Tecnam P2008 Flight Manual
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Tecnam P2008 Flight Manual

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FLIGHT MANUAL
US-LSA

P2008

Manufacturer
COSTRUZIONI AERONAUTICHE TECNAM S.r.l.
Serial number: ________________
Build year: ___________________
Registration: __________________
Introduction
This manual contains information to be furnished to the pilot as required by the FAA in addition to further information
supplied by the manufacturer.
This manual must always be present on board the aircraft.
The aircraft is to be operated in compliance with information and limitations contained herein. All sections follow the
ASTM guidelines as finalized 14December 2007.
Ed2 rev2- 06/02/2014

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May 20, 2025

Is the electric trim standard with the Tecnam 2008; is it a required item?

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Summary of Contents for Tecnam P2008

  • Page 1: P2008

    FLIGHT MANUAL US-LSA P2008 Manufacturer COSTRUZIONI AERONAUTICHE TECNAM S.r.l. Serial number: ________________ Build year: ___________________ Registration: __________________ Introduction This manual contains information to be furnished to the pilot as required by the FAA in addition to further information supplied by the manufacturer.
  • Page 2 Any revisions to the present Manual, except actual weighing data, must be recorded in the following table. New or amended text in the revised pages will be indicated by a black vertical line in the left-hand margin; Log of Revisions Revision No. Date released Chapters Approved By 25/11/2013 TECNAM 06/02/2014 TECNAM...
  • Page 3 List of Effective Pages Page Date Page Date Page Date 18-03-2013 “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “ “...

  • Page 4: Table Of Contents

    Table of Contents P2008 ....................................1 Unit Conversion Chart ..............................10 SECTION 1 GENERAL ................................11 Introduction ................................11 Certification Basis ..............................11 Descriptive Data ..............................13 1.3.1 Airframe ................................13 Powerplant ................................13 1.4.1 Engine ................................13 1.4.2 Allowed Propellers............................13 1.4.3...

  • Page 5: Introduction

    1.9.6 Fuel Pressure ..............................22 1.9.7 O.A.T. Indicator ............................... 22 1.9.8 Stall Warning System ............................22 1.9.9 Avionics................................22 1.9.10 Exterior Lighting.............................. 22 1.10 Pitot and Static Pressure Systems ........................... 23 1.11 Landing Gear ................................24 1.11.1 Brake System ..............................25 SECTION 2 OPERATING LIMITATIONS ..........................26 Introduction ................................26 2.1.1...
  • Page 6 SECTION 4 PERFORMANCE ..............................37 Introduction ................................37 Use of Performance Charts ............................. 37 Airspeed Indicator System Calibration ........................38 ICAO Chart ................................39 Stall Speeds ................................40 Crosswind ................................41 Takeoff Performance .............................. 42 Landing Distance ..............................43 Climb Performance ..............................44 Cruise ..................................
  • Page 7 SECTION 7 GROUND HANDLING & SERVICE ........................60 Introduction ................................60 Aircraft Inspection Periods............................60 Aircraft Alterations or Repairs ..........................60 Ground Handling ..............................60 7.3.1 Towing ................................60 7.3.2 Parking and Tiedown ............................60 7.3.3 Jacking ................................60 7.3.4 Leveling ................................60 7.3.5 Road Transport ...............................
  • Page 8 Abbreviations & Terminology Airspeed Terminology KCAS Calibrated Airspeed is the indicated airspeed corrected for position and instrument error and expressed in knots. KIAS Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. KTAS True Airspeed is the airspeed expressed in knots relative to undisturbed air, which is KCAS, corrected for altitude and temperature.
  • Page 9 Airplane Performance and Flight Planning Terminology Crosswind is the velocity of the crosswind component for which adequate control of the airplane Velocity during takeoff and landing is guaranteed Usable fuel is the fuel available for flight planning Unusable fuel is the quantity of fuel that cannot be safely used in flight is the acceleration of gravity is the takeoff distance measured from actual start to wheel lift off point is total takeoff distance measured from start to clearing a 50’...

  • Page 10: Unit Conversion Chart

    Unit Conversion Chart by  Multiplying Yields Temperature Fahrenheit [°F] Celsius [°C] ⋅ −   Celsius [°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...

  • Page 11: Section 1 General

    1.1 Introduction The P2008 is an high wing, two-place, single-engine airplane equipped with tricycle landing gear. It has metal wings and Stabilator and composite fuselage and vertical stabilizer. It is an ASTM compliant airplane designed to be flown by sport pilot rated pilots as well as higher rated pilots.
  • Page 12 THREE VIEW DRAWING Figure 1-1 General Views Wing Span 9.00 m (29.5 ft) Length 6.93 m (22.7 ft) Tail height 2.46 m (8.1 ft) Propeller ground clearance 310 + 40 mm (12.2 +1.6 in) Minimum ground steering radius 5.50 m (18.0 ft) NOTE •...

  • Page 13: Descriptive Data

    Number of blades Diameter 1730 mm (68”) (no reduction permitted) Type Fixed pitch – wood / composite Manufacturer Sensenich Model 2A0R5R70EN Number of blades Diameter 1778 mm (70”) (no reduction permitted) Type Fixed - ground adjustable pitch Spacer B-1805-81 TECNAM Spacer...

  • Page 14: Oil System

    3B0R5R68C Number of blades Diameter 1730 (68'') (no reduction permitted) Type Fixed - ground adjustable pitch Spacer B-1805-81 TECNAM Spacer 1.4.3 Oil System Oil system Forced, with external oil reservoir See Rotax operator’s manual Oil Capacity Max. 3.0 liters (3.2 qt) – min. 2.0 liters (2.1 qt) 1.4.4...

  • Page 15: Standard Equipment

    1.6 Standard Equipment 1.6.1 Flight Instruments Airspeed Indicator, Altimeter, Vertical Speed Indicator, Compass 1.6.2 Engine instruments Tachometer, Oil Pressure, Fuel Pressure, Oil Temperature, Cylinder Head Temperature, Hour Meter, Left and Right Fuel Quantity, Volt Meter 1.6.3 Warning Lights and Indicators Trim Indicator, Flap Indicator, Generator Warning Light 1.6.4 Controls...

  • Page 16: Airframe

    1.7 Airframe 1.7.1 Wing The wing is constructed of a central light alloy torque box; an aluminum leading edge is attached to the front spar while flap and aileron are hinged to rear spar. Flaps are constructed of a center spar to which front and rear ribs are joined; wrap- around aluminum skin panels cover the flap structure.

  • Page 17: Instrument Panel

    Release the lever when the desired position is found making sure that the locking pin reengages in the seat track. P2008 is equipped with standard bucket seat for the access to the baggage compartment. The same lever allows the pilot to regulate the seat in two position: 20° and 25° to increase the flight comfort.

  • Page 18: Doors

    1.7.10 Doors Standard doors feature a composite frame supporting a clear or tinted window. An internal safety latch mechanism is positioned in proximity of door's upper edge and must be used before flight to secure door. Mechanism rotates, before flight, to engage doorframe to cabin composite frame. 1.7.11 Baggage compartment The baggage compartment is located behind the seats.

  • Page 19: Powerplant

    The Sensenich 2 or 3 blades propellers are also allowed to be mounted with the Sensenich provided installation kit for Tecnam. For Propeller installation see the manufacturer’s AMM P/N 2A0 (2 Blades) and 3B0R5 / 3B0R5-FD (3 Blades). The propeller pitch must be always set following Tecnam related Job Card N° 448 (Sensenich 2/3 Blades Installation and Settings) to ensure the pitch will not allow the airplane to fly over the maximum legal 120KCAS and in order to avoid overspeeds which could damage the engine.
  • Page 20 LH FUEL QUANTITY INDICATOR RH FUEL QUANTITY INDICATOR LH FUEL QUANTITY SENSOR RH FUEL QUANTITY SENSOR FUEL VENT FUEL VENT LH FUEL TANK RH FUEL TANK SUMP SUMP FUEL PRESSURE INDICATOR MESH FILTER + TANK DRAIN FIREWALL ELECTRIC FUEL PUMP FUEL PRESSURE SENDER FILTER MECHANICAL FUEL PUMP...

  • Page 21: Electrical System

    1.9 Electrical System The aircraft's electrical system consists of a 12 VoltDC circuit controlled by a Master switch located on the instrument panel. An integrated AC generator provides electricity and a 12 Volt battery placed in the fuselage or in the engine compartment.

  • Page 22: Cylinder Head Temperature

    1.9.4 Cylinder head temperature The cylinder head temperature gauge normally reads the number three cylinder head temperature. It also indirectly reflects the coolant temperature. The cylinder head temperature reads in degrees Celsius. NOTE The same fuse protects all temperature instruments. 1.9.5 Oil Pressure The oil pressure gauge is electric and is protected by a fuse.

  • Page 23: Pitot And Static Pressure Systems

    1.10 Pitot and Static Pressure Systems The airspeed indicator system for the aircraft is shown below. On the left wing’s strut the Pitot tube (1) while on the fuselage’s sides there are two static ports (2). Two flexible hoses (3) feed the airspeed indicator (4), the altimeter (5) and the VSI (6) on the instrument panel.

  • Page 24: Landing Gear

    1.11 Landing Gear The main landing gear consists of two special steel spring-leaf struts positioned crossways to fuselage for elastic cushioning of landing loads. The two steel spring-leaf struts are attached to the fuselage underside via the main girder. Two rawhide liners are inserted between each spring-leaf and the girder. Two bolts and nuts secure the individual spring- leaf to the edge of the girder via a light alloy clamp while a single bolt and nut secures the inboard end of the leaf-spring to the girder.

  • Page 25: Brake System

    1.11.1 Brake System Figure 7-2 shows the brake system schematic diagram. The left and right wheel brakes are independent systems. The system has a reservoir (4) on the co-pilot’s brake pedals (1). The reservoir is directly connected to the brake master cylinders (3). Two flexible hoses connect the master cylinders on the co-pilot’s brake pedals to the master cylinders on the pilot’s brake pedals.

  • Page 26: Section 2 Operating Limitations

    SECTION 2 OPERATING LIMITATIONS 2 Introduction Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the P2008, its engine, standard systems and standard equipment. 2.1.1 Airspeed Limitations Airspeed limitations and their operational significance are shown below:...

  • Page 27: Powerplant Limitations

    2.1.3 Powerplant Limitations The following table lists operating limitations for aircraft installed engine: Engine manufacturer: Bombardier Rotax GmbH. Engine model: 912 ULS or S2 Maximum power: (see table below) Max Power Max rpm. Time max. kW (hp) rpm prop.(engine) (min) Max.

  • Page 28: Lubricant

    2.1.8 Lubricant Viscosity Use viscosity grade oil as specified in the following table: Warning Admissible pressure for cold start is 7 bar maximum for short periods Warning Use of Aviation Grade Oil with or without additives is not permitted 2.1.9 Coolant Coolant type and specifications are detailed into the “Rotax Operator’s Manual”...

  • Page 29: Powerplant Instrument Markings

    2.1.13 Powerplant Instrument Markings Powerplant instrument markings and their color code significance are shown below: Red line Green arc Yellow arc Red line Instrument Minimum limit Normal operating Caution Maximum limit Engine Tach Rpm -------- 1400-5500 5500-5800 5800 Oil Temp. °C 90-110 50 - 90...

  • Page 30: Maneuvering Load Factor Limits

    Warning Limit load factor could be exceeded by moving the flight controls abruptly to full control deflection at a speed above V (Maneuvering Speed). 2.1.18 Maneuvering Load Factor Limits Maneuvering load factors are as follows: Flaps 0° 2.1.19 Flight Crew Minimum crew for flight is one pilot seated on the left side.

  • Page 31: Day Vfr

    2.1.21 Day VFR The airplane, in standard configuration, is approved only for day VFR operations under VMC: • Altimeter • Airspeed Indicator • Compass • Fuel Gauges • Oil Pressure Indicator • Oil Temp. Indicator • Cylinder Head Temp. Indicator •...

  • Page 32: Section 3 Weight & Balance

    SECTION 3 WEIGHT & BALANCE 3 Introduction This section describes the procedure for establishing the basic empty weight and moment of the aircraft. Loading procedure information is also provided. 3.1 Aircraft weighing procedures 3.1.1 Preparation • Carry out weighing procedure inside closed hangar •...

  • Page 33: Weighing Report

    3.2 Weighing report Model P2008____________S/N ________________ Date ________________ Datum Reference line W2=WL+WR Datum: Propeller support flange w/o spacer. - Equipment list, date: _____ meters Nose wheel weight W Plumb bob distance LH wheel LH wheel weight Plumb bob distance RH wheel RH wheel weight Average distance (A Bob distance from nose wheel...
  • Page 34 Figure 3-1...

  • Page 35: Weight And Balance

    3.3 Weight and Balance In order to compute the weight and balance of this aircraft, we have provided the following loading charts. This will reduce the amount of math you need. To compute weight and balance use the formula: Weight * Arm = Moment. Pilot &...

  • Page 36: Loading

    Get moments from loading charts Obtain the empty weight and moment from the most recent weight and balance Insert the weights and the moments for fuel, occupants and baggage from the previous chart Total the weight and the moment columns Divide the total moment by the total weight to get the arm Check that the total weight does not exceed maximum gross weight of 1320 pounds Check that the arm falls within the C.G.

  • Page 37: Section 4 Performance

    SECTION 4 PERFORMANCE 4 Introduction This section provides all necessary data for accurate and comprehensive planning of flight activity from takeoff to landing. Data reported in graphs and/or tables were determined using: • “Flight test data” with conditions as prescribed by ASTM and bilateral agreements •...

  • Page 38: Airspeed Indicator System Calibration

    4.2 Airspeed Indicator System Calibration Graph shows calibrated airspeed V as a function of indicated airspeed V Fig. 4-1 Calibrated vs. Indicated Airspeed flaps full deflected The following formula gives the CAS with the CAS = 1.0611xIAS – 7.7222...

  • Page 39: Icao Chart

    4.3 ICAO Chart Fig. 4-2 ICAO C HART...

  • Page 40: Stall Speeds

    4.4 Stall Speeds Conditions: - Weight 600 kg (1320 lbs) - Throttle: idle - No ground effect NOTE Altitude loss during conventional stall recovery as demonstrated during test flights is approximately 100ft with banking under 30°. KIAS KCAS FLAPS 0°...

  • Page 41: Crosswind

    4.5 Crosswind Maximum demonstrated crosswind velocity is 15 knots Fig. 4-3 Crosswind chart...

  • Page 42: Takeoff Performance

    4.6 Takeoff Performance TAKEOFF DISTANCE Conditions: Flaps: 15° Runway: dry, compact, grass Engine: full throttle Slope: 0° Wind: zero Vr = 48 KIAS [44KCAS] = 50 KIAS [45KCAS] ≥ 200 ft/min Vx flaps 15 = 63 KIAS [62KCAS] Decrease distances by 10% for each 10 Knots of headwind. Increase distances by 20 % for each 10 Knots of tailwind For dry and paved runway operation decrease ground run by 6 %.

  • Page 43: Landing Distance

    4.7 Landing Distance ONDITIONS Maximum weight = 600 kg (1320 lbs) Engine: throttle idle Brakes: maximum braking Runway: dry, compact grass Slope: 0° Wind: zero Conditions: ISA Flaps: 35° NOTE Decrease distances by 10% for each 10 Knots of headwind. Increase distances by 20 % for each 10 Knots of tailwind; For dry and paved runway operation increase ground run by 10% If it becomes necessary to land without flap extension (flap malfunction), increase approach speed by 10 Knots, increase by landing distance by 40% distance pertaining to flap setting at 35°...

  • Page 44: Climb Performance

    4.8 Climb Performance CLIMB RATE IN CLEAN CONFIGURATION ONDITIONS • Flap: 0° • Engine: Full throttle • = 69 KIAS [67KCAS] Fig. 4-5 C LIMB ⇒ Example: Given Find O.A.T. = 17°C Rate of climb = 654 ft/min Pressure altitude = 5600 ft Weight = 580 Kg (1279 lb)

  • Page 45: Cruise

    4.9 Cruise Maximum takeoff weight = 600 kg (1320 lbs) Fuel tanks 2x52 liters (13.7 gal) (less the unusable fuel = 1.1gal) ALL ENDURANCE DATA (HOURS AND n.m.) ARE GIVEN WITH A RESERVE OF 30’ (FOR EXAMPLE: THE FIRST ROW INDICATES A RANGE OF 5.8hrs + 0.5hr RESERVE) OAT: +15°C Pressure altitude H Endurance (hrs)

  • Page 46: Effects Of Rain And Insects

    ONDITIONS Maximum weight = 600 kg (1320 lb) Engine: full throttle Flaps: 35° 15 flaps = 63 KIAS [62 KCAS] NOTE During balked landing maneuver, flaps should be retracted immediately after applying full power. Fig.5-6. BALKED LANDING 4.11 Effects of Rain and Insects Flight tests have demonstrated that neither rain nor insect impact build-up on leading edge has caused substantial variations on aircraft's flight qualities.

  • Page 47: Section 5 Emergency Procedures

    SECTION 5 EMERGENCY PROCEDURES 5 Introduction Section 6 includes checklists and detailed procedures to be used in the event of emergencies. Emergencies caused by a malfunction of the aircraft or engine is extremely rare if appropriate maintenance and pre-flight inspections are carried out. In case of emergency, suggestions of the present section should be considered and applied as necessary to correct the problem.

  • Page 48: Engine Failures

    5.1 Engine Failures If an emergency arises, the basic guidelines described in this section should be considered and applied as necessary to correct the problem. 5.1.1 Engine Failures on Ground 5.1.1.1 ENGINE FAILURE DURING TAKEOFF RUN Throttle: ..................IDLE Brakes:..................APPLY AS NEEDED Ignition Switches: ..............

  • Page 49: Smoke And Fire

    5.1.2.4 LOW OIL PRESSURE Oil temperature: ................. CHECK If the temperature tends to increase: If stable within the green arc: ............ LAND as soon as possible If increasing: ................LAND as soon as possible and be alert for impending engine failure 5.1.2.5 IN-FLIGHT ENGINE RESTART...

  • Page 50: Cabin Fire During Flight

    5.2.4 Cabin Fire during Flight Cabin heat: ................OFF Cabin vents: ................OPEN Doors: ..................OPEN, if necessary Master switch: ................OFF Try to choke the fire. Direct the fire extinguisher towards flame base Procedure for a forced landing: ..........APPLY 5.3 Landing Emergency FORCED LANDING WITHOUT ENGINE POWER Establish: ...................

  • Page 51: Recovery From Unintentional Spin

    5.4 Recovery from Unintentional Spin Power: ..................IDLE Ailerons: ..................NEUTRAL (and Flaps Up) Rudder: ..................FULL OPPOSITE Elevator: ..................THROUGH NEUTRAL HOLD THESE INPUTS UNTIL ROTATION STOPS, THEN: Rudder: ..................NEUTRAL Elevator: ..................RECOVER NOTE Use elevator control to recover to straight and level or a climbing attitude NOTE The first letter in each of the four primary recovery inputs spells out the acronym, PARE (pronounced “pair”).

  • Page 52: Electric Power System Malfunction

    5.6 Electric Power System Malfunction Electric power supply system malfunctions may be avoided by carrying out inspections as scheduled and prescribed in the Service Manual. Causes for malfunctions are hard to establish but, in any case, problems of this nature must be dealt with immediately.

  • Page 53: Section 6 Normal Procedures

    SECTION 6 NORMAL PROCEDURES 6 Introduction Section 6 contains checklists and the procedures for normal operation. 6.1 Removing and Reinstalling the Engine Cowling 6.1.1 Upper Cowling Parking brake: .........ON Fuel selector valve: ......OFF Ignition Switches: ......OFF Master switch: .........OFF • Unlatch all four butterfly Cam-locks mounted on the top cowling by rotating them 90°...

  • Page 54: Checklist Procedures

    6.2 Checklist Procedures 6.2.1 Pre-Flight Inspection Before each flight, it is necessary to carry out a complete inspection of the aircraft starting with an external inspection followed by an internal inspection. 6.2.1.1 Cabin Inspection All required paperwork: ............ONBOARD Weight and balance: ..............CHECK Safety belts used to lock controls: ..........
  • Page 55 6.2.1.2 External Inspection It is best to follow to follow the external inspection in the station order outlined in fig. 6-1 so nothing is missed. Visual inspection is defined as follows: check for defects, cracks, detachments, excessive play, and unsafe or improper installation as well as for general condition.
  • Page 56 • Check no foreign objects are present • Check the cooling system for losses, check coolant reservoir level, and insure radiator honeycomb is unobstructed • Check oil system for losses, check oil reservoir level, and insure radiator honeycomb is unobstructed •...
  • Page 57 Strobe light: ................ON Ignition Switches: ..............ON Master Switch:................START NOTE Starter duty cycle: max of 10 seconds on followed by a cooling period of 2 minutes off Oil pressure: ................CHECK WARNING If oil pressure doesn’t rise within 10 seconds, shut down engine. The maximum oil pressure for cold conditions is 7 bar.
  • Page 58 Magnetic compass and DG: ............CHECK, SET Throttle: ..................FULL NOTE Static RPM is approximately 5100 ± 250 rpm Engine instruments: ..............CHECK Vr (Rotation speed): ..............~ 48 KIAS [44 KCAS] NOTE Rotate to takeoff attitude and accelerate to a climb speed of 60 knots with 15° Flaps Above 300’...
  • Page 59 6.2.1.13 ENGINE SHUT DOWN Keep engine running at 2500 rpm for about one minute in order to reduce latent heat. This can be accomplished during taxi. NOTE Do not ride the brakes to facilitate cool down. If necessary, stop for one minute with parking brake on to cool the engine. Electrical equipment (except the Strobe Light): ......

  • Page 60: Section 7 Ground Handling & Service

    SECTION 7 GROUND HANDLING & SERVICE 7 Introduction This section contains factory-recommended procedures for proper ground handling and routine care and servicing. It also identifies certain inspection and maintenance requirements, which must be followed if the aircraft is to retain its new-plane performance and dependability.

  • Page 61: Cleaning And Care

    7.3.6 Cleaning and Care To clean painted surfaces, use a mild detergent such as shampoo normally used for car finish; use a soft cloth for drying. The plastic windshield and windows should never be dusted when dry; use lukewarm soapy water and dry using chamois only.

  • Page 62: Placards And Markings

    Section 8 PLACARDS & MARKINGS 8 Placards and Markings 8.1.1 Magnetic compass compensation table To compensate the deviation errors of the magnetic compass, the following correction table is located just below the compass: Steer Steer DATE RADIO ON AIRPATH 8.1.2 Engine throttle friction A throttle friction lock is located on the side of central to keep the desired throttle friction setting.

  • Page 63: Trim Switch

    8.1.5 Trim switch The trim shunt control is located on the upper left area of the instrument panel alternatively allocating trim control to either Rh or Lh control stick. The following placard (25x14mm) is positioned just above of it. 8.1.6 Breakers Breakers are located on the lower/right side of the instrument panel and each fuse is individually marked as follows: Depending on the specific equipment installed on the a/c the type and position of the breakers could vary from the above...

  • Page 64: Choke

    8.1.9 Choke Located above the choke lever: 8.1.10 Generator light A generator warning light is located on the upper/right side of the instrument panel and it is marked with the following label. 8.1.11 Fuel selector valve Fuel shutoff valve is located on central section of cockpit panel. It controls the fuel coming from the tanks making the pilot able to switch LEFT TANK, RIGHT TANK and OFF.

  • Page 65: Oil Tank Reservoir

    8.1.13 Oil tank reservoir On the oil tank reservoir are present two placards (30x12mm) indicating the type and quantity of engine’s oil stored into the reservoir. 8.1.14 Cooling system overflow tank Located on the overflow tank inside the engine cowling left side, is located the following placard (60x15mm): 8.1.15 Brake oil reservoir On the cap of the brake’s oil tank, is a placard indicating the type of oil that must be used.

  • Page 66: Identification Plate

    The following placard is located on the pilot side of the empennage forward of the stabilator and made of stainless steel. Builder: CostruzioniAeronauticheTecnam Model: P2008 Serial number: XXX 8.1.19 Static port On each static port is locate a placard diam 20mm: 8.1.20 Fuel Tank...
  • Page 67 On the pilot’s panel a placard will state the following: NO INTENTIONAL SPINS Located on the instrument panel is the following placard: This aircraft was manufactured in accordance with Light Sport aircraft airworthiness standards and does not conform to standard category airworthiness requirements.

  • Page 68: Supplement List

    SUPPLEMENT LIST 9 SUPPLEMENT LIST 9.1 Introduction This Section concerns the supplemental manuals of additional (or optional) instrumentation equipping the P2008 and/or information and limitations related to installed equipment configuration or needed to fit local national rules. 9.2 Supplements list...
  • Page 69 INTENTIONALLY LEFT BLANK...
  • Page 70 P2008 Flight Manual Feedback Form Send your comments to: In the USA: Tecnam North America Headquarters 7511 Airfield Drive, Box 8 Richmond, VA 23237 1-888-359-4682 www.tecnam.net info@tecnam.net (770) 309-4155 Italian Address: www.tecnam.com COSTRUZIONI AERONAUTICHE TECNAM s.r.l. Via Maiorise 81043 Capua (CE) - ITALY ...
  • Page 71 P2008 Flight Manual SUPPLEMENT No. S1 AIRSPEED INCREMENT Record of Revisions Any revisions to the present Manual, except actual weighing data, must be recorded in the following table. New or amended text in the revised pages will be indicated by a black vertical line in the left-hand margin;...
  • Page 72 P2008 Flight Manual List of Effective Pages Page Date Page Date 25/11/2013 “ “ “ “ “ “ “ “ “ “ “ “ “...
  • Page 73 P2008 Flight Manual Table of Contents SUPPLEMENT No. S1 AIRSPEED INCREMENT ....................... 1 Record of Revisions ..............................1 Log of Revisions ................................1 List of Effective Pages ..............................2 Table of Contents ............................... 3 Introduction ................................5 Section 1 –General..............................7 Section 2 –Operating Limitations ..........................
  • Page 74 P2008 Flight Manual INTENTIONALLY LEFT BLANK...
  • Page 75 Airspeeds increment in subject. It is the owner’s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section. NOTE: TECNAM reminds that flights in yellow arcs should be only performed in smooth with caution.
  • Page 76 P2008 Flight Manual INTENTIONALLY LEFT BLANK...

  • Page 77: Section 1 -General

    P2008 Flight Manual Supplement S1: pages replacement instructions Section 1 –General Refer to Basic AFM Section 1.
  • Page 78 P2008 Flight Manual INTENTIONALLY LEFT BLAN...

  • Page 79: Section 2 -Operating Limitations

    P2008 Flight Manual Supplement S1: pages replacement instructions Section 2 –Operating Limitations Apply following pages replacement procedure: Supplement S1 – Basic AFM LIMITATIONS page Section 2 page REPLACES Page 26 REPLACES Page 27...
  • Page 80 P2008 Flight Manual INTENTIONALLY LEFT BLANK...
  • Page 81 OPERATING LIMITATIONS 2. Introduction Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the P2008, its engine, standard systems and standard equipment. 2.1.1 Airspeed Limitations Airspeed limitations and their operational significance are shown below:...
  • Page 82 P2008 Flight Manual 2.1.3 Powerplant Limitations The following table lists operating limitations for aircraft installed engine: Engine manufacturer: Bombardier Rotax GmbH. Engine model: 912 ULS or S2 Max Power Max rpm. Time max. kW (hp) rpm prop.(engine) (min) Max. 73.5 (98.5) 2388 (5800) Max cont.
  • Page 83 P2008 Flight Manual Supplement S1: pages replacement instructions Section 3 – Weight & Balance Refer to Basic AFM Section 3.
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  • Page 85: Section 4 -Performance

    P2008 Flight Manual Supplement S1: pages replacement instructions Section 4 –Performance Apply following pages replacement procedure: Supplement S1 – Basic AFM Performance page Section 4 page REPLACES Page 38 REPLACES Page 39 Page 40 REPLACES REPLACES Page 41...
  • Page 86 P2008 Flight Manual INTENTIONALLY LEFT BLANK...
  • Page 87 P2008 Flight Manual 4.4 Airspeed Indicator System Calibration Graph shows calibrated airspeed V as a function of indicated airspeed V IAS-CAS kts FLAP CLEAN Fig. 4-1 Calibrated vs. Indicated Airspeed flaps full deflected The following formula gives the CAS with the...
  • Page 88 P2008 Flight Manual 4.5 ICAO Chart Fig. 4-2 ICAO C HART...
  • Page 89 P2008 Flight Manual 4.6 Stall Speeds Conditions: - Weight 600 kg (1320 lbs) - Throttle: idle - No ground effect NOTE Altitude loss during conventional stall recovery as demonstrated during test flights is approximately 200ft with banking under 30°. KIAS...
  • Page 90 P2008 Flight Manual 4.7 Crosswind Maximum demonstrated crosswind velocity is 15 knots Fig. 4-3 Crosswind chart...

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