Page 1 Page 0 - 1 Aircraft Flight Manual Doc. No. 2008/100 Ed.1 – Rev. 0 2013, July 30 TECNAM P2008 JC TECNAM ANUFACTURER S.r.l. COSTRUZIONI AERONAUTICHE :P2008 JC IRCRAFT MODEL EASA T : A .583 ( 2013, 27 ERTIFICATE DATED EPTEMBER : …………....
Page 2 Page 0 - 2 SECTION 0 INDEX RECORD OF REVISIONS ..................3 LIST OF EFFECTIVE PAGES ..................8 FOREWORD ......................11 SECTIONS LIST ......................12 Ed. 1, Rev. 0 Aircraft Flight Manual INDEX...
Page 3 Page 0 - 3 1. RECORD OF REVISIONS Any revision to the present Manual, except actual weighing data, is recorded: a Record of Revisions is provided in this Section and the operator is advised to make sure that the record iskept up-to-date. The Manual issue is identified by Edition and Revision codes reported on each page, lower right side.
Page 4 Page 0 - 4 EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges EASA approved as First issue G. Paduano M. Landi M. Oliva part of Type Investigation Ed. 1, Rev. 0 Aircraft Flight Manual RECORD OF REVISIONS...
Page 5 Page 0 - 5 EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Ed. 1, Rev. 0 Aircraft Flight Manual RECORD OF REVISIONS...
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Page 8 Page 0 - 8 2. LIST OF EFFECTIVE PAGES The List of Effective Pages (LOEP), applicable to manuals of every operator, lists all the basic AFM pages: each manual could contain either basic pages orone variant of these pages when the pages of some Supplementsare embodied. Pages affected by the current revision are indicated by an asterisk (*) following the re- vision code.
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Page 11 Page 0 - 11 3. FOREWORD Tecnam P2008 JC is a single-enginetwo-seat aircraft with a strut braced high wingand- fixedlanding 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.
Page 12 Page 0 - 12 4. SECTIONS LIST Section 1 General (*) Section 2 Limitations (**) Section 3 Emergency Procedures (**) Normal Procedures (**) Section 4 Performance (***) Section 5 Weight and balance (*) Section 6 Airframe and Systems description (*) Section 7 Ground Handling and Service (*) Section 8...
Page 13 Page 1 - 1 SECTION 1 - GENERAL INDEX INTRODUCTION ....................3 CERTIFICATION BASIS ..................3 WARNINGS – CAUTIONS – NOTES ..............3 THREE-VIEW AND DIMENSIONS ................. 4 ENGINE ....................... 6 PROPELLER ......................6 FLIGHT CONTROL SURFACES TRAVEL .............. 7 SPECIFIC LOADINGS...................
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Page 15 Page 1 - 3 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.
Page 16 Page 1 - 4 4. THREE-VIEW AND DIMENSIONS Figure 1 – General views Ed. 1, Rev 0 Section 1 – General THREE-VIEW AND DIMENSIONS...
Page 17 Page 1 - 5 Dimensions Wing Wing Span 9.00 m (29.5 ft) Wing Area 12.16 m (130.9 ft Aspect Ratio Taper Ratio 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...
Page 18 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.
Page 19 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°...
Page 20 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.
Page 21: Meteorological Terminology
Page 1 - 9 Meteorological terminology International Standard Atmosphere: is the air atmospheric standard condition at sea level, at 15°C (59°F) and at 1013.25hPa (29.92inHg). Official atmospheric pressure at airport level: it indicates the air- craft absolute altitude with respect to the official airport level. 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.
Page 22 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.
Page 23: Weight And Balance Terminology
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. 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.
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Page 25: Unit Conversion Chart
Page 1 - 13 10. UNIT CONVERSION CHART  MOLTIPLYING YIELDS EMPERATURE Fahrenheit [°F] Celsius [°C] ⋅ − [°F]   Celsius [°C] Fahrenheit   + ⋅   ORCES Kilograms [kg] 2.205 Pounds [lbs] Pounds [lbs] 0.4536 Kilograms [kg] PEED Meters per second...
Page 26 Page 1 - 14 11. LITRES / US GALLONS CONVERSION CHART Litres US Gallons US Gallons Litres 11.4 15.1 22.7 30.3 37.9 10.6 45.4 11.9 53.0 13.2 60.6 15.9 68.1 18.5 75.7 21.1 83.3 23.8 90.9 26.4 98.4 29.1 106.0 31.7 113.6 34.3...
Page 27 Page 2 - 1 SECTION2–LIMITATIONS INDEX INTRODUCTION ..................3 AIRSPEED LIMITATIONS ................5 AIRSPEED INDICATOR MARKINGS ............6 POWERPLANT LIMITATIONS ..............7 FUEL ......................8 LUBRICANT ....................8 COOLANT LIQUID ..................8 PAINT ....................... 8 PROPELLER ....................9 10. MAXIMUM OPERATING ALTITUDE ............9 11.
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Page 29 Page 2 - 3 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. Ed.1, Rev. 0 Section 2 – Limitations INTRODUCTION...
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Page 31 Page 2 - 5 2. AIRSPEED LIMITATIONS The following table addresses the airspeed limitations and theiroperational signifi- cance: AIRSPEED KIAS KCAS REMARKS V NE Never exceed speed Do not exceed this speed in any operation. V NO Maximum Structural Do not exceed this speed except in smooth air, and Cruising speed only with caution.
Page 32 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 Positive Flap Operating Range (lower limit 40 – 71 is V , at specified maximum weight and upper limit is the maximum speed permissi- ble with landing flaps extension).
Page 33 Page 2 - 7 4. POWERPLANT LIMITATIONS Following table reports the powerplant operating limitations: : Bombardier Rotax GmbH. NGINE MANUFACTURER : 912 S2 NGINE MODEL AXIMUM POWER Max Power Max rpm. Time max. kW (hp) Prop. rpm(engine) (minutes) 73.5 (98.6) 2388 (5800) Max.
Page 34 Page 2 - 8 5. FUEL 62 litres each one (16.38 US gallons) ANKS 124 litres (32.76 US gallons) AXIMUM CAPACITY 120 litres (32 US gallons) AXIMUM USABLE FUEL MOGAS ASTM D4814 (min RON 95/AKI 91) PPROVED FUEL MOGAS EN 228 Super/Super plus (min. RON 95/AKI 91) AVGAS 100 LL (ASTM D910) Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits...
Page 35 Page 2 - 9 9. PROPELLER GT Propeller ANUFACTURER GT-2/173/VRR-FW101 SRTC ODEL One-piece 2-blade, constructed of wood materials, protective LADES layer of laminate. Fixed pitch 1730 mm (no reduction is permitted) IAMETER 10. MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 13000ft (3962 m) MSL. At altitudes above 10000ft (3048 m) up to and including 13000 ft (3962 m), flight crew is recommended to use supplemental oxygen.
Page 36 Page 2 - 10 12. POWERPLANT INSTRUMENTS MARKINGS Powerplant instrument markings and their colour code significance are shown be- low: RED LINE GREEN ARC YELLOW ARC RED LINE Minimum Normal Caution Maximum NSTRUMENT limit operating limit Propeller ---- 577 - 2265 2265 - 2388 2388 Oil temp.
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Page 38 Page 2 - 12 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/dm 256 lbs/sq in Ed.1, Rev. 0 Section 2 – Limitations...
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Page 40 Page 2 - 14 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...
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Page 42 Page 2 - 16 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 •...
Page 43 Page 2 - 17 17. MANOEUVRES LOAD FACTOR LIMITS Manoeuvre load factors limits are as follows: Positive Negative + 4 g - 2 g Manoeuvre load factors limits with flaps extended are as follows: Positive Negative + 2 g Ed.1, Rev. 0 Section 2 –...
Page 44 Page 2 - 18 18. DEMONSTRATED CROSS WIND SAFE OPERATIONS The aircraft controllability, during take-offs and landings, has been demonstrated with a cross wind components of 15kts. 19. FLIGHT CREW Minimum crew: 1 pilot Maximum number of occupants: 2 people (including the pilot) Ed.1, Rev.
Page 45 Page 2 - 19 20. KINDS OF OPERATION EQUIPMENT LIST (KOEL) 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 prescribed equipment is installed and operational.
Page 46 Page 2 - 20 Equipment VFR Day ● Analogue Altimeter ● Analogue Airspeed Indicator ● Magnetic Direction Indicator ● Analogue Fuel Quantity Indicators ● Analogue CHT indicator ● Garmin G3X suite ● Transponder ● Altitude Encoder ● Slip indicator ● Longitudinal Trim Indicator ●...
Page 47 Page 2 - 21 21. LIMITATIONS PLACARDS The following limitation placards are placed in plain view on the pilot. On the left side instrument panel, above on the left, it is placed the following plac- ard reporting the speed limitations: On the central side of the instrument panel, the following placard is placed remind- ing the observance of aircraft operating limitations according to installed equipment configuration (see KOEL, Para.
Page 48 Page 2 - 22 Below LH and RH Garmin G3X display and analogue instruments following plac- ards are placed : Ed. 1, Rev. 0 Section 2 – Limitations Limitations placards...
Page 49 Page 2 - 23 22. OTHER PLACARDS Engine compartment placards Oil brakes reservoir placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 50 Page 2 - 24 Usable fuel markings Allowed fuel placard Emergency exit placard Parking brake placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 51 Page 2 - 25 Throttle marking Fuel selector valve marking Choke placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 52 Page 2 - 26 Cabin heat/defrost placard Carb heat placard Ignition key placard Master/Generator placards Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 53 Page 2 - 27 Flap indicator placard Backrest lever placard Safety equipment location placard Elt placard Battery placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 54 Page 2 - 28 Annunciator panel Upper panel labels Switches labels Door lock lever Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 55 Page 2 - 29 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 56 Page 2 - 30 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 57 Page 3 - 1 SECTION3–EMERGENCY PROCEDURES INDEX I NTRODUCTION ................3 A IRPLANE ALERTS ................4 2 .1. E lectric Power System Malfunction ............... 5 2 .2. G 3X Failures ....................6 2 .2.1 LH or RH Display failure ................6 2 .2.2 Loss of engine parameters on G3X ...............
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Page 59 Page 3 - 3 1. INTRODUCTION Section 3 includes checklists and detailed procedures to be used in the event of emergencies. Emergencies caused by a malfunction of the aircraft or engine are extremely rare if appropriate maintenance and pre-flight inspections are carried out.
Page 60 Page 3 - 4 2. AIRPLANE ALERTS The alert lights, located on the instrument panel can have the following colours: GREEN to indicate that pertinent device is turned ON AMBER to indicate no-hazard situations which have to be considered and which require a proper crew action to indicate emergency conditions Ed.
Page 61 Page 3 - 5 2.1. LECTRIC OWER YSTEM ALFUNCTION Alternator Failure Light ON Alternator light may illuminate for a faulty alternator or when NOTE voltage is above 16V; in this case the over-voltage sensor auto- matically shuts down the alternator. If ALTOUT caution is ON: Generator switch: Master switch:...
Page 62 Page 3 - 6 2.2. G3X F AILURES 2.2.1. LH RH D ISPLAY FAILURE In case of LH or RH display failure, navigation and engine data will be automati- cally available in the remaining display(split mode). INSTRUCTION: revert to the remaining display. 2.2.2.
Page 63 Page 3 - 7 2.3. ITOT EATING YSTEM AILURE When the Pitot Heat system (if installed) is activated, the green PITOT HEAT ON safe operating annunciation is ON; If the amber PITOT HEAT caution turns ON, the Pitot Heat system is not functioning properly.
Page 64 Page 3 - 8 3. AIRPLANE EVACUATION With the engine secured and propeller stopped (if practical): Parking brake: Seat belts: unstrap completely Headphones: REMOVE Door: OPEN Escape away from flames/ hot engine compartment/ spilling fuel tanks/ Hot brakes. ENGINE SECURING Following procedure is applicable to shut-down the engine in flight: Throttle Lever IDLE...
Page 65 Page 3 - 9 5. ENGINE FAILURE 5.1. NGINE AILURE URING Throttle: IDLE (keep fully out) Rudder: Keep heading control Brakes: apply as needed When safely stopped: Ignition key: OFF. Fuel selector valve: Electric fuel pump: Alternator& Master switches: OFF. 5.2.
Page 66 Page 3 - 10 5.3. NGINE AILURES URING LIGHT 5.3.1 Low Fuel Pressure If the fuel pressure indicator falls below 2.2 psi/FP LOW warning is ON: Electric fuel pump: Fuel selector valve: select opposite fuel tank if NOT empty Fuel quantity indicators: Check both If fuel pressure doesn’t build up: Land as soon as possible applying forced landing procedure (See Para.
Page 67 Page 3 - 11 5.3.2 Low Oil Pressure If oil pressure is below12 psi/OP LOW warning is ON: Throttle Lever REDUCE to minimum practical Land as soon as practical If oil pressure does not increase and OP LOW persists ON: Land as soon as possible applying forced landing procedure (See Para.
Page 68 Page 3 - 12 5.3.3 High Oil Temperature If OP LOW warning is ON, see para. 5.3.2 “Low Oil Pressure”. If oil pressure is within limits: Throttle Lever REDUCE to Minimum practical If oil temperature does not decrease Airspeed INCREASE if practical If oil temperature does not come back within limits, the thermostatic valve regulating the oil flow to the heat NOTE...
Page 69 Page 3 - 13 5.3.4 CHT limit exceedance If CHT is above 135°C, apply following procedure: If OP LOW warning is ON, see para. 5.3.2 “Low Oil Pressure”. If oil pressure is within limits: Throttle Lever REDUCE Minimum practical Land as soon as practical If CHT does not come back within limits, the thermo- static valve regulating the water flow to the cylinder NOTE...
Page 70 Page 3 - 14 6. IN-FLIGHT ENGINE RESTART After a mechanical engine seizure, fire or a major propeller damage engine restart is not recommended. WARNING Carburettor heat ON if required Electrical fuel pump Fuel quantity indicator CHECK Fuel Selector select opposite tank if not empty Ignition key BOTH Ignition key...
Page 71 Page 3 - 15 7. SMOKE AND FIRE 7.1. NGINE FIRE ON THE GROUND Fuel Selector Electrical fuel pump Ignition key Throttle lever FULL POWER Cabin Heat Alternator & Master Switches Parking Brake ENGAGED Aircraft Evacuation carry out immediately 7.2. NGINE URING AKEOFF...
Page 72 Page 3 - 16 7.3. NGINE LIGHT Cabin heat: Fuel selector valve: Electric fuel pump: Throttle: FULL FORWARD until the engine stops Ignition key: Cabin vents: OPEN Do not attempt engine restart WARNING Land as soon as possible applying forced landing procedure(See Para. 7). 7.4.
Page 73 Page 3 - 17 8. LANDING EMERGENCIES 8.1. ORCED ANDING ITHOUT NGINE OWER Flaps: Airspeed: 71 KIAS Find a suitable place to land safely, plan to approach it upwind. Fuel selector valve: Electric fuel pump: Ignition key: Safety belts: Tighten When certain to land Flaps: as necessary...
Page 74 Page 3 - 18 8.4. ANDING If it’s suspected a main tire defect or it’s reported to be defective: 1. Pre-landing checklist: Complete 2. Flaps: Land 3. Land the aeroplane on the side of runway opposite to the defective tire to compensate the change in direction which is to be expected during final rolling 4.
Page 75 Page 3 - 19 9. RECOVERY FROM UNINTENTIONAL SPIN If unintentional spin occurs, the following recovery procedure should be used: Throttle: IDLE (full out position and hold) Rudder: full, in the opposite direction of the spin Stick: centralize and hold neutral As the spin stops: Rudder: SET NEUTRAL...
Page 76 Page 3 - 20 10. OTHER EMERGENCIES 10.1. NINTENTIONAL LIGHT CING ONDITIONS Carburettor ice is possible when flying at low engine rpm in visi- ble moisture (outside visibility less than 5 km, vicinity of fog, mist, clouds, rain, snow or hail) and OAT less than 10°C.Airbox carbu- rettor heater is designed to help prevent carburettor ice, less ef- WARNING fectively functions as a de-icing system.
Page 77 Page 3 - 21 10.2. YSTEM AILURE Trim Jamming Should trim control be inoperative, act as follows: Breaker: CHECK IN LH/RH Trim switch: CHECK for correct position If jamming persists Trim cutout switch: CHECKON Speed: adjust to control aircraft without excessive stick force Land aircraft as soon as possible.
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Page 79 Page 4 - 1 SECTION 4 – NORMAL PROCEDURES INDEX INTRODUCTION ....................3 AIRSPEEDS FOR NORMAL OPERATIONS ............3 PRE-FLIGHT INSPECTIONS ................5 3.1. Cabin Inspection ..................5 3.2. Aircraft Walk-around ..................6 CHECKLISTS ....................12 4.1. Before Engine Starting (After Pre-flight Inspection) ......... 12 4.2.
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Page 81 Page 4 - 3 1. INTRODUCTION Section 4 describes checklists and recommended procedures for the conduct of normal operations for P2008 JC aircraft. Garmin G3X provides primary engine and electric system pa- rameters information, supported by caution/warning lights in NOTE the annunciator panel and backup CHT indicator.
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Page 83 Page 4 - 5 3. PRE-FLIGHT INSPECTIONS Before each flight, it is necessary to carry out a complete aircraft check including a cabin inspection followed by an external inspection, as below detailed. 3.1. ABIN NSPECTION Aircraft documents (ARC, Certificate of Airworthiness, Noise certificate, Radio COM certificate, AFM): check current and on board Weight and balance: calculate (ref.
Page 84 Page 4 - 6 3.2. IRCRAFT AROUND To perform the aircraft walk-around, carry out the checklists according to the pattern shown in Figure 4-1. Visual inspection is defined as follows: check for defects, cracks, detachments, excessive play, unsafe or improper installation as well as for general condition.
Page 85 Page 4 - 7 Figure 4.1 Left fuel filler cap CHECK desired fuel level (use graduated dipstick). Drain the left fuel tank sump by quick drain valve using a cup to collect fuel (drainage operation must be carried with the aircraft parked on a level surface).
Page 86 Page 4 - 8 CHECK inflation, tire condition, alignment, Left main landing gear fuselage skin condition. Check fuselage skin status, tire status (cuts, bruises, cracks and excessive wear), slippage markers integrity, gear structure and brakes hoses: there should be no sign of hydraulic fluid leakage. Stabilator and tab CHECK stabilator leading edge.
Page 87 Page 4 - 9 Check the engine cowling surface conditions, then open engine inspection doors and perform the following checks: a) Nacelle inlets and exhausts openings must be free of obstructions. Check connection and integrity of air intake system, visually inspect that ram air intake is unobstructed.
Page 88 Page 4 - 10 Tow bar and chocks REMOVE, stow on board pitot, static ports and stall warning protective plugs. Avoid blowing inside Pitot tube and inside airspeed indicator system's NOTE static ports as this may damage instruments. Ed. 1, Rev. 0 Section 4 –...
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Page 90 Page 4 - 12 4. CHECKLISTS 4.1. EFORE NGINE TARTING FTER FLIGHT NSPECTION 1. Seat position and safety belts: adjust In-flight seat release can cause the loss of airplane control. Check that occupied seats are positively locked: after seat adjustment, make sure that the adjustment lever is well aligned with the aircraft longitudinal axis(neutral position) and that WARNING has a springback return to the neutral position.
Page 91 Page 4 - 13 4.2. NGINE TARTING Engine throttle: idle Choke: as needed Fuel selector valve: select the tank with less fuel Electric fuel pump: ON Propeller area: call for CLEAR and visually check Check to insure no person or object is present in the area close to the propeller.
Page 92 Page 4 - 14 4.4. AXIING Brakes: check Flight instruments: check altimeter. 4.5. RIOR TO TAKEOFF 1. Parking brake: brake pedal press, ON 2. Engine instruments: Check: • Oil temperature: 50-130 °C • Cylinder heads temperature: Max. 135 °C • Oil pressure: 12 –...
Page 93 Page 4 - 15 4.6. AKEOFF AND CLIMB Primary flight information (airspeed, altitude and heading) is pro- vided by analogue instruments. Flight information provided by G3X is only for situational awareness. WARNING On uncontrolled fields, before line up, check runway wind direc- tion and speed and check for traffic on final WARNING 1.
Page 94 Page 4 - 16 4.8. EFORE ANDING Electric fuel pump: ON 2. Fuel valve: select the fullest tank Landing Light: ON On downwind, leg abeam touch down point: Flaps: set T/O Approach speed: 58 KIAS On final leg: Flaps: set LAND Final Approach Speed: 54 KIAS Carburettor heat: OFF (full IN) Optimal touchdown speed: 54 KIAS...
Page 95 Page 4 - 17 4.11. NGINE SHUT DOWN Parking brake: engage Keep engine running at 1200 propeller rpm for about one minute in order to reduce latent heat. Avionic equipment: OFF Ignition key: OFF, keys extracted Strobe light: OFF Master &Generator switches: OFF Fuel selector valve: OFF Before disembarkation verify propeller is fully stopped.
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Page 97 Page 5 - 1 SECTION 5 - PERFORMANCE INDEX INTRODUCTION ..................2 USE OF PERFORMANCE CHARTS ............2 AIRSPEED INDICATOR SYSTEM CALIBRATION ........3 ICAO STANDARD ATMOSPHERE ............. 4 STALL SPEED ..................5 CROSSWIND .................... 6 TAKEOFF PERFORMANCE ..............7 TAKE-OFF RATE OF CLIMB ..............
Page 98 Page 5 - 2 1. INTRODUCTION This section provides all necessary data for an accurate and comprehensive plan- ning of flight activity from take-off to landing. Data reported in graphs and/or in tables were determined using:  “Flight Test Data” under conditions prescribed by EASA CS-VLA regulation ...
Page 99: Airspeed Indicator System Calibration
Page 5 - 3 3. AIRSPEED INDICATOR SYSTEM CALIBRATION Airspeed Indication System Calibration Graph shows calibrated airspeed V as a function of indicated airspeed V Flap UP Flap T/O Flap LN Calibrated Airspeed [KCAS] . 5-1. C ALIBRATED VS NDICATED IRSPEED Example: Given...
Page 100 Page 5 - 4 4. ICAO STANDARD ATMOSPHERE . 5-2. ICAO C HART Examples: Scope Given Find A: Pressure altitude = 1600ft → C: Density Altitude = 2550ft Density Altitude: B: Temperature = 20°C → E: ISA Air Temperature = 12°C ISA Temperature: D: Pressure altitude = 1600ft Ed.
Page 101 Page 5 - 5 5. STALL SPEED Weight: 630 kg Throttle Levers: IDLE CG: Most Forward (20%) No ground effect TALL PEED EIGHT NGLE 0° LAPS LAPS LAPS [kg] [deg] KIAS KCAS KIAS KCAS KIAS KCAS (FWD C.G.) Altitude loss during conventional stall recovery, as demonstrated NOTE during flight tests is approximately 350 ft with banking below 30°.
Page 102 Page 5 - 6 6. CROSSWIND Maximum demonstrated crosswind is 15 Kts  Example: Given Find Wind direction ( ) = 30° Headwind = 17.5 Kts with respect to aircraft longitudinal axis Wind speed = 20 Kts Crosswind = 10 Kts .
Page 103 Page 5 - 7 7. TAKEOFF PERFORMANCE To account for likely in service performance variations apply a NOTE factored to distances of 1.10 Weight = 630 kg Corrections Headwind: - 5m for each kt (16 ft/kt) Flaps: T/O Speed at Lift-Off = 48 KIAS Tailwind: + 15m for each kt (49 ft/kt) Speed Over 50ft Obstacle = 60 KIAS Paved Runway: - 10% to Ground Roll...
Page 104 Page 5 - 8 Weight = 580 kg Corrections Headwind: - 5m for each kt (16 ft/kt) Flaps: T/O Tailwind: + 15m for each kt (49 ft/kt) Speed at Lift-Off = 48 KIAS Speed Over 50ft Obstacle = 60 KIAS Paved Runway: - 10% to Ground Roll Throttle Levers: Full Forward Runway slope: + 7% to Ground Roll for each +1%...
Page 105 Page 5 - 9 Weight = 530 kg Corrections Headwind: - 5m for each kt (16 ft/kt) Flaps: T/O Tailwind: + 15m for each kt (49 ft/kt) Speed at Lift-Off = 48 KIAS Speed Over 50ft Obstacle = 60 KIAS Paved Runway: - 10% to Ground Roll Throttle Levers: Full Forward Runway slope: + 7% to Ground Roll for each + 1%...
Page 106 Page 5 - 10 8. TAKE-OFF RATE OF CLIMB To account for likely in service performance variations apply a NOTE factored to rate of climb of 0.90 Full Forward Throttle Levers: Flaps: Take-Off (15°) Rate of Climb [ft/min] Climb Pressure Weight Speed Altitude...
Page 107 Page 5 - 11 9. EN-ROUTE RATE OF CLIMB To account for likely in service performance variations apply a NOTE factored to rate of climb of 0.90 Full Forward Throttle Levers: Flaps: UP Rate of Climb [ft/min] Climb Pressure Weight Speed Altitude Temperature [°C]...
Page 108: Cruise Performance
Page 5 - 12 10. CRUISE PERFORMANCE Propeller speed over 2265 RPM is restricted to 5min. CAUTION Weight = 630 kg CORRECTIONS Fuel Specific KTAS Endurance Range Consumption Range For each +15°C of OAT -2.5% For each -15°C of OAT For -100kg of weight +3.3% CRUISE PERFORMANCE...
Page 109 Page 5 - 13 Weight = 630 kg CORRECTIONS Fuel Specific KTAS Endurance Range Consumption Range For each +15°C of OAT -2.5% For each -15°C of OAT For -100kg of weight +3.3% CRUISE PERFORMANCE Pressure Fuel Specific Propeller Endurance Range Altitude KTAS Consumption...
Page 110 Page 5 - 14 11. LANDING PERFORMANCE To account for likely in service performance variations apply a NOTE factored to distances of 1.67 Weight = 630 kg Corrections Headwind: - 4m for each kt (13 ft/kt) Flaps: LAND Tailwind: + 13m for each kt (43 ft/kt) Short Final Approach Speed = 54 KIAS Throttle Levers: Idle Paved Runway: - 10% to Ground Roll...
Page 111 Page 5 - 15 12. BALKED LANDING PERFORMANCE To account for likely in service performance variations apply a NOTE factored to rate of climb and to angle of climb of 0.90 Throttle Levers: Full Forward Flaps: Take-Off (15°) Speed: 60 KIAS Rate of Climb [ft/min] (angle of climb [deg]) Pressure Weight...
Page 112 Page 5 - 16 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 5 - Performances...
Page 113 Page 6 - 1 SECTION6–WEIGHT AND BALANCE INDEX INTRODUCTION ....................3 WEIGHING PROCEDURES ................... 3 2.1. Preparation ....................3 2.2. Levelling ...................... 3 2.3. Weighing ...................... 3 2.4. Determination of C.G. location ..............4 2.5. Weighing record ................... 5 2.6. Weighing record (II) ..................
Page 114 Page 6 - 2 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 6 – Weight and balance...
Page 115: Weighing Procedures
Page 6 - 3 1. INTRODUCTION This section describes the procedure for establishing the basic empty weight and the moment of the aircraft. Loading procedure information is also provided. Aircraft must be operated in accordance with the limits con- cerning the maximum takeoff weight and CG excursion as re- NOTE ported in Flight Manual Section 2.
Page 116 Page 6 - 4 2.4. C.G. ETERMINATION OF LOCATION Drop a plumb bob tangent to the wing leading edge and trace a reference mark on the floor(see Figure on Para. 2.5 or 2.6) Repeat the operation for other wing Stretch a taught line between the two marks Measure the distance between the reference line and both main and nose wheel axis(A and B distances respectively) Using recorded data it is possible to determine the aircraft C.G.
Page 117 Page 6 - 5 2.5. EIGHING RECORD ModelP2008 JCS/N:________ Weighing no. ____ Date:_________ Datum: Propeller Flange Datum Reference line W2=WL+WR Kg or Lbs Meters or feet Nose wheel weight W Plumb bob distance LH wheel LH wheel weight Plumb bob distance RH wheel RH wheel weight Average distance (A Plumb bob distance from nose wheel B =...
Page 118 Page 6 - 6 2.6. (II) EIGHING RECORD ModelP2008 JCS/N:________ Weighing no. ____ Date:_________ Datum: Propeller Flange Datum Reference line W2=WL+WR Kg or Lbs Meters or feet Nose wheel weight W Plumb bob distance LH wheel LH wheel weight Plumb bob distance RH wheel RH wheel weight Average distance (A Plumb bob distance from nose wheel B =...
Page 119 Page 6 - 7 3. WEIGHTS AND C.G. In order to compute the weight and balance of this aircraft, the following loading charts are provided. To compute weight and balance use the formula: Weight * Arm = Moment. Pilot&Passenger Fuel Baggage Momen Momen...
Page 120 Page 6 - 8 Meter Inches Pilot and PAX 1.800 70.90 FUEL 2.209 86.97 BAGGAGE 2.417 95.16 To compute weight and balance: 1. Get moments from loading charts 2. Obtain the empty weight and moment from the most recent weight and balance 3.
Page 121 Page 6 - 9 C.G.Range Max FWD Max AFT Meters 1.841 1.978 Max Weight Pounds Kilograms 1320.00 630.00 Example Weight Weight Moment Moment (lbs) (kg) (inches) (lbs x in) (lbs x in) 60531.97 691.88 Empty Weight 813.5 366.075 74.41 1.89 13051.16 149.18 Fuel...
Page 122: Equipment List
Page 6 - 10 5. EQUIPMENT LIST The following is a comprehensive list of all TECNAM supplied equipment for the P2008 JC. The list consists of the following groups: A Engine and accessories Landing gear Electrical system D Instruments Avionics the following information describes each listing: ...
Page 123 Page 6 - 11 P2008 JC E QUIPMENT EIGHT ATUM & ESCRIPTION [kg] [mm] [N°] & NGINE ACCESSORIES Prop. GT Propellers – p/nGT-2/173/VRR-FW101 -144 SRTC Heat exchanger - p/n28-10-8000-000 2.00 Oil Reservoir (full) - p/n956137 4.00 Oil radiator - p/n886032 0.50...
Page 124 Page 6 - 12 P2008 JC E QUIPMENT EIGHT ATUM & ESCRIPTION [kg] [mm] [N°] NSTRUMENTS LUN 1128.12B6 –TSO Altimeter 1.00 1084 MIKROTECHNAp/n C10b Airspeed indicator – MIKROTECHINA p/nLUN 1.00 1084 1116F0B2 - TSO C2b Compass - AirpathC2400 L4P – TSO C7c 0.29...
Page 125 Page 7 - 1 SECTION7–AIRFRAME AND SYSTEMS DESCRIPTION INDEX INTRODUCTION ................2 AIRFRAME ..................2 2.1. Wing ......................2 2.2. Fuselage ....................3 2.3. Empennages ....................3 2.4. Landing gear ..................... 4 FLIGHT CONTROLS ..............5 INSTRUMENT PANEL ..............5 4.1.
Page 126 Page 7 - 2 1. INTRODUCTION This section provides description and operation of the aircraft and its systems. 2. AIRFRAME P2008 JC’s airframe can be divided in the following main groups, as highlighted be- low on: 1) Wings 2) Fuselage...
Page 127 2.2. USELAGE The P2008 JC fuselage is mainly made by carbon fibres composite materials. The fuselage is made by two main shells that are later assembled bonding the two main bodies and the floor (composite) and adding aluminium stiffeners that allow the connection of the main landing gear, seats, wing and instrument panel.
Page 128 Page 7 - 4 2.4. ANDING GEAR The main landing gear (see Figure 7-3) consists of two special steel leaf-springs posi- tioned crossways to the fuselage. Fig. 7-3.M ANDING EAR STRUCTURE The steel leaf-springs are attached to the fuselage structure via two couples of ma- chined aluminium beams.
Page 129 Page 7 - 5 3. FLIGHT CONTROLS Aircraft flight controls are operated through conventional stick and rudder pedals. Longitudinal control acts through a system of push-rods and is equipped with a trim tab. a cable control circuit is confined within the cabin and it is connected to a pair of push-pull rod systems positioned in each main wing which control ailer- ons differentially.
Page 130 Page 7 - 6  Pitot heat switch (optionally provided);  Carburetor heat knob; • The lower-Central portion of the instrument panel holds:  Throttle;  Two analogue fuel quantity indicators;  Fuel selector valve. • The lower-RH portion of the instrument panel holds: ...
Page 131 6. DOORS Two doors are provided for P2008 JC, on Pilot and co-pilot side. A sketch of the door is shown below (RH and LH doors are specular): Gas spring support...
Page 132 Page 7 - 8 7. POWERPLANT 7.1. ENGINE Manufacturer: Bombardier-Rotax GmbH Model: ROTAX 912 S2 Type: 4 stroke, horizontally-opposed 4 cylinder, mixed air and water cooled, twin electronic ignition, forced lubrication. Maximum rating: 98.6hp (73.5kW) @ 5800 rpm/min (2388 rpm/min. prop). Gear reduction ratio - 2.4286:1 Max oil consumption: Max: 0.1 litres/hour 7.2.
Page 133 Page 7 - 9 8. FUEL SYSTEM The fuel system is designed to supply the reciprocating engine (Bombardier-Rotax 912 S2) with the suitable flow rate and pressure according to engine limitations re- quired by Rotax. Following figure shows the fuel system assy of P2008JC airplane. Fig.7-7.
Page 134 Page 7 - 10 The fuel selector is operated by a fuel selector control knob located in the cabin on the central panel. The fuel selector control and the fuel valve are connected via a rigid control rod. Ed. 1, Rev 0 Section 7 –...
Page 135 9.2. VIONICS The avionic system installed P2008 JC features four analogue indicators, an airspeed indicator, an altimeter, a magnetic compass and a slip indicator, which provide pri- mary flight information. Garmin G3X integrated avionic suite in a dual screen configuration is installed. It provides flight information intended for the pilot’s situational awareness only.
Page 136 Page 7 - 12 Two dedicated indicators provide the pilot with information about the flaps and pitch trim position. Stand-alone external COM/NAV and transponder sources (Garmin SL 30 and GTX 328) are installed. Garmin SL 30 Navigation information is presented on the display (course and direction) along with the information related to active/standby frequency.
Page 137 Page 7 - 13 9.3. XTERNAL OWER UPPLY On the right side of the tail cone, an external power is present. Using this device it is possible to feed the electric system directly on the bus bar, by an external power source.
Page 138 Page 7 - 14 10. PITOT-STATIC PRESSURE SYSTEMS The P2008 JC air speed/altitude indicating systems are connected with a Pitot-Static system based on a total pressure/Pitot probe (simple Pitot tube) mounted on left wing strut and two static pressure ports connected in parallel and located in corre- spondence of engine firewall on left and right side of fuselage.
Page 139 Page 7 - 15 11. BRAKES The P2008 JC is provided with an independent hydraulically actuated brake system for each main wheel. A master cylinder is attached to each pilot’s rudder pedal. Hy- draulic pressure, applied via the master cylinders, enters the brake via lines connect- ed to the caliper.
Page 140 Page 7 - 16 INTENTIONALLY LEFT BLANK Ed. 1, Rev 0 Section 7 – Airframe and Systems description BRAKES...
Page 141 Page 8 - 1 SECTION 8 – GROUND HANDLING & SERVICE INDEX INTRODUCTION ..............2 AIRCRAFT INSPECTION INTERVALS ......... 3 AIRCRAFT CHANGES OR REPAIRS ........4 MAINTENANCE ..............5 4.1. Refuelling ................. 5 4.2. Oil level control ............... 5 4.3. Landing gear tires pressure control ........5 ENGINE COWLING CHECK ..........
Page 142 Page 8 - 2 INTRODUCTION This section contains factory-recommended procedures for proper ground han- dling and routine care and servicing. It also identifies certain inspection and maintenance requirements. It is recommended to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered locally.
Page 143 Page 8 - 3 AIRCRAFT INSPECTION INTERVALS Scheduled inspections must be performed in accordance with the instructions addressed on the Aircraft Maintenance Manual. Independently from the aircraft flight hours, an annual inspection has to be performed. All required inspections are reported in the Aircraft Maintenance Manual. As far as the scheduled/unscheduled engine maintenance is concerned, refer to the engine manufacturer Maintenance Manual.
Page 144 Page 8 - 4 AIRCRAFT CHANGES OR REPAIRS Aircraft changes or repairs must be performed in accordance with Aircraft Main- tenance Manual and Job cards provided by TECNAM. Ed. 1, Rev. 0 Section 8 – GROUND HANDLING & SERVICE AIRCRAFT CHANGES OR REPAIRS...
Page 145 Page 8 - 5 MAINTENANCE 4.1. EFUELLING Do not perform aircraft refuelling near flames, sparks or similar. Avoid fuel contact with the skin: a skin corrosion could occur. Make sure that a fire extinguisher is available nearby during refu- elling operations. Make sure that overall aircraft instrumentation is turned OFF be- fore performing the refuelling.
Page 146 Page 8 - 6 ENGINE COWLING CHECK 5.1. PPER COWLING Parking brake: ON Fuel selector valve: OFF III. Magnetos: OFF Generator & Master switches: OFF Unlatch all four butterfly Cam-locks mounted on the cowling by rotat- ing them 90° counter clockwise while slightly pushing inwards. Remove engine cowling paying attention to propeller shaft passing through nose.
Page 147: Ground Handling
Page 8 - 7 GROUND HANDLING 6.1. OWING The aircraft is most easily and safely maneuvered by hand by pushing on wing struts near attachments or by pulling it by its propeller near the axle. A tow bar can be fixed onto nose gear fork. Aircraft may be steered by turning rudder or, for steep turns, by pushing lightly on tail cone to lift nose wheel.
Page 148 Page 8 - 8 6.3. OORING The aircraft is moored to insure its immovability, protection, and security under various weather conditions. Mooring is strongly recommended when the wind is more than 15 knots and the a/c is completely refuelled. CAUTION Procedure 1.
Page 149: Cleaning And Care
Page 8 - 9 CLEANING AND CARE Aircraft surface must be kept clean to ensure expected flight performance. Excessively dirty surfaces can affect normal flight conditions. CAUTION 7.1. INDOWS For windows cleaning, it is allowed the use of acrylic products employed for glass and Plexiglas surfaces cleaning.
Page 150 Page 8 - 10 ICE REMOVAL Anti icing products are not allowed. To remove ice, tow the aircraft in the hangar and operate with a soft brush or a humid cloth. Ed. 1, Rev. 0 Section 8 – GROUND HANDLING & SERVICE ICE REMOVAL...
Page 151 Page 9-1 SECTION 9 – AFM SUPPLEMENTS INDEX INDEX ......................... 1 Introduction ......................2 Supplements list ....................3 Ed., Rev. 0 SECTION 9 – AFM Supplements SUPPLEMENTS LIST...
Page 152 Page 9-2 1. I NTRODUCTION This Section concerns the supplemental manuals of additional (or optional) instrumen- tation equipping the P2008JC and/or information and limitations related to installed equipment configuration or needed to fit local national rules. Ed., Rev. 0 SECTION 9 – AFM Supplements SUPPLEMENTS LIST...
Page 153 Page 9-3 2. S UPPLEMENTS LIST Aircraft S/N: Registration marks: Date: SUPPLEMENTS LIST FOR AIRPLANES WITH ANALOGUE INSTRUMENTS APPLICABLE: Sup. No. Title Rev. no. Date VFR Night equipment configuration Ed., Rev. 0 SECTION 9 – AFM Supplements SUPPLEMENTS LIST...
Page 154 Page 9-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements SUPPLEMENTS LIST...
Page 155 Page S1-1 .S1- UPPLEMENT NO VFR N IGHT QUIPMENT ONFIGURATION Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges EASA approved as First Issue G. Paduano M. Landi M. Oliva part of Type...
Page 156 Page S1-2 INDEX INTRODUCTION ..................3 SECTION 1 – GENERAL ................5 SECTION 2 – LIMITATIONS ..............7 SECTION 3 – EMERGENCY PROCEDURES ........... 9 SECTION 4 – NORMAL PROCEDURES ..........11 SECTION 5 - PERFORMANCE .............. 13 SECTION 6 – WEIGHT AND BALANCE ..........15 SECTION 7 –...
Page 157 Page S1-3 NTRODUCTION The information contained herein supplements or supersedes the basic Aircraft Flight Manual: detailed instructions are provided to allow the owner for replacing the basic AFM pages containing information amended as per the VFR Night Equipment Configuration in subject. It is the owner’s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section.
Page 158 Page S1-4 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 159 Page S1-5 Supplement S1: pages replacement instructions 1 –G ECTION ENERAL Refer to Basic AFM Section 1. Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 160 Page S1-6 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 161 Page S1-7 Supplement S1: pages replacement instructions 2 – L ECTION IMITATIONS Supplement S1 – Limitations pages replace basic AFM Section 2 as a whole. Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 162 Page S1-8 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 163 AFMS for VFR NIGHT equipped airplanes Page 2N - 1 SECTION 2 – LIMITATIONS INDEX INTRODUCTION ..................3 AIRSPEED LIMITATIONS ................5 AIRSPEED INDICATOR MARKINGS ............6 POWERPLANT LIMITATIONS ..............7 FUEL ......................8 LUBRICANT ....................8 COOLANT LIQUID ..................8 PAINT .......................
Page 164 AFMS for VFR NIGHT equipped airplanes Page 2N - 2 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 2 – Limitations...
Page 165 AFMS for VFR NIGHT equipped airplanes Page 2N - 3 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. Ed.1, Rev. 0 Section 2 – Limitations INTRODUCTION...
Page 166 AFMS for VFR NIGHT equipped airplanes Page 2N - 4 INTENTIONALLY LEFT BLANK Ed.1, Rev. 0 Section 2 – Limitations...
Page 167 AFMS for VFR NIGHT equipped airplanes Page 2N - 5 2. AIRSPEED LIMITATIONS The following table addresses the airspeed limitations and their operational signifi- cance: AIRSPEED KIAS KCAS REMARKS V NE Never exceed speed Do not exceed this speed in any operation.
Page 168 AFMS for VFR NIGHT equipped airplanes Page 2N - 6 3. AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. MARKING KIAS EXPLANATION White arc Positive Flap Operating Range (lower limit 40 – 71 is V , at specified maximum weight and upper limit is the maximum speed permissi-...
Page 169 AFMS for VFR NIGHT equipped airplanes Page 2N - 7 4. POWERPLANT LIMITATIONS Following table reports the powerplant operating limitations: : Bombardier Rotax GmbH. NGINE MANUFACTURER : 912 S2 NGINE MODEL AXIMUM POWER Max Power Max rpm. Time max. kW (hp) Prop.
Page 170 AFMS for VFR NIGHT equipped airplanes Page 2N - 8 5. FUEL 62 litres each one (16.38 US gallons) ANKS 124 litres (32.76 US gallons) AXIMUM CAPACITY 120 litres (32 US gallons) AXIMUM USABLE FUEL MOGAS ASTM D4814 (min RON 95/AKI 91) PPROVED FUEL MOGAS EN 228 Super/Super plus (min.
Page 171 AFMS for VFR NIGHT equipped airplanes Page 2N - 9 9. PROPELLER GT Propeller ANUFACTURER GT-2/173/VRR-FW101 SRTC ODEL One-piece 2-blade, constructed of wood materials, protec- LADES tive layer of laminate. Fixed pitch 1730 mm (no reduction is permitted) IAMETER 10. MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 13000ft (3962 m) MSL.
Page 172 AFMS for VFR NIGHT equipped airplanes Page 2N - 10 12. POWERPLANT INSTRUMENTS MARKINGS Powerplant instrument markings and their colour code significance are shown be- low: RED LINE GREEN ARC YELLOW ARC RED LINE Minimum limit Normal Caution Maximum NSTRUMENT operating limit Engine...
Page 173 AFMS for VFR NIGHT equipped airplanes Page 2N - 11 INTENTIONALLY LEFT BLANK Ed.1, Rev. 0 Section 2 – Limitations...
Page 174 AFMS for VFR NIGHT equipped airplanes Page 2N - 12 14. WEIGHTS Condition Weight Maximum takeoff weight 630 kg 1388 lb Maximum landing weight 630 kg 1388 lb Baggage Compartment Maximum weight 20 kg 44 lb Maximum specific pressure 12,5 kg/dm 256 lbs/sq in Ed.1, Rev.
Page 175 AFMS for VFR NIGHT equipped airplanes Page 2N - 13 INTENTIONALLY LEFT BLANK Ed.1, Rev. 0 Section 2 – Limitations WEIGHTS...
Page 176 AFMS for VFR NIGHT equipped airplanes Page 2N - 14 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...
Page 177 AFMS for VFR NIGHT equipped airplanes Page 2N - 15 INTENTIONALLY LEFT BLANK Ed.1, Rev. 0 Section 2 – Limitations...
Page 178 AFMS for VFR NIGHT equipped airplanes Page 2N - 16 16. APPROVED MANOEUVRES The aircraft is certified in Normal Category in accordance with EASA CS- VLAregulation applying to aeroplanes intended for non-aerobatic operation only. Non aerobatic operation includes: • Any manoeuvre pertaining to “normal” flight •...
Page 179 AFMS for VFR NIGHT equipped airplanes Page 2N - 17 17. MANOEUVRES LOAD FACTOR LIMITS Manoeuvre load factors limits are as follows: Positive Negative + 4 g - 2 g Manoeuvre load factors limits with flaps extended are as follows: Positive Negative + 2 g...
Page 180 AFMS for VFR NIGHT equipped airplanes Page 2N - 18 18. DEMONSTRATED CROSS WIND SAFE OPERATIONS The aircraft controllability during take-offs and landings has been demonstrated with a cross wind components of 15kts. 19. FLIGHT CREW Minimum crew: 1 pilot Maximum number of occupants: 2people (including the pilot) Ed.
Page 181 AFMS for VFR NIGHT equipped airplanes Page 2N - 19 20. KINDS OF OPERATION EQUIPMENT LIST (KOEL) This paragraph reports the KOEL table, concerning the equipment list required on board under CS-VLA regulations to allow flight operations in VFR Day and VFR Night.
Page 182 AFMS for VFR NIGHT equipped airplanes Page 2N - 20 Equipment VFR Day VFR Night ● ● ANALOGUE ALTIMETER ● ● ANALOGUE AIRSPEED INDICATOR ● ● MAGNETIC DIRECTION INDICATOR ● ANALOGUE ATTITUDE INDICATOR ● ● ANALOGUE FUEL QUANTITY INDICATORS ● ●...
Page 183 AFMS for VFR NIGHT equipped airplanes Page 2N - 21 21. LIMITATIONS PLACARDS The following limitation placards are placed in plain view on the pilot. On the left side instrument panel, above on the left, it is placed the following plac- ard reporting following speed limitation: On the central side of the instrument panel, the following placard is placed remind- ing the observance of aircraft operating limitations according to the installed...
Page 184 AFMS for VFR NIGHT equipped airplanes Page 2N - 22 Below the G3X screens and analogue instruments, the following labels are placed: Ed. 1, Rev. 0 Section 2 – Limitations Limitations placards...
Page 185 AFMS for VFR NIGHT equipped airplanes Page 2N - 23 22. OTHER PLACARDS Engine compartment placards Oil brakes reservoir placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 186 AFMS for VFR NIGHT equipped airplanes Page 2N - 24 Usable fuel markings Allowed fuel placards Emergency exit placard Parking brake placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 187 AFMS for VFR NIGHT equipped airplanes Page 2N - 25 Throttle marking Fuel selector valve marking Choke placard Alternate static port placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 188 AFMS for VFR NIGHT equipped airplanes Page 2N - 26 Cabin heat/defrost placard Carb heat placard Ignition key placard Master/Generator placards Map-light placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 189 AFMS for VFR NIGHT equipped airplanes Page 2N - 27 Flap indicator placard Backrest lever placard Safety equipment location placard Elt placard Battery placard Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 190 AFMS for VFR NIGHT equipped airplanes Page 2N - 28 Annunciator panel Upper panel labels Switches labels Day/Night switch label Door lock lever Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 191 AFMS for VFR NIGHT equipped airplanes Page 2N - 29 Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 192 AFMS for VFR NIGHT equipped airplanes Page 2N - 30 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 2 – Limitations OTHER placards...
Page 193 Page S1-9 Supplement S1: pages replacement instructions 3 – E ECTION MERGENCY ROCEDURES Supplement S1 – Emergency Procedures pages replace basic AFM Section 3 as a whole. Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 194 Page S1-10 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 195 AFMS for VFR NIGHT equipped airplanes Page 3N - 1 SECTION 3 – EMERGENCY PROCEDURES INDEX 1. INTRODUCTION ................3 2. AIRPLANE ALERTS ................4 2.1. Electric Power System Malfunction ............... 5 2.2. Pitot Heating System Failure ................6 2.3. G3X Failures ....................7 3.
Page 196 AFMS for VFR NIGHT equipped airplanes Page 3N - 2 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 3 – Emergency procedures INDEX...
Page 197 AFMS for VFR NIGHT equipped airplanes Page 3N - 3 1. INTRODUCTION Section 3 includes checklists and detailed procedures to be used in the event of emergencies. Emergencies caused by a malfunction of the aircraft or engine are extremely rare if appropriate maintenance and pre-flight inspections are carried out.
Page 198 AFMS for VFR NIGHT equipped airplanes Page 3N - 4 2. AIRPLANE ALERTS The alert lights, located on the annunciator panel, feature the following colours: GREEN to indicate that pertinent device is turned ON AMBER to indicate no-hazard situations which have to be considered and which require a proper crew action to indicate emergency conditions Ed.
Page 199 AFMS for VFR NIGHT equipped airplanes Page 3N - 5 2.1. LECTRIC OWER YSTEM ALFUNCTION Alternator Failure Light ON Alternator light may illuminate for a faulty alternator or when NOTE voltage is above 16V; in this case the over-voltage sensor auto- matically shuts down the alternator.
Page 200 AFMS for VFR NIGHT equipped airplanes Page 3N - 6 2.2. ITOT EATING YSTEM AILURE When the PitotHeat system is activated, the green PITOT HEAT ON safe operating annunciation is ON; If the amber PITOT HEAT caution turns ON, the Pitot Heat system is not functioning properly.
Page 201 AFMS for VFR NIGHT equipped airplanes Page 3N - 7 2.3. G3X F AILURES In case of LH or RH display failure, navigation and engine data will be automati- cally available in the remaining display(split mode). INSTRUCTION: revert to the remaining display. Ed.
Page 202 AFMS for VFR NIGHT equipped airplanes Page 3N - 8 3. AIRPLANE EVACUATION With the engine secured and propeller stopped (if practical): Parking brake: Seat belts: unstrap completely Headphones: REMOVE Door: OPEN Escape away from flames/ hot engine compartment/ spilling fuel tanks/ Hot brakes.
Page 203 AFMS for VFR NIGHT equipped airplanes Page 3N - 9 5. ENGINE FAILURE 5.1. NGINE AILURE URING Throttle: IDLE (keep fully out) Rudder: Keep heading control Brakes: apply as needed When safely stopped: Ignition key: OFF. Fuel selector valve: Electric fuel pump: Alternator&...
Page 204 AFMS for VFR NIGHT equipped airplanes Page 3N - 10 5.3. NGINE AILURES URING LIGHT 5.3.1 Low Fuel Pressure If FP LOW warning is ON: Electric fuel pump: Fuel selector valve: select opposite fuel tankif NOT empty Fuel quantity indicators: Check both If FP LOW warning persists ON: Land as soon as possible applying forced landing procedure (See Para.
Page 205 AFMS for VFR NIGHT equipped airplanes Page 3N - 11 5.3.2 Low Oil Pressure If OP LOW warning is ON: Throttle Lever REDUCEto Minimum practical Land as soon as practical If OP LOWwarning persists ON: Land as soon as possible applying forced landing procedure (See Para. 8) Ed.
Page 206 AFMS for VFR NIGHT equipped airplanes Page 3N - 12 5.3.3 High Oil Temperature If high OT occurs, apply following procedure: If OP LOW warning is ON, see para. 5.3.2 “Low Oil Pressure”. If oil pressure is within limits (OP HIGH and OP LOW warning are OFF): Throttle Lever REDUCE Minimum practical...
Page 207 AFMS for VFR NIGHT equipped airplanes Page 3N - 13 5.3.4 CHT limit exceedance If CHT is above 135°C, apply following procedure: If OP LOW warning is ON, see Para. 5.3.2 “Low Oil Pressure”. If oil pressure is within limits (OP HIGH and OP LOW warnings are OFF): Throttle Lever REDUCE to Minimum practical Land as soon as practical...
Page 208 AFMS for VFR NIGHT equipped airplanes Page 3N - 14 6. IN-FLIGHT ENGINE RESTART After a mechanical engine seizure, fire or a major propeller damage engine restart is not recommended. WARNING Carburettor heat ON if required Electrical fuel pump Fuel quantity indicator CHECK Fuel Selector select opposite tank if not empty...
Page 209 AFMS for VFR NIGHT equipped airplanes Page 3N - 15 7. SMOKE AND FIRE 7.1. NGINE FIRE ON THE GROUND Fuel Selector Electrical fuel pump Ignition key Throttle lever FULL POWER Cabin Heat Alternator&Master Switches Parking Brake ENGAGED Aircraft Evacuation carry out immediately 7.2.
Page 210 AFMS for VFR NIGHT equipped airplanes Page 3N - 16 7.3. NGINE LIGHT Cabin heat: Fuel selector valve: Electric fuel pump: Throttle: FULL FORWARD until the engine stops Ignition key: Cabin vents: OPEN Do not attempt engine restart WARNING Land as soon as possible applying forced landing procedure(See Para. 8). 7.4.
Page 211 AFMS for VFR NIGHT equipped airplanes Page 3N - 17 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 3 – Emergency procedures SMOKE AND FIRE...
Page 212 AFMS for VFR NIGHT equipped airplanes Page 3N - 18 8. LANDING EMERGENCIES 8.1. ORCED ANDING ITHOUT NGINE OWER Flaps: Airspeed: 71 KIAS Find a suitable place to land safely, plan to approach it upwind. Fuel selector valve: Electric fuel pump: Ignition key: Safety belts: Tighten...
Page 213 AFMS for VFR NIGHT equipped airplanes Page 3N - 19 8.4. ANDING If it’s suspected a main tire defect or it’s reported to be defective: 1. Pre-landing checklist: Complete 2. Flaps: Land 3. Land the aeroplane on the side of runway opposite to the defective tire to compensate the change in direction which is to be expected during final rolling 4.
Page 214 AFMS for VFR NIGHT equipped airplanes Page 3N - 20 9. RECOVERY FROM UNINTENTIONAL SPIN If unintentional spin occurs, the following recovery procedure should be used: Throttle: IDLE (full out position and hold) Rudder: full, in the opposite direction of the spin Stick: centralize and hold neutral As the spin stops:...
Page 215 AFMS for VFR NIGHT equipped airplanes Page 3N - 21 10. OTHER EMERGENCIES 10.1. NINTENTIONAL LIGHT CING ONDITIONS Carburettor ice is possible when flying at low engine rpm in visi- ble moisture (outside visibility less than 5 km, vicinity of fog, mist, clouds, rain, snow or hail).
Page 216 AFMS for VFR NIGHT equipped airplanes Page 3N - 22 10.2. YSTEM AILURE Trim Jamming Should trim control be inoperative, act as follows: Breaker: CHECK IN LH/RH Trim switch: CHECK for correct position If jamming persists Trim cutout switch: CHECK ON Speed: adjust to control aircraft without excessive stick force Land aircraft as soon as possible.
Page 217 AFMS for VFR NIGHT equipped airplanes Page 3N - 23 10.3. TATIC PORTS FAILURE In case of static ports failure, the alternate static port in the cabin (identified by the placard below) must be activated. In this case apply following procedure: Cabin heat ALTERNATE STATIC PORT VALVE OPEN...
Page 218 AFMS for VFR NIGHT equipped airplanes Page 3N - 24 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 3 – Emergency procedures OTHER EMERGENCIES...
Page 219 Page S1-11 Supplement S1: pages replacement instructions 4 – N ECTION ORMAL ROCEDURES Supplement S1 – Normal Procedures pages replace basic AFM Section 4 as a whole. Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 220 Page S1-12 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 221 AFMS for VFR NIGHT equipped airplanes Page 4N - 1 SECTION 4 – NORMAL PROCEDURES INDEX Introduction .................. 3 Airspeeds for normal operations ..........3 Pre-flight Inspections ................5 3.1. Cabin Inspection ..................5 3.2. Aircraft Walk-around ..................6 Checklists....................... 12 4.1.
Page 222 AFMS for VFR NIGHT equipped airplanes Page 4N - 2 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 4 – Normal procedures TABLE OF CONTENTS...
Page 223 1. I NTRODUCTION Section 4 describes checklists and recommended procedures for the conduct of normal operations for P2008 JC aircraft. Garmin G3X is NOT intended to be used as primary reference for flight information but only provides information for situa- tional awareness.
Page 224 AFMS for VFR NIGHT equipped airplanes Page 4N - 4 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 4 – Normal procedures AIRSPEEDS FOR NORMAL OPERATIONS...
Page 225 AFMS for VFR NIGHT equipped airplanes Page 4N - 5 3. P FLIGHT NSPECTIONS Before each flight, it is necessary to carry out a complete aircraft check including a cabin inspection followed by an external as below detailed. 3.1. ABIN NSPECTION Aircraft documents (ARC, Certificate of Airworthiness, Noise certificate, Radio COM certificate, AFM): check current and on board...
Page 226 AFMS for VFR NIGHT equipped airplanes Page 4N - 6 3.2. IRCRAFT AROUND To perform the aircraft walk-around, carry out the checklists according to the pattern shown in Figure 4-1. Visual inspection is defined as follows: check for defects, cracks, detachments, excessive play, unsafe or improper installation as well as for general condition.
Page 227 AFMS for VFR NIGHT equipped airplanes Page 4N - 7 Figure 4.1 Left fuel filler cap CHECK desired fuel level (use graduated dipstick). Drain the left fuel tank sump by quick drain valve using a cup to collect fuel (drainage operation must be carried with the aircraft parked on a level surface).
Page 228 AFMS for VFR NIGHT equipped airplanes Page 4N - 8 CHECK inflation, tire condition, alignment, Left main landing gear fuselage skin condition. Check fuselage skin status, tire status (cuts, bruises, cracks and excessive wear), slippage markers integrity, gear structure and brakes hoses :there should be no sign of hydraulic fluid leakage.
Page 229 AFMS for VFR NIGHT equipped airplanes Page 4N - 9 a) Nacelle inlets and exhausts openings must be free of obstructions. Check connection and integrity of air intake system, visually inspect that ram air intake is unobstructed. If inlet and outlet plugs are installed, they must be removed.
Page 230 AFMS for VFR NIGHT equipped airplanes Page 4N - 10 Avoid blowing inside Pitot tube and inside airspeed indicator system's NOTE static ports as this may damage instruments. Ed. 1, Rev. 0 Section 4 – Normal procedures PRE-FLIGHT INSPECTIONS...
Page 231 AFMS for VFR NIGHT equipped airplanes Page 4N - 11 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 4 – Normal procedures PRE-FLIGHT INSPECTIONS...
Page 232 AFMS for VFR NIGHT equipped airplanes Page 4N - 12 4. C HECKLISTS 4.1. EFORE NGINE TARTING FTER FLIGHT NSPECTION Seat position and safety belts: adjust In-flight seat release can cause the loss of airplane control. Check that occupied seats are positively locked: after seat adjustment, make sure that the adjustment lever is well aligned with the aircraft longitudinal axis(neutral position) and that WARNING has a springback return to the neutral position.
Page 233 AFMS for VFR NIGHT equipped airplanes Page 4N - 13 4.2. NGINE TARTING Engine throttle: idle Choke: as needed Fuel selector valve: select the tank with less fuel Electric fuel pump: ON Propeller area: call for CLEAR and visually check Check to insure no person or object is present in the area close to the propeller.
Page 234 AFMS for VFR NIGHT equipped airplanes Page 4N - 14 4.4. AXIING 1. Brakes: check for operation 2. Flight instruments: check altimeter and attitude indicator alignment 4.5. RIOR TO TAKEOFF 1. Parking brake: ON, brake pedal press 2. Engine parameters: check all cautions/warnings OFF , OT within the limits 3.
Page 235 AFMS for VFR NIGHT equipped airplanes Page 4N - 15 4.6. AKEOFF AND CLIMB Primary flight information (airspeed, altitude, heading and atti- tude) is provided by analogue instruments. Flight information provided by G3X is only for situational awareness. WARNING On uncontrolled fields, before line up, check runway wind direc- tion and speed and check for traffic on final WARNING 1.
Page 236 AFMS for VFR NIGHT equipped airplanes Page 4N - 16 4.8. EFORE ANDING Electric fuel pump: ON 2. Fuel valve: select the fullest tank Landing Light: ON On downwind, leg abeam touch down point: Flaps: set T/O Approach speed: 58 KIAS On final leg: Flaps: set LAND Final Approach Speed: 54 KIAS...
Page 237 AFMS for VFR NIGHT equipped airplanes Page 4N - 17 4.11. NGINE SHUT DOWN Parking brake: engage Keep engine running at 1200 propeller rpm for about one minute in order to reduce latent heat. Avionic equipment: OFF Ignition key: OFF, keys extracted Strobe light: OFF Master &...
Page 238 AFMS for VFR NIGHT equipped airplanes Page 4N - 18 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 4 – Normal procedures CHECKLISTS...
Page 239 Page S1-13 Supplement S1: pages replacement instructions 5 - P ECTION ERFORMANCE Refer to Basic AFM Section 5. Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 240 Page S1-14 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 241 Page S1-15 Supplement S1: pages replacement instructions 6 – W ECTION EIGHT AND ALANCE Refer to Basic AFM Section 6. Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 242 Page S1-16 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 243 Page S1-17 Supplement S1: pages replacement instructions 7 – A ECTION IRFRAME AND YSTEM ESCRIPTION Supplement S1 – Airframe and System Description pages replace basic AFM Section 7 as a whole. Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 244 Page S1-18 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 245 AFMS for VFR NIGHT equipped airplanes Page N7 - 1 SECTION 7 – AIRFRAME AND SYSTEMS DESCRIPTION INDEX Introduction ................. 2 Airframe ..................2 2.1. Wing ......................2 2.2. Fuselage ...................... 3 2.3. Empennages ....................3 2.4. Landing gear ....................4 Flight Controls ................
Page 246 Page N7 - 2 1. INTRODUCTION This Section provides description and operation of the aircraft and its systems. 2. AIRFRAME P2008 JC’s airframe can be divided in the following main groups, as highlighted be- low on: 1) Wings 2) Fuselage...
Page 247 2.2. USELAGE The P2008 JC fuselage is mainly made by carbon fibres composite materials. The fuselage is made by two main shells that are later assembled bonding the two main bodies and the floor (composite) and adding aluminium stiffeners that allow the connection of the main landing gear, seats, wing and instrument panel.
Page 248 AFMS for VFR NIGHT equipped airplanes Page N7 - 4 2.4. ANDING GEAR The main landing gear (see Figure 7-3) consists of two special steel leaf-springs posi- tioned crossways to the fuselage. Fig. 7-3.M ANDING EAR STRUCTURE The steel leaf-springs are attached to the fuselage structure via two couples of ma- chined aluminium beams.
Page 249 AFMS for VFR NIGHT equipped airplanes Page N7 - 5 3. FLIGHT CONTROLS Aircraft flight controls are operated through conventional stick and rudder pedals. Longitudinal control acts through a system of push-rods and is equipped with a trim tab. a cable control circuit is confined within the cabin and it is connected to a pair of push-pull rod systems positioned in each main wing which control ailer- ons differentially.
Page 250 AFMS for VFR NIGHT equipped airplanes Page N7 - 6 4. INSTRUMENT PANEL The instrument panel is divided in four areas:  The left area holds primary (analogue) and pilot’s situational awareness (G3X LH display) flight instruments, a chronometer, a pitch trim indicator and a holds Day/night switch (selecting between two brightness levels for warning lights in the annunciator panel);...
Page 251 AFMS for VFR NIGHT equipped airplanes Page N7 - 7 Fig. 7-5. I NSTRUMENT ANEL 4.1. NTERNAL IGHTS YSTEM An internal lights system is provided; it’s based on the following elements:  2 dimmable panel lights (with flexible and adjustable supports) located in both sides of the dashboard and 2 LED lights above the annunciator panel (Panel DIM device);...
Page 252 AFMS for VFR NIGHT equipped airplanes Page N7 - 8 4.3. ABIN The cabin heat control knob is positioned on the lower right side of the instrument panel; when knob is pulled fully outward, cabin receives maximum hot air. If the outlets are kept closed, hot air only performs windshield defrost.
Page 253 6. DOORS Two doors are provided for P2008 JC, on Pilot and co-pilot side. A sketch of the door is shown below (RH and LH doors are specular): Gas spring support...
Page 254 AFMS for VFR NIGHT equipped airplanes Page N7 - 10 7. POWERPLANT 7.1. ENGINE Manufacturer: Bombardier-Rotax GmbH Model: ROTAX 912 S2 Type: 4 stroke, horizontally-opposed 4 cylinder, mixed air and water cooled, twin electronic ignition, forced lubrication. Maximum rating: 98.6hp (73.5kW) @ 5800 rpm/min (2388 rpm/min. prop). Gear reduction ratio - 2.4286:1 Max oil consumption: Max: 0.1 litres/hour 7.2.
Page 255 AFMS for VFR NIGHT equipped airplanes Page N7 - 11 8. FUEL SYSTEM The fuel system is designed to supply the reciprocating engine (Bombardier-Rotax 912 S2) with the suitable flow rate and pressure according to engine limitations re- quired by Rotax manuals. Following figure shows the fuel system schematic of P2008JC airplane.
Page 256 AFMS for VFR NIGHT equipped airplanes Page N7 - 12 9. ELECTRICAL SYSTEM Primary DC power is provided by an external alternator with a 14 VDC output, rated to 40 Amps @ 5800 rpm. During normal operations, it recharges the battery. Secondary DC power is provided by a battery (Main) which provides the energy ne- cessary for feeding the essential electrical loads in the event of a alternator failure.
Page 257 9.2. VIONICS The avionic system installed P2008 JC is based on five analogue indicators, an air- speed indicator, an attitude indicator, an altimeter, a magnetic compass and a slip in- dicator, which provide primary flight information on the left side of the instrument panel.
Page 258 AFMS for VFR NIGHT equipped airplanes Page N7 - 14 9.3. XTERNAL OWER UPPLY On the right side of the tail cone, an external power is present. Using this device it is possible to feed the electric system directly on the bus bar, by an external power source.
Page 259 Page N7 - 15 10. PITOT-STATIC PRESSURE SYSTEMS The P2008 JC air speed/altitude indicating systems are connected with a Pitot-Static system based on a total pressure/Pitot probe (Heated Pitot tube) mounted under left wing and two static pressure ports connected in parallel and located in correspon- dence of engine firewall on left and right side of fuselage.
Page 260 Page N7 - 16 11. BRAKES The P2008 JC is provided with an independent hydraulically actuated brake system for each main wheel. A master cylinder is attached to each pilot’s rudder pedal Hy- draulic pressure, applied via the master cylinders, enters the brake via lines con- nected to the caliper.
Page 261 AFMS for VFR NIGHT equipped airplanes Page N7 - 17 INTENTIONALLY LEFT BLANK Ed. 1, Rev 0 Section 7 – Airframe and Systems description BRAKES...
Page 262 AFMS for VFR NIGHT equipped airplanes Page N7 - 18 INTENTIONALLY LEFT BLANK Ed. 1, Rev 0 Section 7 – Airframe and Systems description BRAKES...
Page 263 Page S1-19 Supplement S1: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Refer to Basic AFM section 8. Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...
Page 264 Page S1-20 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Supplement no.S1- VFR NIGHT EQUIPMENT CONFIGURATION...

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