Aircraft Flight Manual

Section 6 1 thru 10, 14 Rev 0 11 thru 13 Rev 5 Section 7 1 thru 44 Rev 0 Section 8 1 thru 10 Rev 0 Section 9 1 thru 8 Rev 5 Supplements LOEP: make reference to the Supplements Cover Pages Page 0 - 8 4th Edition - Rev. 0 Aircraft Flight Manual INTENTIONALLY LEFT BLANK 4th Edition - Rev. 0 Aircraft Flight Manual Page 0 - 9 INTENTIONALLY LEFT BLANK Page 0 - 10 4th Edition - Rev. 0 Aircraft Flight Manual FOREWORD 3. FOREWORD Tecnam P2006T is a twin-engine four-seat aircraft with high cantilevered wing and tri- cycle retractable landing gear. 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 AERONAUTICHE TECNAM s.r.l. Via MAIORISE CAPUA (CE) - ITALY  +39 (0) 823.62.01.34  www.tecnam.com 4th Edition - Rev. 0 Aircraft Flight Manual SECTIONS LIST Page 0 - 11 4. SECTIONS LIST General Section 1 (a non-approved Chapter) Limitations Section 2 - EASA Approved Chapter Emergency Procedures Section 3 (a non-approved Chapter) Normal Procedures Section 4 (a non-approved Chapter) Performances Section 5 (a non-approved Chapter) Weight and Balance Section 6 (a non-approved Chapter) Airframe and Systems description Section 7 (a non-approved Chapter) Airplane Care and Maintenance Section 8 (a non-approved Chapter) Supplements Section 9 (*) (*) EASA approved parts, if any, are reported on the supplements Page 0 - 12 4th Edition - Rev. 4 Aircraft Flight Manual INTENTIONALLY LEFT BLANK Page 1 - 1 Section 1 – General INDEX 4th Edition, Rev 0 SECTION 1 - GENERAL INDEX 1. Introduction .................................................................................. 3 2. Three-view and dimensions .......................................................... 4 3. Control Surfaces Travel Limits .................................................... 6 4. Engine ........................................................................................... 6 5. Propeller ....................................................................................... 6 6. Governor ....................................................................................... 7 7. Fuel ............................................................................................... 7 8. Lubrication .................................................................................... 7 9. Cooling .......................................................................................... 8 10. Maximum weights ...................................................................... 8 11. Standard weights ....................................................................... 8 12. Specific loadings ....................................................................... 8 13. Acronyms and terminology ...................................................... 10 14. Unit conversion chart .............................................................. 15 15. Litres / US gallons conversion chart ....................................... 16 Page 1 - 2 Section 1 – General 4th Edition, Rev 0 INTENTIONALLY LEFT BLANK Page 1 - 3 Section 1 – General INTRODUCTION 4th 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 P2006T. Warning – Caution – Note 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 - 4 Section 1 – General THREE-VIEW AND DIMENSIONS 4th Edition, Rev 0 2. THREE-VIEW AND DIMENSIONS P2006 T GENERAL VIEW Figure 1 – General views Page 1 - 5 Section 1 – General THREE-VIEW AND DIMENSIONS 4th Edition, Rev 0 Dimensions Overall dimensions Wingspan 11,4 m 37,4 ft Length 8,7 m 28,5 ft Overall height 2,58 m 8,46 ft Wing Wing surface 14,76 m2 158,9 ft2 Mean Geometric Chord 1,295 m 4,25 ft Dihedral 1° Aspect ratio 8,80 Main Landing Gear Track 2.0 m Wheelbase 2.9 m Tire 6.00-6 Wheel rim assembly (Cleveland) P/N 40-59A Nose Landing Gear Tire 5.00 – 5 Wheel rim assembly (Cleveland) P/N 40-77C Page 1 - 6 Section 1 – General GENERAL FEATURES 4th Edition, Rev 0 3. CONTROL SURFACES TRAVEL LIMITS Ailerons Up 20° Down 17 ° ( 2°) Stabilator (refer to Trailing Edge) Up 4° Down 15° ( 2°) Stabilator trim tab (refer to Trailing Edge) Up 2°; Down 19° ( 2°) Rudder RH 26° LH 26° ( 2°) Rudder trim tab RH 20° LH 20° ( 2°) Flaps 0°; 40° (- 2°) 4. ENGINE Manufacturer Bombardier-Rotax GmbH Model 912 S3 Certification basis FAR 33 - Amendment 15 Type Certificate EASA TCDS no. E.121 dated 1 April 2008 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) 5. PROPELLER Manufacturer MT Propeller Type Certificate LBA 32.130/086 (MTV-21 series) Model MTV-21-A-C-F/CF178-05 Blades/hub 2 wood/composite blades – aluminum hub Diameter 1780 mm (no reduction allowed) Type Variable pitch - hydraulically controlled Page 1 - 7 Section 1 – General GENERAL FEATURES 4th Edition, Rev 0 6. GOVERNOR Manufacturer Mt Propeller Model P-875-12 Type Hydraulic 7. FUEL 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 integrated tanks (one in each wing) fitted with drainable sump and drain valve Capacity of each wing tan 100 litres (26,42 US gallons) Tanks overall capacity 200 litres (52,8 US gallons) Overall usable fuel 194.4 litres (51,35 US gallons) Overall unusable fuel 5.6 litres (1,48 US gallons) 8. LUBRICATION Lubrication system Forced type with external reservoir Oil Use only oil with API classification “SG” or higher. For additional info, refer to “Ro- tax Operators Manual” – last issue -, “Op- erating Media” Section. Oil capacity Max. 3.0 litres – min. 2.0 litres (per tank) Page 1 - 8 Section 1 – General GENERAL FEATURES 4th Edition, Rev 0 9. COOLING Cooling system Ram-air cooled cylinders, liquid cooled cylinder heads (closed and pressurized circuit) Coolant liquid Certified for Water/Coolant mixture. Make reference to “Rotax Operators Manual” – last issue Overall circuit capacity 1410 cm3 10. WEIGHTS See Section 2. 11. STANDARD WEIGHTS Empty Weight: see weighing record on Section 6 12. SPECIFIC LOADINGS NOTE. Reference is made to both MTOW: 1180 kg and 1230 kg (if Supplement A19 or G10 - Increased MTOW @1230 KG - is applicable). MTOW 1180 kg (2601 lb) MTOW 1230 kg (2712 lb) Wing Loading 80 kg/m2 (16,37 lb/sqft ) 83 kg/m2 (17,1 lb/sqft ) Power Loading 6.0 kg/hp (13,26 lb/hp ) 6.28 kg/hp (13,84 lb/hp ) Page 1 - 9 Section 1 – General GENERAL FEATURES 4th Edition, Rev 0 INTENTIONALLY LEFT BLANK Page 1 - 10 Section 1 – General ACRONYMS AND TERMINOLOGYACRONYMS AND TERMINOLOGY 4th Edition, Rev 0 13. 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. VLO Maximum Landing Gear Operating speed is the maximum speed allowed to retract or to extend the landing gear. VLE Maximum Landing Gear Extended speed is the maximum speed allowed with the landing gear extended. VMC Minimum control speed: is the minimum speed necessary to en- sure an efficient aircraft control in case of one engine inopera- tive. 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 and landing gear ex- tended). VS1 Stall speed in the given flap and landing gear configuration. VSSE Recommended safe simulated OEI speed is the minimum speed at which simulated OEI training operation should be executed. 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 VYSE Best Rate-of-Climb speed in case of one engine inoperative. Page 1 - 11 Section 1 – General ACRONYMS AND TERMINOLOGYACRONYMS AND TERMINOLOGY 4th Edition, Rev 0 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. Page 1 - 12 Section 1 – General ACRONYMS AND TERMINOLOGYACRONYMS AND TERMINOLOGY 4th Edition, Rev 0 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. Page 1 - 13 Section 1 – General ACRONYMS AND TERMINOLOGYACRONYMS AND TERMINOLOGY 4th Edition, Rev 0 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 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 P2006T it is equiv- alent to the Maximum Takeoff Weight). Page 1 - 14 Section 1 – General 4th Edition, Rev 0 INTENTIONALLY LEFT BLANK Page 1 - 15 Section 1 – General UNIT CONVERSION CHART 4th Edition, Rev 0 14. 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 - 16 Section 1 – General LITRES / US GALLONS CONVERSION CHART 4th Edition, Rev 0 15. 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 - 17 Section 1 – General 4th Edition, Rev 0 INTENTIONALLY LEFT BLANK Page 1 - 18 Section 1 – General 4th Edition, Rev 0 INTENTIONALLY LEFT BLANK Section 2 – Limitations INDEX Page 2 - 1 4th Edition, Rev. 0 EASA Approved SECTION 2 – LIMITATIONS INDEX 1. Introduction ......................................................................................................... 3 2. Speed limitations ................................................................................................. 5 3. Airspeed indicator markings ................................................................................ 7 4. Powerplant limitations ........................................................................................ 9 5. Lubricant............................................................................................................ 10 6. Coolant liquid .................................................................................................... 10 7. Propeller ............................................................................................................ 10 8. Governor ........................................................................................................... 10 9. Maximum operating altitude ............................................................................. 11 10. Ambient temperature ........................................................................................ 11 11. Powerplant instruments markings ..................................................................... 12 12. Other instruments markings .............................................................................. 12 13. Warnings, cautions and advisories lights............................................................ 13 14. Weights ............................................................................................................. 15 15. Center of gravity range ...................................................................................... 17 16. Approved maneuvers......................................................................................... 19 17. Maneuvers load factor limits ............................................................................. 19 18. Flight crew ......................................................................................................... 19 19. Flight conditions ................................................................................................ 20 20. Fuel .................................................................................................................... 20 21. Limitations placards ........................................................................................... 21 21.1. Speed limitations........................................................................................... 21 21.2. Operating limitations .................................................................................... 22 21.3. Inflight engine restart .................................................................................... 23 21.4. Baggage compartment capacity..................................................................... 23 21.5. Engine oil level .............................................................................................. 24 21.6. Fuel type ....................................................................................................... 24 21.7. Landing Gear Hydraulic System ..................................................................... 25 21.8. Rear seats ...................................................................................................... 26 21.9. Other placards ............................................................................................... 27 22. Kinds of Operations Equipment List ................................................................... 29 Page 2 - 2 Section 2 – Limitations 4th Edition, Rev. 0 INTENTIONALLY LEFT BLANK Page 2 - 3 4th Edition, Rev. 0 Section 2 – Limitations INTRODUCTION EASA Approved 1. INTRODUCTION Section 2 includes operating limitations, instrument markings and basic placards necessary for safe operation of P2006T aircraft, its engines and standard systems and equipment. This AFM Section is EASA approved. Page 2 - 4 4th Edition, Rev. 0 Section 2 – Limitations INTENTIONALLY LEFT BLANK Page 2 - 5 4th Edition, Rev. 0 Section 2 – Limitations SPEED LIMITATIONS EASA Approved 2. SPEED LIMITATIONS The following table addresses the airspeed limitations and their operational signifi- cance: SPEED KIAS KCAS REMARKS VNE Never exceed speed 167 168 Do not exceed this speed in any operation. VNO Maximum Structural Cruising Speed 135 133 Do not exceed this speed except in smooth air, and only with caution. VA Design Manoeuvring speed 118 117 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 VLE Maximum Landing Gear ex- tended speed 93 92 Do not exceed this speed with the landing gear ex- tended. VLO Maximum Landing Gear op- erating speed 93 92 Do not exceed this speed when operating the landing gear. VFE Maximum flaps extended speed FULL 93 92 Do not exceed this speed for indicated flaps setting. T.O. 119 117 VMC Aircraft minimum control speed with one engine inoper- ative 62 62 Do not reduce speed below this value in event of one engine inoperative condi- tion. Page 2 - 6 4th Edition, Rev. 0 Section 2 – Limitations INTENTIONALLY LEFT BLANK Page 2 - 7 4th Edition, Rev. 0 Section 2 – Limitations AIRSPEED INDICATOR MARKINGS EASA Approved 3. AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. MARKING KIAS EXPLANATION White arc 53-93 Lower limit is VSO, upper limit is the maxi- mum allowable speed with flaps extended in FULL position. Red line 62 Minimum aircraft control speed with one en- gine inoperative and flaps set to T.O. Green arc 66-135 Normal aircraft operating range (lower limit is VS1, stall speed in “clean” configuration, and upper limit is the maximum structural cruise speed VNO). Blue line 80 Best rate-of-climb speed with one engine in- operative at sea level. Yellow arc 135-167 Speed range where manoeuvres must be con- ducted with caution and only in smooth air. Red line 167 Maximum speed for all operations. 4th Edition, Rev. 0 Section 2 – Limitations Page 2 - 8 INTENTIONALLY LEFT BLANK 4th Edition, Rev. 0 Section 2 – Limitations POWERPLANT LIMITATIONS EASA Approved Page 2 - 9 4. POWERPLANT LIMITATIONS Following table reports the operating limitations for both engines installed: ENGINE MANUFACTURER: Bombardier Rotax GmbH. ENGINE MODEL: 912 S3 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 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 CAUTION In event of cold starting operation, it is permitted a maximum oil pressure of 7 bar for a short period. 4th Edition, Rev. 0 Section 2 – Limitations POWERPLANT LIMITATIONS EASA Approved Page 2 - 10 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 or 893114 5. LUBRICANT Use only oil with API classification “SG” or higher. For additional info, refer to “Rotax Operators Manual” – last issue -, “Operating Media” Section. 6. COOLANT LIQUID Refer to “Rotax Operators Manual” – last issue -, “Operating Media” Section. 7. PROPELLER MANUFACTURER: MT Propeller MODEL: MTV-21-A-C-F-/CF178-05 TYPE: wood/composite 2-blade, variable pitch hydraulically con- trolled and fully featherable DIAMETER: 1780 mm (no reduction is permitted) 8. GOVERNOR MANUFACTURER: MT Propeller MODEL: P-875-12 OPERATION: Hydraulically controlled (oil pressure to reduce the pitch)