TECNAM P2010 - Aircraft Flight Manual

3. FOREWORD 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 0823.99.75.38 airworthiness@tecnam.com  www.tecnam.com Page 0 - 9 2nd Edition, Rev. 0 Aircraft Flight Manual SECTIONS LIST 4. SECTIONS LIST General (*) Section 1 Limitations (**) Section 2 Emergency Procedures (*) Section 3 Normal Procedures (*) Section 4 Performances (*) Section 5 Weight and Balance (*) Section 6 Airframe and Systems description (*) Section 7 Airplane Care and Maintenance (*) Section 8 Supplements (***) Section 9 (*) non-approved Section (**) approved Section (***) partially approved Section - approved parts, if any, are reported in the supplements. Page 0 - 10 2nd Edition, Rev. 0 Aircraft Flight Manual INTENTIONALLY LEFT BLANK Page 1 - 1 Section 1 – General INDEX 2nd Edition, Rev.0 SECTION 1 - GENERAL INDEX 1. INTRODUCTION ............................................................................... 3 2. CERTIFICATION BASIS .................................................................... 3 3. WARNING – CAUTION – NOTE ......................................................... 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.................................................... 9 10. UNIT CONVERSION CHART ........................................................... 14 11. LITRES / US GALLONS CONVERSION CHART .............................. 15 Page 1 - 2 Section 1 – General 2nd Edition, Rev.0 INTENTIONALLY LEFT BLANK Page 1 - 3 Section 1 – General INTRODUCTION 2nd Edition, Rev.0 1. INTRODUCTION The Aircraft Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of this aeroplane. This manual also contains supplemental data supplied by the aeroplane manufac- turer. 2. CERTIFICATION BASIS This type of aircraft has been approved by the European Aviation Safety Agency in accordance with CS-23 including Amendment 2 and the Type Certificate No. EASA.A.576 has been issued on 26th September 2014. Category of Airworthiness: Normal. Noise Certification Basis: EASA CS 36 Amendment 2. This type of aircraft has been validated also in the normal category of 14 CFR part 23 and part 36 3. WARNING – CAUTION – NOTE 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 2nd Edition, Rev.0 4. THREE-VIEW AND DIMENSIONS Figure 1 – General views Page 1 - 5 Section 1 – General THREE-VIEW AND DIMENSIONS 2nd Edition, Rev.0 Dimensions Overall dimensions Wing Span …..…………………………….. 10.30 m / 33.79 ft Overall Length ……………………………. 7.97 m / 26.15 ft Overall height ……………………………... 2.64 m / 8.66 ft Stabilator Span ……………………………. 3.35 m / 10.99 ft Wing Wing surface ..…………………………….. 13.9 m2 / 149.6 ft2 Mean Geometric Chord ...………………… 1.349 m / 4.427 ft Dihedral …………………………………... 1° Aspect ratio ………………………………. 7.63 Fuselage Cabin width ..…………………………….. 1.14 m / 3.74 ft Cabin length..…………………………….. 2.3 m / 7.54 ft Landing Gear Wheels Track …………………………….. 2.1 m / 6.89 ft Wheels base ……………………………… 2.15 m / 7.05 ft Main Gear Tire …………………………… 6.00-6 Nose Gear Tire …………………………… 5.00-5 Page 1 - 6 Section 1 – General GENERAL FEATURES 2nd Edition, Rev.0 TERMINOLOGYFLI GHT CONTROL SURFACES 5. ENGINE Manufacturer …………………………… Lycoming Engines Model …………………………………... IO-360-M1A Type Certificate ………………………... EASA TCDS no. IM.E.032 Engine type …………………………….. Fuel injected (IO), direct drive, four cylinder horizontally opposed, air cooled with down exhaust outlets. Maximum power ……. Maximum continuous power …………... 134.0 kW (180 hp) @ 2700 rpm 134.0 kW (180 hp) @ 2700 rpm 6. PROPELLER Manufacturer ………………………….. MT Propeller Model …………………………………. MT 188 R 145 – 4G Type Certificate ……………………….. EASA TCDS no. P.006 Blades/hub …………………………….. 2 wood/composite blades – aluminium hub Diameter ………………………………. 1880 mm (74 in) (no reduction allowed) Type …………………………………… Fixed pitch Page 1 - 7 Section 1 – General GENERAL FEATURES 2nd Edition, Rev.0 TERMINOLOGYSP ECIFIC LOADINGS 7. FLIGHT CONTROL SURFACES TRAVEL Ailerons Up 19°; Down 14 ° ( 2°) Stabilator* Up 6°; Down 17° ( 2°) Stabilator trim tab Up 3°; Down 15° ( 1°) Rudder RH 25°; LH 25° ( 2°) Rudder trim tab RH 20°; LH 20° ( 2°) Flaps 0°; 20°; 40° ( 1°) *degrees are measured from the Stabilator Leading Edge. 8. SPECIFIC LOADINGS MTOW 1160 kg (2557 lb) Wing Loading 83.45 kg/m2 (17.09 lb/ft2) Power Loading 6.44 kg/hp (14.21 lb/hp) Page 1 - 8 Section 1 – General 2nd Edition, Rev.0 TERMINOLOGYSP ECIFIC LOADINGS INTENTIONALLY LEFT BLANK Page 1 - 9 Section 1 – General ACRONYMS AND TERMINOLOGY 2nd Edition, Rev.0 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 and landing gear ex- tended). VS1 Stall speed in clean configuration (flaps 0°). VX Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude with respect to a given horizontal dis- tance. VY Best Rate-of-Climb Speed is the speed which results in the great- est gain in altitude in a given time. VR Rotation speed: is the speed at which the aircraft rotates about the pitch axis during takeoff VLOF Lift off speed: is the speed at which the aircraft generally lifts off from the ground. Vobs Obstacle speed: is the speed at which the aircraft flies over a 15m obstacle during takeoff or landing. Page 1 - 10 Section 1 – General ACRONYMS AND TERMINOLOGY 2nd 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 1013.25 hPa (29.92 inHg). 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 - 11 Section 1 – General ACRONYMS AND TERMINOLOGY 2nd 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 MLG 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 kilo of fuel used. Page 1 - 12 Section 1 – General ACRONYMS AND TERMINOLOGY 2nd 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 P2010 it is equiva- lent to the Maximum Takeoff Weight). Page 1 - 13 Section 1 – General 2nd Edition, Rev.0 INTENTIONALLY LEFT BLANK Page 1 - 14 Section 1 – General UNIT CONVERSION CHART 2nd Edition, 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 sec- ond [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 - 15 Section 1 – General LITRES / US GALLONS CONVERSION CHART 2nd Edition, 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 42 159 190 50.2 45 170.3 200 52.8 47 177.9 210 55.5 50 189.3 220 58.1 55 208.2 230 60.7 60 227.1 240 63.4 63 238.4 Page 1 - 16 Section 1 – General 2nd Edition, Rev.0 INTENTIONALLY LEFT BLANK Section 2 – Limitations INDEX Page 2 - 1 2nd Edition, 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. PAINT ........................................................................................... 9 8. PROPELLER .................................................................................. 9 9. MAXIMUM OPERATING ALTITUDE .............................................. 9 10. AMBIENT TEMPERATURE ............................................................ 9 11. POWERPLANT INSTRUMENT MARKINGS .................................. 10 12. OTHER INSTRUMENT MARKINGS ............................................. 10 13. WEIGHTS .................................................................................... 11 14. CENTER OF GRAVITY RANGE .................................................... 11 15. FLIGHT CREW ............................................................................ 11 16. APPROVED MANEUVERS ........................................................... 12 16.1. Types of Surface ............................................................................. 12 17. MANEUVERS LOAD FACTOR LIMITS ......................................... 12 18. KINDS OF OPERATION EQUIPMENT LIST (KOEL) ..................... 13 19. LIMITATIONS PLACARDS........................................................... 15 19.1. Speed limitations ............................................................................ 15 19.2. Operating limitations ...................................................................... 15 19.3. No Smoking placard ........................................................................ 15 19.4. Baggage Compartment placard ...................................................... 16 Page 2 - 2 Section 2 – Limitations 2nd Edition, Rev.0 INTENTIONALLY LEFT BLANK Page 2 - 3 2nd Edition, 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 and standard systems and equipment. Page 2 - 4 2nd Edition, Rev.0 Section 2 – Limitations INTENTIONALLY LEFT BLANK Page 2 - 5 2nd Edition, Rev.1 Section 2 – Limitations AIRSPEED LIMITATIONS Approved 2. AIRSPEED LIMITATIONS The following table addresses the airspeed limitations and their operational signifi- cance: AIRSPEED KIAS KCAS REMARKS VNE Never exceed speed 166 164 Do not exceed this speed in any operation. VNO Maximum Structural Cruising Speed 132 130 Do not exceed this speed except in smooth air, and only with caution. VA Design Manoeuvring speed 120 119 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 91 92 Do not exceed this speed for indicated flaps setting. Page 2 - 6 Section 2 – Limitations AIRSPEED INDICATOR MARKINGS 2nd Edition, Rev.1 Approved 3. AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. MARKING KIAS EXPLANATION White arc 50 – 91 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 59– 132 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 132 – 166 Manoeuvres must be conducted with caution and only in smooth air. Red line 166 Maximum speed for all operations. Page 2 - 7 Section 2 – Limitations POWERPLANT LIMITATIONS 2nd Edition, Rev.1 Approved 4. POWERPLANT LIMITATIONS Following table reports the operating limitations the installed engine: ENGINE MANUFACTURER: Lycoming Engines ENGINE MODEL: IO-360-M1A MAXIMUM POWER: Max Power (hp) Max rpm. Prop. rpm Max. T.O. 180 2700 Max. Cont. 180 2700 Temperatures: Max CHT ……………………………………….. 500° F (260° C) Max Oil …………………………………………. 245° F (118° C) Oil Pressure: Minimum Idling ………………………………… 25 psi (1.7 Bar) Minimum Normal ………………………………. 55 psi (3.8 Bar) Maximum Normal ……………………………… 95 psi (6.5 Bar) Starting, Warm-up, taxi and take-off (Max) …… 115 psi (7.9 Bar) Fuel pressure: - At Inlet to fuel injector: Minimum .............................................................. 14 psi (0.96 Bar) Maximum ............................................................. 35 psi (2.41 Bar) Page 2 - 8 Section 2 – Limitations FUEL & LUBRIFICANT 2nd Edition, Rev.1 Approved 5. FUEL 2 TANKS: 120 litres each one (31.7 US gallons) MAXIMUM CAPACITY: 240 litres (63.4 US gallons) MAXIMUM USABLE FUEL: 231 litres (61 US gallons) APPROVED FUEL: AVGAS Grade 91/96 or 100 LL (ASTM D910) For additional information, refer to Lycoming Service Instruction No. 1070, latest issue. 6. LUBRICANT Recommended Grade Oil: Average Ambient Temperature All Temperatures Above 80°F Above 60°F 30°F to 90°F 0°F to 70°F Below 10°F MIL-L-6082B or SAEJ1966 Spec. Mineral Grades ---- SAE60 SAE50 SAE40 SAE30 SAE20 MIL-L-22851 or SAEJ1899 Spec. Ashless Dispersant Grades SAE15W50 or SAE20W-50 SAE60 SAE40 or SAE50 SAE40 SAE40, SAE30, SAE20W40 SAE30 or SAE20W30 For additional info, refer to “(L)IO-360-M1A Operation and Installation Manual”, latest issue, “Operating instruction” Section. Page 2 - 9 2nd Edition, Rev.1 Section 2 – Limitations PAINT, PROPELLER, MAX ALTITUDE AND OAT Approved 7. PAINT To ensure that the temperature of the composite structure does not exceed limits, the outer surface of the aeroplane must be painted with white paint, except for areas of registration marks, placards, and ornament. Refer to Aircraft Maintenance Manual (AMM), ATA Chapter 4 and 51, for specific paint requirements. 8. PROPELLER MANUFACTURER: .…….. MT Propeller MODEL: …………….……. MT 188 R 145 – 4G TYPE: .……………….…… wood/composite 2-blade, fixed pitch DIAMETER: ……………... 1880 mm (74 in) (no reduction is permitted) 9. MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 12000 ft (3658 m) MSL. CAUTION At altitudes above 10000 ft (3048 m) up to and including 12000 ft (3658 m), flight crew is recommended to use supplemental oxygen. 10. AMBIENT TEMPERATURE Ambient temperature: from -25 °C (-13 °F) to +50 °C (122 °F). WARNING Flight in expected and/or known icing conditions is forbidden. Page 2 - 10 2nd Edition, Rev.1 Section 2 – Limitations POWERPLANT AND OTHER INSTRUMENT MARKINGS Approved 11. POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their colour code significance are shown below: INSTRUMENT RED ARC Minimum limit WHITE ARC Advisory GREEN ARC Safe operation YELLOW ARC Caution RED ARC Maximum limit PROPELLER RPM / / 950-2700 0-950 2700-2800 OIL TEMP. °F / / 140-245 0 - 140 245 - 255 CHT °F / 435 (line) 150-475 0 – 150 475-500 500-510 EGT °F / 1000-1500 / 1375 (line) 1500-1550 OIL PRESS psi 0-25 / 55-95 25 - 55 95-115 115 - 125 FUEL PRESS psi 0-14 / 14-35 / 35 - 40 FUEL QTY litres 0 / 0-115 / / gal 0 0-30,4 FUEL FLOW l/hr / 0-75 / / / gal/hr 0-20 12. OTHER INSTRUMENT MARKINGS INSTRUMENT RED ARC Minimum limit GREEN ARC Safe operation YELLOW ARC Caution RED ARC Maximum limit Voltmeter 20-21 Volt 24–30 Volt 21–24 Volt 30-31 Volt Page 2 - 11 Section 2 – Limitations WEIGHTS 2nd Edition, Rev.1 Approved 13. WEIGHTS Refer to Section 6 for proper aircraft and baggage loading. 14. CENTER OF GRAVITY RANGE Datum Vertical plane tangent to the wing leading edge (the aircraft must be levelled in the longitudinal plane) Levelling Refer to the seat track supporting beams (see procedure in Section 6) Forward limit 0.262 m (10.3 in) (19% MAC) aft of datum for all weights Aft limit 0.440 m (17.3 in) (32% 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. 15. FLIGHT CREW Minimum crew: 1 pilot Maximum seating configuration: 4 people (including the pilot) Condition Weight Maximum takeoff weight 1160 kg 2557 lb Maximum landing weight 1160 kg 2557 lb Maximum baggage weight 40 kg 88 lb Baggage Compartment Weight Maximum weight 40 kg 88 lb Maximum specific pressure 0.72 kg/dm2 14.9 lb/ft2 NOTE Page 2 - 12 Section 2 – Limitations MANEUVERS 2nd Edition, Rev.1 Approved 16. APPROVED MANEUVERS The aircraft is certified in Normal Category in accordance with EASA CS-23and FAA 14 CFR part 23 regulations. Non aerobatic operations include:  Any manoeuvre pertaining to “normal” flight  Stalls (except whip stalls)  Lazy eights  Turns in which the angle of bank is not more than 60°  Chandelle WARNING Acrobatic manoeuvres, including spins and turns with angle of bank of more than 60°, are not approved for such a category. In addition Intentional shutdown of engine in flight is forbidden. WARNING Limit load factor could be exceeded by moving flight controls to maxi- mum deflection at a speed above VA=VO (120 KIAS, Manoeuvring Speed). WARNING Flight in expected and/or known icing conditions, in proximity of storms or in severe turbulence is forbidden. 16.1. TYPES OF SURFACE This aircraft may operate on both paved and grass surfaces, refer to Section 5 for impacts on performances. 17. MANEUVERS LOAD FACTOR LIMITS Maneuver load factors limits are as follows: Positive Negative + 3.8 g - 1.52 g Maneuver load factors limits with flaps extended are as follows: Positive + 2 g Negative 0 g Page 2 - 13 Section 2 – Limitations KOEL 2nd Edition, Rev.1 Approved 18. KINDS OF OPERATION EQUIPMENT LIST (KOEL) This paragraph reports the KOEL table, concerning the equipment list required on board under CS-23 and Far-23 regulations to allow flight operations in VFR Day/Night and IFR Day/Night. Flight in VFR Day/Night and IFR is permitted only if the prescribed 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. The owner is responsible for fulfilling these requirements. Equipment VFR Day VFR Night IFR Day IFR Night Note External Power Circuit Breakers ● ● ● ● As Required Battery ● ● ● ● Safety Equipment & Furnishing First Aid kit ● ● ● ● Fire extinguisher ● ● ● ● ELT ● ● ● ● Torch (with spare batteries) ● ● Ice Protection Pitot heating system ● ● ● Landing Gear Wheel pants Removable Lights Landing/taxi lights ● ● ● ● Strobe lights ● ● ● ● NAV lights ● ● ● ● Cabin lights ● ● Instrument lights ● ● Emergency light ● ● Dimming Devices ● ● Day/Night switch ● ● COM/Navigation/Engine parameters Magnetic compass ● ● ● ● GARMIN G1000 Suite ● ● ● ● MD 302 suite ● ● ● Pitot system ● ● ● ● Clock ● ● ● ● Flight Controls Pitch trim indicator ● ● ● ● Flap System ● ● ● ● Flaps position lights ● ● ● ● Rudder trim system ● ● ● ● only for VFR operations, rudder trim system may be inoperative provided the trim tab is fixed in the streamlined position and the system is electrically disabled Stall warning system ● ● ● ● VFR Day VFR Night IFR Day IFR Night Page 2 - 14 Section 2 – Limitations 2nd Edition, Rev.1 Approved INTENTIONALLY LEFT BLANK