANT LIQUID Refer to “Rotax Operators Manual” – last issue -, “Operating Media” Section. NOTE: For the Engines affected by Rotax SB-912-066 R1, the waterless coolant is not permitted) 8. PAINT To ensure that the temperature of the composite structure does not exceed limits, the outer surface of the airplane must be painted with white paint, except for areas of registration marks, placards, and ornament. Refer to Aircraft Maintenance Manual (AMM), Chapter 51, for specific paint requirements. NOTE Page 2 - 9 Ed. 2, Rev. 0 Section 2 – Limitations ALTITUDE AND OAT LIMITATIONS Approved 9. PROPELLER MANUFACTURER: GT Propeller MODEL: GT-2/173/VRR-FW101 SRTC BLADES: One-piece 2-blade, constructed of wood materials, protective layer of laminate. TYPE: Fixed pitch DIAMETER: 1730 mm (no reduction is permitted) 10. MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 13000ft (3962 m) MSL. CAUTION Flight crew is required to use supplemental oxygen according to applica- ble Air Operation Rules. 11. AMBIENT TEMPERATURE Ambient temperature: from -25°C to +50°C. WARNING Flight in expected and/or known icing conditions is forbidden. Ed. 2, Rev. 0 Section 2 – Limitations POWERPLANT INSTRUMENTS MARKINGS Page 2 - 10 Approved 12. 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 ---- 577 - 2265 2265 - 2388 2388 Oil temp. °C 50 50-130 ---- 130 CHT* °C ---- 0-135 ---- 135 CT °C ---- 0-120 ---- 120 Oil pressure psi OP LOW WARNING 12 psi ---- ----- 102 Fuel press. psi FP LOW WARNING 2.2 psi 2.2-7.26 ---- 7.26 *- 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 13. OTHER INSTRUMENTS MARKINGS INSTRUMENT RED ARC Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED ARC Maximum limit Voltmeter 10-10.5 Volt 12–16 Volt -- 16-16,5 Section 2 – Limitations Ed. 2, Rev. 0 0 Page 2 - 11 Approved INTENTIONALLY LEFT BLANK Section 2 – Limitations Ed. 2, Rev. 0 Page 2 - 12 Approved 14. WEIGHTS Condition Weight Maximum takeoff weight 630 kg 1388lb Maximum landing weight 630 kg 1388lb Baggage Compartment Maximum weight 20 kg 44lb Maximum specific pressure 12,5 kg/dm2 256 lbs/sq in Section 2 – Limitations Ed. 2, Rev. 0 Page 2 - 13 Approved INTENTIONALLY LEFT BLANK Section 2 – Limitations CENTER OF GRAVITY RANGE Ed. 2, Rev. 0 Page 2 - 14 Approved 15. CENTER OF GRAVITY RANGE Datum Vertical plane tangent to the propeller flange (the aircraft must be levelled in the longitudinal plane) Levelling Refer to the seat track supporting beams (see procedure in Section 6) Forward limit 1.841 m (20% MAC) aft of datum for all weights Aft limit 1.978 m (30% 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 Ed. 2, Rev. 0 Page 2 - 15 Approved INTENTIONALLY LEFT BLANK Section 2 – Limitations APPROVED manOeuvREs Ed. 2, Rev. 0 Page 2 - 16 Approved 16. APPROVED MANOEUVRES The aircraft is certified in Normal Category in accordance with EASA CS-VLA regu- lation applying to aeroplanes intended for non-aerobatic operation only. Non aerobatic operation includes:  Any manoeuvre pertaining to “normal” flight  Stalls (except whip stalls)  Lazy eights  Chandelles  Steep 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 99 Chandelle 113 Steep turn (max 60°) 99 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 Limit load factor could be exceeded by moving abruptly flight controls at their end run at a speed above VA (Manoeuvring Speed: 99 KIAS). WARNING Flight in expected and/or known icing conditions, in proximity of storms or in severe turbulence is forbidden.