Tecnam P2008 Technical specifications

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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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;
Log of Revisions
Revision No.
Date released
Chapters
Approved By
01
25/11/2013
9
TECNAM
02
06/02/2014
6
TECNAM

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Table of Contents
P2008 ............................................................................................................................................................................... 1
Unit Conversion Chart .................................................................................................................................................... 10
SECTION 1 GENERAL........................................................................................................................................................11
1.1 Introduction ............................................................................................................................................................ 11
1.2 Certification Basis ................................................................................................................................................... 11
1.3 Descriptive Data ..................................................................................................................................................... 13
1.3.1 Airframe.......................................................................................................................................................... 13
1.4 Powerplant ............................................................................................................................................................. 13
1.4.1 Engine ............................................................................................................................................................. 13
1.4.2 Allowed Propellers.......................................................................................................................................... 13
1.4.3 Oil System ....................................................................................................................................................... 14
1.4.4 Cooling............................................................................................................................................................ 14
1.4.5 Fuel ................................................................................................................................................................. 14
1.5 Weights................................................................................................................................................................... 14
1.5.1 Maximum Weights ......................................................................................................................................... 14
1.5.2 Standard Weights ........................................................................................................................................... 14
1.5.3 Specific Loadings............................................................................................................................................. 14
1.6 Standard Equipment............................................................................................................................................... 15
1.6.1 Flight Instruments .......................................................................................................................................... 15
1.6.2Engine instruments......................................................................................................................................... 15
1.6.3 Warning Lights and Indicators........................................................................................................................ 15
1.6.4 Controls .......................................................................................................................................................... 15
1.6.5 Interior............................................................................................................................................................ 15
1.6.6 Exterior ........................................................................................................................................................... 15
1.6.7 Powerplant and Accessories........................................................................................................................... 15
1.7 Airframe.................................................................................................................................................................. 16
1.7.1 Wing ............................................................................................................................................................... 16
1.7.2 Fuselage.......................................................................................................................................................... 16
1.7.3 Empennage..................................................................................................................................................... 16
1.7.4 Flight controls................................................................................................................................................. 16
1.7.5 Instrument Panel ............................................................................................................................................ 17
1.7.6 Carburetor Heat.............................................................................................................................................. 17
1.7.7 Cabin Heat / Defrost....................................................................................................................................... 17
1.7.8 Throttle Friction Lock...................................................................................................................................... 17
1.7.9 Seats, Seatbelts, and Shoulder harnesses ...................................................................................................... 17
1.7.10 Doors .............................................................................................................................................................. 18
1.7.11 Baggage compartment ................................................................................................................................... 18
1.8 Powerplant ............................................................................................................................................................. 19
1.8.1 Engine ............................................................................................................................................................. 19
1.8.2 Propeller ......................................................................................................................................................... 19
1.8.3 Fuel system..................................................................................................................................................... 19
1.9 Electrical System..................................................................................................................................................... 21
1.9.1 Generator light ............................................................................................................................................... 21
1.9.2 Voltmeter ....................................................................................................................................................... 21
1.9.3 Oil temperature gauge ................................................................................................................................... 21
1.9.4 Cylinder head temperature ............................................................................................................................ 22
1.9.5 Oil Pressure..................................................................................................................................................... 22

5
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
2Introduction ............................................................................................................................................................26
2.1.1 Airspeed Limitations....................................................................................................................................... 26
2.1.2 Airspeed Indicator Markings .......................................................................................................................... 26
2.1.3 Powerplant Limitations .................................................................................................................................. 27
2.1.4 Temperatures ................................................................................................................................................. 27
2.1.5 Oil Pressure..................................................................................................................................................... 27
2.1.6 Operating & starting temperature range ....................................................................................................... 27
2.1.7 Fuel Pressure .................................................................................................................................................. 27
2.1.8 Lubricant......................................................................................................................................................... 28
2.1.9 Coolant ........................................................................................................................................................... 28
2.1.10 Propellers........................................................................................................................................................ 28
2.1.11 Fuel ................................................................................................................................................................. 28
2.1.12 Approved Fuel ................................................................................................................................................ 28
2.1.13 Powerplant Instrument Markings................................................................................................................... 29
2.1.14 Other Instrument Markings............................................................................................................................ 29
2.1.15 Weights........................................................................................................................................................... 29
2.1.16 Center of Gravity Limits.................................................................................................................................. 29
2.1.17 Approved Maneuvers ..................................................................................................................................... 29
2.1.18 Maneuvering Load Factor Limits .................................................................................................................... 30
2.1.19 Flight Crew...................................................................................................................................................... 30
2.1.20 Kinds of Operations ........................................................................................................................................ 30
2.1.21 Day VFR........................................................................................................................................................... 31
2.1.22 Night ............................................................................................................................................................... 31
2.1.23 IFR................................................................................................................................................................... 31
2.1.24 Demonstrated Crosswind Safe Operations .................................................................................................... 31
2.1.25 Service Ceiling................................................................................................................................................. 31
2.1.26 Limitation Placards ......................................................................................................................................... 31
SECTION 3 WEIGHT & BALANCE ......................................................................................................................................32
3Introduction ............................................................................................................................................................32
3.1 Aircraft weighing procedures ................................................................................................................................. 32
3.1.1 Preparation..................................................................................................................................................... 32
3.1.2 Calculate empty weight Weighing.................................................................................................................. 32
3.1.3 Determination of C.G. location....................................................................................................................... 32
3.2 Weighing report ..................................................................................................................................................... 33
3.2.1 Center of Gravity Limits.................................................................................................................................. 33
3.2.2 Distances from the datum.............................................................................................................................. 33
3.3 Weight and Balance ............................................................................................................................................... 35
3.3.1 Loading ........................................................................................................................................................... 36

6
SECTION 4 PERFORMANCE ..............................................................................................................................................37
4Introduction ............................................................................................................................................................37
4.1 Use of Performance Charts..................................................................................................................................... 37
4.2 Airspeed Indicator System Calibration.................................................................................................................... 38
4.3 ICAO Chart .............................................................................................................................................................. 39
4.4 Stall Speeds............................................................................................................................................................. 40
4.5 Crosswind ............................................................................................................................................................... 41
4.6 Takeoff Performance .............................................................................................................................................. 42
4.7 Landing Distance .................................................................................................................................................... 43
4.8 Climb Performance ................................................................................................................................................. 44
4.9 Cruise ...................................................................................................................................................................... 45
4.10 Balked Landing ....................................................................................................................................................... 45
4.11 Effects of Rain and Insects...................................................................................................................................... 46
SECTION 5 EMERGENCY PROCEDURES.............................................................................................................................47
5Introduction ............................................................................................................................................................47
5.1 Engine Failures........................................................................................................................................................ 48
5.1.1 Engine Failures on Ground ............................................................................................................................. 48
5.1.2 Engine Failure during Flight ............................................................................................................................ 48
5.2 Smoke and Fire ....................................................................................................................................................... 49
5.2.1 Engine Fire while parked ................................................................................................................................ 49
5.2.2 Engine Fire during Takeoff.............................................................................................................................. 49
5.2.3 Engine Fire in-flight......................................................................................................................................... 49
5.2.4 Cabin Fire during Flight................................................................................................................................... 50
5.3 Landing Emergency ................................................................................................................................................ 50
5.4 Recovery from Unintentional Spin .......................................................................................................................... 51
5.5 Other Emergencies ................................................................................................................................................. 51
5.5.1 UNINTENTIONAL FLIGHT INTO ICING CONDITIONS........................................................................................ 51
5.5.2 Carburetor Ice................................................................................................................................................. 51
5.6 Electric Power System Malfunction ........................................................................................................................ 52
5.6.1 GENERATOR LIGHT ILLUMINATES................................................................................................................... 52
5.7 Trim System Failure ................................................................................................................................................ 52
5.7.1LOCKED CONTROL .......................................................................................................................................... 52
SECTION 6 NORMAL PROCEDURES ..................................................................................................................................53
6Introduction ............................................................................................................................................................53
6.1 Removing and Reinstalling the Engine Cowling...................................................................................................... 53
6.1.1 Upper Cowling ................................................................................................................................................ 53
6.1.2 Lower Cowling ................................................................................................................................................ 53
6.2 Checklist Procedures............................................................................................................................................... 54
6.2.1 Pre-Flight Inspection....................................................................................................................................... 54

7
SECTION 7 GROUND HANDLING & SERVICE.....................................................................................................................60
7Introduction ............................................................................................................................................................60
7.1 Aircraft Inspection Periods...................................................................................................................................... 60
7.2 Aircraft Alterations or Repairs................................................................................................................................ 60
7.3 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 ............................................................................................................................................... 60
7.3.6 Cleaning and Care........................................................................................................................................... 61
7.3.7Ground anchorage.......................................................................................................................................... 61
8Placards and Markings.............................................................................................................................................62
8.1.1 Magnetic compass compensation table......................................................................................................... 62
8.1.2 Engine throttle friction ................................................................................................................................... 62
8.1.3 Cabin heat....................................................................................................................................................... 62
8.1.4 Carburetor heat (If installed).......................................................................................................................... 62
8.1.5 Trim switch ..................................................................................................................................................... 63
8.1.6 Breakers.......................................................................................................................................................... 63
8.1.7 Flaps................................................................................................................................................................ 63
8.1.8 Generator, Master, Starter............................................................................................................................. 63
8.1.9 Choke.............................................................................................................................................................. 64
8.1.10 Generator light ............................................................................................................................................... 64
8.1.11 Fuel selector valve .......................................................................................................................................... 64
8.1.12 Baggage compartment ................................................................................................................................... 64
8.1.13 Oil tank reservoir ............................................................................................................................................ 65
8.1.14 Cooling system overflow tank ........................................................................................................................ 65
8.1.15 Brake oil reservoir .......................................................................................................................................... 65
8.1.16 Tire pressures ................................................................................................................................................. 65
8.1.17 Doors .............................................................................................................................................................. 65
8.1.18 Identification plate ......................................................................................................................................... 66
8.1.19 Static port ....................................................................................................................................................... 66
8.1.20 Fuel Tank ........................................................................................................................................................ 66
8.1.21 Limitation Placards ......................................................................................................................................... 66
9SUPPLEMENT LIST....................................................................................................................................................68
9.1 Introduction ............................................................................................................................................................ 68
9.2 Supplements list...................................................................................................................................................... 68
WARNINGS - CAUTIONS - NOTES
The following definitions apply to warnings, cautions and notes used in the Flight Manual.
WARNING
Means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight
safety
CAUTION
Means that the non-observation of the corresponding procedure leads to a minor or to a more or less long-term degradation
of the flight safety
NOTE
Draws the attention to any special item not directly related to safety but which is important or unusual.

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.
VA
Design maneuvering speed
VC
Design cruising speed
V
FE
Maximum Flap Extended Speed is the highest speed permissible with
wing flaps in a prescribed extended position.
VH
Max Speed in level flight with Max continuous power
V
LO
Lift off speed: is the speed at which the aircraft generally lifts off from the
ground.
V
NE
Never Exceed Speed is the speed limit that may not be exceeded at any
time.
V
NO
Maximum Structural Cruising Speed is the speed that should not be
exceeded except in smooth air, then only with caution.
VS
Stalling Speed or minimum steady flight speed flaps retracted
VS0
Stalling speed or minimum steady flight speed in landing configuration
VS1
Stalling speed in clean configuration (flap 0°)
V
X
Best Angle-of-Climb Speed is the speed, which results in the greatest gain
of altitude in a given horizontal distance.
V
Y
Best Rate-of-Climb Speed is the speed, which results in the greatest gain
in altitude in a given time.
V
R
Rotation speed: is the speed at which the aircraft rotates about the pitch
axis during takeoff.
Meteorology Terminology
OAT
Outside Air Temperature is the free air static temperature expressed in
degrees Celsius (°C).
T
S
Standard Temperature is 15°C (59°F) at sea level pressure altitude and
decreased by 2°C for each 1000 ft of altitude.
H
P
Pressure Altitude is the altitude read from an altimeter when the
barometric subscale has been set to 29.92”
Engine Power Terminology
RPM
Revolutions Per Minute: is the number of revolutions per minute of the
propeller, multiplied by 2.4286 yields engine RPM.

9
Airplane Performance and Flight Planning Terminology
Crosswind
Velocity
is the velocity of the crosswind component for which adequate control of the airplane
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
g
is the acceleration of gravity
TOR
is the takeoff distance measured from actual start to wheel lift off point
TOD
is total takeoff distance measured from start to clearing a 50’ obstacle
GR
is the distance measured during landing from actual touchdown to stop point
LD
is the distance measured during landing, from clearing a 50’ obstacle to actual stop
S/R
is specific range, that is, the distance (in nautical miles) which can be expected at a
specific power setting and/or flight configuration per gallon of fuel used
Weight and Balance Terminology
Datum
“Reference datum” is an imaginary vertical plane from which all horizontal
distances are measured for balance purposes
Arm
is the horizontal distance from the reference datum to the center of gravity
(C.G.) of an item
Moment
is the product of the weight of an item multiplied by its arm
C.G.
Center of Gravity is the point at which the airplane, or equipment, would
balance if suspended. Its distance from the reference datum is found by
dividing the total moment by the total weight of the airplane
Empty Weight
Empty Weight is the weight of the airplane with engine fluids and oil at
operating levels
Useful Load
is the difference between takeoff weight and the empty weight
Maximum Takeoff Weight
is the maximum weight approved for the start of the takeoff run
Maximum Landing Weight
is the maximum weight approved for the landing touch down
Tare
is the weight of chocks, blocks, stands, etc. used when weighing an airplane,
and is included in the scale readings; tare is then deducted from the scale
reading to obtain the actual (net) airplane weight

10
Unit Conversion Chart
Multiplying
by

Yields
Temperature
Fahrenheit
[°F]
( )
5
932⋅ −F
Celsius
[°C]
Celsius
[°C]
9
532⋅




+C
Fahrenheit
[°F]
Forces
Kilograms
[kg]
2.205
Pounds
[lbs]
Pounds
[lbs]
0.4536
Kilograms
[kg]
Speed
Meters per second
[m/s]
196.86
Feet per minute
[ft/min]
Feet per minute
[ft/min]
0.00508
Meters per second.
[m/s]
Knots
[kts]
1.853
Kilometers / hour
[km/h]
Kilometers / hour
[km/h]
0.5396
Knots
[kts]
Pressure
Atmosphere
[atm]
14.7
Pounds / sq. in
[psi]
Pounds / sq. in
[psi]
0.068
Atmosphere
[atm]
Length
Kilometers
[km]
0.5396
Nautical miles
[nm]
Nautical miles
[nm]
1.853
Kilometers
[km]
Meters
[m]
3.281
Feet
[ft]
Feet
[ft]
0.3048
Meters
[m]
Centimeters
[cm]
0.3937
Inches
[in]
Inches
[in]
2.540
Centimeters
[cm]
Volume
Liters
[l]
0.2642
U.S. Gallons
[US Gal]
U.S. Gallons
[US Gal]
3.785
Liters
[l]
Area
Square meters
[m2]
10.76
Square feet
[sq ft]
Square feet
[sq ft]
0.0929
Square meters
[m2]
Torque
foot-pounds
1.3558
Newton-meters
foot-pounds
0.1383
kilogram-meters
foot-pounds
12.0
inch-pounds
inch-pounds
0.0115
kilogram-meters
inch-pounds
0.1130
Newton-meters
inch-pounds
0.0833
foot-pounds
kilogram-meters
7.233
foot-pounds
kilogram-meters
86.7964
inch-pounds
kilogram-meters
9.8067
Newton-meters
Newton-meters
0.7376
foot-pounds
Newton-meters
8.8508
inch-pounds
Newton-meters
0.1020
kilogram-meter

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.
This aircraft is designed and built in Italy and as such, was built using the metric system. Therefore, the primary numbers
are in metric and the US conversion is in parenthesis for your information.
This Flight Manual has been prepared to ASTM standards to provide pilots and instructors with information for the safe
and efficient operation of this aircraft.
This Flight Manual contains the following sections:
1. General Information
2. Operating Limitations
3. Weight & Balance
4. Performance
5. Emergency Procedures
6. Normal Procedures
7. Aircraft Ground Handling and Servicing
8. Required Placards and Markings
1.2 Certification Basis
This aircraft is certificated as a Special Light Sport Aircraft under FAR part 21.190 and complies with all applicable ASTM
standards.

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
•Dimensions shown refer to aircraft weight of 600 kg (1320 lbs) and normal operating tire pressure

13
1.3 Descriptive Data
1.3.1 Airframe
1.3.1.1 Wing
Wing Span
9.00 m (29.5 ft)
Wing Area
12.16 m2(130.9 ft2)
Aspect Ratio
6.7
Taper Ratio
0.8
Wing chord
1.373 m (4.5 ft)
1.3.1.2 Fuselage
Overall length
6.93 m (22.7 ft)
Overall width
1.20 m (3.9 ft)
Overall height
2.46 m (8.07 ft)
1.3.1.3 Empennage
Stabilator span
2.90 m (9.51 ft)
Stabilator area
2.03 m2(21.8 ft2)
Vertical tail area
1.06 m2(11.4 ft2)
1.3.1.4 Landing Gear
Wheel track
1.8 m (5.9 ft)
Wheel base
1.94 m (6.4 ft) -1.74 m (5.7 ft steerable nose landing gear)
Main gear tire
Air Trac 5.00-5
Nose Gear tire
Sava 4.00-6
Wheel brakes
Marc Ingegno 199-102
1.4 Powerplant
1.4.1 Engine
Manufacturer
Model
Certification basis
Type
Bombardier-RotaxGmbH
912 ULS
ASTM F2339-06
4stroke carburetorengine
73.5 kW (98.5 hp) @ 5800 rpm(max. 5 minutes)
Maximumpower
69.0 kW (92.5 hp) @ 5500 rpm(cont.)
1.4.2 Allowed Propellers
Manufacturer
Model
Numberof blades
Diameter
Type
GT Tonini
GT-2/173/VRR- FW101
2
1730mm(68”)(no reduction permitted)
Fixed pitch – wood / composite
Manufacturer
Model
Numberofblades
Diameter
Type
Spacer
Sensenich
2A0R5R70EN
2
1778mm(70”)(no reduction permitted)
Fixed -ground adjustable pitch
B-1805-81 TECNAM Spacer

14
Manufacturer
Model
Number of blades
Diameter
Type
Spacer
Sensenich
3B0R5R68C
3
1730 (68'') (no reductionpermitted)
Fixed - ground adjustable pitch
B-1805-81 TECNAM Spacer
1.4.3 Oil System
Oil system
Oil
Oil Capacity
Forced, with external oil reservoir
See Rotaxoperator’s manual
Max. 3.0 liters (3.2 qt) – min. 2.0 liters (2.1 qt)
1.4.4 Cooling
Cooling system:
Coolant:
Capacity
3.0 liters (3.17 quarts)
Combination airand liquid cooled system
See Rotaxoperator’s manual
1.4.5 Fuel
Fuel grade:
Auto fuel
Avgas
Fuel tanks
Capacity of each
Total capacity
Min. RON 95 (AKI 91 PremiumUSA)
100LL
2integralwing tanks
52 liters (13.7 gal)
104 liters (27.5 gal)
1.5 Weights
1.5.1 Maximum Weights
Maximumtake-off
600 kg (1320 lb )
Maximumlanding
600 kg (1320 lb )
Maximumbaggage
20 kg (44 lb )
1.5.2 Standard Weights
Empty weight 355 kg (783 lb )
Maximumpayload
245 kg (540 lb )
1.5.3 Specific Loadings
Wing loading
59 kg/m2 (12 lb/ft2)
Power loading
6.1 kg/hp (13.5 lb/hp)
NOTE
Standard weights are estimates based on standard equipment.

15
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
Dual Stick Flight Controls and Rudder Pedals, Single Throttle, Throttle Friction Control, Engine Choke, Electric
Flaps, Hydraulic Disc Brakes with Parking Brake and toe brakes on both seats, Left and Right Fuel Selector Valve,
Direct Nose Wheel Steering (or pivoting NLG with differential breaking system)
1.6.5 Interior
Adjustable Pilot and Copilot Seats, reclining for baggages compartement access, Acoustic Cabin Soundproofing,
Adjustable Cabin Air Intakes, Cabin Heat and Windshield Defrost, 12V Power Outlet, Composite Instrument
Panel
1.6.6 Exterior
Composite structure, Landing Light, Strobe Light, Fixed Landing Gear, Nose Gear Strut Fairing, Nose and Main
Wheel Fairings
1.6.7 Powerplant and Accessories
Rotax 912 ULS Engine (100 hp), Composite Covered Wood / Composite Propeller with Spinner , 12Volt 18 Ah
Battery, 18 Amp Alternator, Engine Driven Fuel Pump, Electric Starter, Engine Exhaust Muffler, Gascolator with
Quick Drain, Integral Wing Fuel Tanks with sump and quick drain, Integral INOX hoses and AN Fittings for fuel
line, All Electric Circuits Fuse Protected

16
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. The aileron is constructed of an aluminum spar to which a formed
sheet metal leading edge and metal ribs are attached; a wrap-around. Aluminium material covers aileron structure.
The wing box incorporates the integral fuel tanks of 52liters each.
1.7.2 Fuselage
The fuselage and the vertical stabilizer are made up of a composite fiber structure. The engine housing is isolated from the
cabin by a stainless steel firewall (0.5mm thick); the steel engine mount is attached to the cabin's composite structure.
NOTE: See the AMM for the lamination schemes and repair procedures.
1.7.3 Empennage
The vertical tail is made up of a mixed structure: the vertical stabilizer is made up of composite fiber while the rudder
consists of an aluminum torque stringer connected to light alloy ribs and skin. The horizontal tail is an all-moving type
(stabilator); its structure consists of an aluminum spar connected to ribs and leading edge; the entire structure is covered
with aluminum material.
1.7.4 Flight controls
The control surfaces are manually operated using a control stick for ailerons and stabilator and rudder pedals for the rudder;
longitudinal control acts through a system of push-rods and is equipped with a trim tab. Aileron control is of mixed type
with push-rods and cables; the cable control circuit is confined within the cabin and is connected to a pair of push-rods
positioned in the wings that control ailerons differentially. Aileron trimming is carried out on ground through a small tab
positioned on left aileron.
Flaps are extended via an electric servo actuator controlled by a switch on the panel. Flaps act in a continuous mode; a
panel mounted indicator shows surface position. A fuse positioned on the right side of the panel protects the electric circuit.
Longitudinal trim is performed by a small tab positioned on the stabilator and controlled via an electric servo actuator by
pushing an Up/Down push-button located on the control stick.

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1.7.5 Instrument Panel
The instrument panel is of conventional type, allowing space for a broad range of equipment.
Fig. 1-2 Instrument Panel
1.7.6 Carburetor Heat
Carburetor heat (if available) control knob is located just to the right of the center throttle control. When the knob is pulled
fully outward from the instrument panel, carburetors receive maximum hot air. During normal operation, the knob is OFF.
1.7.7 Cabin Heat / Defrost
The cabin heat control knob (if available) is positioned on the lower of the instrument panel; when knob is pulled fully
outward, cabin receives maximum hot air. Vents are located by the rudder pedals and above instrument panel. If necessary,
outside fresh air can be circulated inside cabin by opening the vents on the panel.
1.7.8 Throttle Friction Lock
Adjust the engine's throttle friction by tightening or loosening the friction lock located on the console side near center
throttle control.
1.7.9 Seats, Seatbelts, and Shoulder harnesses
The P2008usually comes with three point safety belts with waist and diagonal straps adjustable via a sliding metal buckle.
Standard seats are aluminum with cushions. Seats are adjustable fore and aft by using the handle located under the seat on
the outboard sides. Pushing the lever towards the center of the aircraft will release the locking pin allowing you to move the
seat fore and aft. 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.
WARNING
Make sure that the locking pin is securely installed or the seat will not lock in position.

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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. Baggage shall be uniformly distributed and its weight shall not
exceed 20 kg (44 lbs) and the c.g. must be computed before flight. Always tie down the baggage by using the adjustable tie-
down net provided.

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1.8 Powerplant
1.8.1 Engine
Rotax is an Austrian engine manufacturer, founded in 1920 inDresden, Germany. In 1970 Bombardier bought Rotax. The
company constructed only two-stroke engines until 1982, when it started building four-stroke engines. In 1989, Rotax
received Type Certification for its 912 A aircraft engine.
The Rotax 912 ULS engine is an ASTM compliant engine. The 912 is a four stroke, horizontally opposed, spark ignition
engine with single central camshaft with hydraulic tappets. The 912 has liquid cooled cylinder heads and ram air cooled
cylinders and engine. It is rated at 5800 RPM and can be run continuously at 5500 RPM.
The oil system is a dry sump, forced lubrications system. The oil tank is located on the passenger side of the engine
compartment and holds 3 liters (3.2 quarts) of oil.
The dual ignition system is a solid state, breakerless, capacitive discharge, interference suppression system instead of a
mechanical magneto system. Each ignition system is powered by individual and totally independent AC generators which
are not dependent on the aircraft battery.
The electrical system consists of an integrated AC generator with an external rectifier – regulator. An external alternator
can be installed. The Rotax engine is equipped with an electric starter.
The dual carburetors are constant depression carburetors that automatically adjust for altitude.
The fuel system is equipped with an engine driven mechanical pump and electrical back up FACET pump.
The cooling system is a mixture of liquid and air cooling.
The engine uses a reduction gearbox with a gear reduction ratio of 2.4286:1.
A central console located throttle in the cockpit controls the engine.
The owner can register and get important information from the following website: http://www.rotax-owner.com/.
1.8.2 Propeller
The GT propeller is a wood composite propeller built by GT Tonini in Italy. The Tonini brothers began building propellers
in 1969.
The propeller is finished with a white polyurethane lacquer and an additional layer of transparent lacquer. The tips are
painted in bright yellow and red so that when the propeller is turning it is obvious to personnel on the ground. The back of
the propeller is painted black to prevent reflections. More information on the company and the propeller can be found at
http://www.gt-propellers.com. Check with your dealer for propeller options.
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. More information on the company and the propeller can be found at
http://www.sensenich.com/.
1.8.3 Fuel system
The system is equipped with two aluminum fuel tanks integrated in the wing box and accessible for inspection through two
dedicated covers. Capacity of individual tank is 52lt (13.7 gal) and total usable fuel is 104lt (27.4 gal). Each fuel tank is
equipped with a cabin installed shutoff and selector Andair valve. A strainer cup with a drainage valve (Gascolator) is
located on the engine side of the firewall. Fuel level indicators for each tank are located on instrument panel. Fuel feed is
through an engine-driven mechanical pump. All fuel lines located in the engine compartment are protected with fireproof
braiding to avoid possible fire. Figure 1-3 illustrates the schematic of the fuel system. All lines in the fuselage are made in
steel hoses to prevent leaks and damages. Fittings are AN type.
WARNING
Fuel quantity should be checked on a level surface or a false reading may result. Always visually verify fuel quantity by
looking inside the tanks during filling.

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Figure 1-3 Fuel System
LH FUEL QUANTITY SENSOR
LH FUEL QUANTITY INDICATOR
FIREWALL
FUEL VENT
M
FILTER
MECHANICAL FUEL PUMP
Rh
MESH FILTER + TANK DRAIN
Off
ELECTRIC FUEL PUMP
SUMP
Lh
LH FUEL TANK
ELECTRICAL LINE
SUMP
FUEL PRESSURE INDICATOR
FUEL PRESSURE SENDER
RH FUEL TANK
RH FUEL QUANTITY INDICATOR
RH FUEL QUANTITY SENSOR
ELECTRICAL LINE
FUEL
VENT
TO LH CARBURATOR
ELECTRIC LINE
TO RH CARBURATOR
RETURN LINE TO FUEL PRESSURE SENDER