Tecnam P2002-JF Technical specifications

FLIGHT MANUAL
P2002-JF
Introduction
1
st
Edition – 29th March 2004 i-1
FLIGHT MANUAL
Doc. n° 2002/28
1st edition, March 29th 2004
1st revision, August 3rd 2005
P2002-JF
MANUFACTURER: COSTRUZIONI AERONAUTICHE TECNAM S.r.l.
AIRCRAFT MODEL: P2002-JF
EASA TYPE CERTIFICATE NO.A.006
SERIAL NUMBER:………………………………………………………
BUILD YEAR: ………….……………………………………………….
REGISTRATION MARKINGS: ……..……………………………………..
This manual contains information to be furnished to the pilot as required by
EASA in addition to further information supplied by the manufacturer.
This manual must always present on board the aircraft
The aircraft is to be operated in compliance with information and
limitations contained herein.
Sections2, 3, 4, 5 and 9 (supp.1) are approved by EASA n°EASA.AC.01372
dated 3/8/2005

FLIGHT MANUAL
P2002-JF
Introduction
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RECORD of REVISIONS
Any revisions to the present Manual, except actual weighing data, must be
recorded in the following table and, in case of approved sections, endorsed
by the responsible airworthiness authority.
New or amended text in the revised pages will be indicated by a black
vertical line in the left-hand margin; Revision No. and date will be shown
on the left-hand side of the amended page.
LOG of REVISIONS
Rev n° Sect. Page Date EASA Approval Date Insert. date Sign.
1 0 1,2,3 3/8/05 - -
1 1 6 3/8/05 - -
1 2 4,6,11 3/8/05
EASA.AC.01372 3/8/05
1 4 5,9 3/8/05
EASA.AC.01372 3/8/05
1 5 6 3/8/05
EASA.AC.01372 3/8/05

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LIST OF EFFECTIVE PAGES
Sect. Page Date Sect. Page Date
0 i-1 3 August 2005 3-4 29 March 2004
i-2 “ 3-5 “
i-3 “ 3-6 “
i-4 29 March 2004 3-7 “
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i-6 “ 3-9 “
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1-3 “ 4 4-1 29 March 2004
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1-7 29 March 2004 4-5 3 August 2005
1-8 “ 4-6 29 March 2004
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1-10 “ 4-8 “
1-11 “ 4-9 3 August 2005
1-12 “ 4-10 29 March 2004
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2-3 “ 5 5-1 29 March 2004
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2-6 3 August 2005 5-4 “
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2-8 “ 5-6 3 August 2005
2-9 “ 5-7 29 March 2004
2-10 “ 5-8 “
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2-12 29 March 2004 5-10 “
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3-2 “ 5-13 “
3-3 “ 5-14 “

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Sect. Page Date Sect. Page Date
6 6-1 29 March 2004 9 9-1 29 March 2004
6-2 “ 9-2 “
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P2002-JF
Introduction
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TABLE OF CONTENTS
General Section 1
Limitations Section 2*
Emergency Procedures Section 3*
Normal Procedures Section 4*
Performances Section 5**
Weight & Balance / Equipment List Section 6
Systems Section 7
Ground Handling, Servicing and
Maintenance
Section 8
Supplements Section 9*
* Section approved by EASA
** Section partially approved by EASA

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P2002-JF
Introduction
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FLIGHT MANUAL
P2002-JF
SECTION 1
General
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SECTION 1
GENERAL
TABLE OF CONTENTS
INTRODUCTION ........................................................................................ 2
CERTIFICATION BASIS ............................................................................ 2
WARNINGS -CAUTIONS -NOTES.......................................................... 2
THREE-VIEW DRAWING.......................................................................... 3
DESCRIPTIVE DATA................................................................................. 4
CONTROL SURFACES TRAVEL LIMITS................................................ 4
ENGINE ....................................................................................................... 5
PROPELLER................................................................................................ 5
FUEL ............................................................................................................ 6
OIL SYSTEM............................................................................................... 6
COOLING .................................................................................................... 6
MAXIMUM WEIGHTS............................................................................... 7
STANDARD WEIGHTS.............................................................................. 7
SPECIFIC LOADINGS................................................................................ 7
ABBREVIATIONS AND TERMINOLOGY............................................... 8
UNIT CONVERSION CHART.................................................................. 11

FLIGHT MANUAL
P2002-JF
SECTION 1
General
1
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Edition – 29th March 2004 1-2
INTRODUCTION
The P2002-JF is a twin seat, single engine aircraft with a tapered,
low wing. fixed main landing gear and steerable nosewheel.
This Flight Manual has been prepared to provide pilots and
instructors with information for the safe and efficient operation of
this very light aeroplane.
This manual includes the material required to be furnished to the
pilot of CS-VLA. It also contains supplemental data supplied by
aeroplane manufacturer.
CERTIFICATION BASIS
This type of aircraft has been approved by the European Safety
Aviation Agency in accordance with CS-VLA of 14 November
2003, and the Type Certificate No. A.006 issued on 27th May 2004.
Category of Airworthiness: Normal
Noise Certification Basis: EASA CS-36 1stedition dated 17th October
2003, with reference to ICAO/Annex 16 3rdedition dated 1993, Vol.1
Chapter 10.
WARNINGS - CAUTIONS - NOTES
The following definitions apply to warnings, cautions and notes
used in the Flight Manual.
Means that the non-observation of the
corresponding procedure leads to an
immediate or important degradation of the
flight safety.
Means that the non-observation of the
corresponding procedure leads to a minor or to
a more or less long term degradation of the
flight safety.
Draws the attention to any special item not
directly related to safety but which is important
or unusual.
WARNING
CAUTION
NOTE

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General
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THREE-VIEW DRAWING
•Dimensions shown refer to aircraft weight of 580 kg and
normal operating tire pressure.
•Propeller ground clearance 320mm
•Propeller ground clearance with deflated front tire and
nosewheel shock absorber compressed by 102mm
•Minimum ground steering radius 5.5m
NOTE
8.6 m
6.61 m
2.43 m

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SECTION 1
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DESCRIPTIVE DATA
WING
Wing span: 8.6 m
Wing surface 11.5 m2
Wing loading 50.4 kg/m2
Aspect ratio 6.4
Taper ratio 0.6
Dihedral 5°
FUSELAGE
Overall length 6.61 m
Overall width 1.11 m
Overall height 2.43 m
EMPENNAGE
Stabilator span 2.90 m
Vertical tail span 1.10 m
LANDING GEAR
Wheel track: 1.85 m
Wheel base: 1.62 m
Main gear tires: Air Trac 5.00-5
Wheel hub and brakes: Cleveland 199-102
Nose gear tire: Sava 4.00-6
CONTROL SURFACES TRAVEL LIMITS
Ailerons Up 20° down 15 ° ±2°
Stabilator Up 15° down 3° ±1°
Trim-Tab 2° ; 9° ±1°
Rudder RH 30° LH 30° ±2°
Flaps 0°; 40° ±1°

FLIGHT MANUAL
P2002-JF
SECTION 1
General
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Edition – 29th March 2004 1-5
ENGINE
Manufacturer: Bombardier-Rotax GmbH
Model 912 S2
Certification basis FAR 33 Amendment 15
Austrian T.C. No. TW 9-ACG dated 27th November
1998
Type: 4 cylinder horizontally-opposed twins
with overall displacement of 1352
c.c., mixed cooling, (water-cooled
heads and air-cooled cylinders), twin
carburettors, integrated reduction
gear with torque damper.
Maximum power: 73.5 kW (98.5 hp) @ 5800 rpm (max. 5’)
69.0 kW (92.5 hp) @ 5500 rpm (cont.)
PROPELLER
Manufacturer: Hoffmann Propeller
Certification Basis CAR Part 14
Type Certificate No. SO/E 30 dated 10 December 1999
Model: HO17GHM A 174 177 C
Number of blades: 2
Diameter: 1740 mm (no reduction permitted)
Type: Fixed pitch – wood

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P2002-JF
SECTION 1
General
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FUEL
Fuel grade: •Min. RON 95
•EN 228 Premium
•EN 228 Premium plus
•AVGAS 100LL (see Section 2 page 11)
Fuel tanks: 2 wing tanks integrated within the
wing’s leading edge. Equipped with
finger strainers outlet and with drain
fittings.
Capacity of each wing tank 50 liters
Total capacity: 100 liters
Total usable fuel 99 litres
OIL SYSTEM
Oil system type: Forced, with external oil reservoir
Oil: Lubricant specifications and grade
are detailed into the “Rotax
Operator’s Manual” and in its related
documents.
Oil Capacity: Max. 3.0 litres – min. 2.0 liters
COOLING
Cooling system: Mixed air and liquid pressurized closed circuit
system
Coolant: Coolant type and specifications are detailed into
the “Rotax Operator’s Manual” and in its related
documents.
1s
t
revision, August 3r
d
2005

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P2002-JF
SECTION 1
General
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MAXIMUM WEIGHTS
Maximum take-off weight: 580 kg
Maximum landing weight: 580 kg
Maximum baggage weight 20 kg
STANDARD WEIGHTS
Standard Empty Weight 337 kg
Maximum useful load 243 kg
SPECIFIC LOADINGS
Wing Loading 50.4 kg/m2
Power Loading 5.9 kg/hp

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ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
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.
VFE Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended position.
VNO Maximum Structural Cruising Speed is the speed that should
not be exceeded except in smooth air, then only with caution.
VNE Never Exceed Speed is the speed limit that may not be
exceeded at any time.
VSStalling Speed.
VS0 Stalling speed in landing configuration
VS1 Stalling speed in clean configuration (flap 0°)
VXBest Angle-of-Climb Speed is the speed which results in the
greatest gain of altitude in a given horizontal distance.
VYBest Rate-of-Climb Speed is the speed which results in the
greatest gain in altitude in a given time.
Vr Rotation speed: is the speed at which the aircraft rotates about
the pitch axis during takeoff
VLO Lift off speed: is the speed at which the aircraft generally lifts
off from the ground.
Vobs Obstacle speed: is the speed at which the aircraft flies over a
15m obstacle during takeoff or landing

FLIGHT MANUAL
P2002-JF
SECTION 1
General
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Edition – 29th March 2004 1-9
METEOROLOGICAL TERMINOLOGY
OAT Outside Air Temperature is the free air static temperature
expressed in degrees Celsius (°C).
TSStandard Temperature is 15°C at sea level pressure altitude
and decreased by 2°C for each 1000 ft of altitude.
HPPressure Altitude is the altitude read from an altimeter when
the barometric subscale has been set to 1013 mb.
ENGINE POWER TERMINOLOGY
RPM Revolutions Per Minute: is the number of revolutions per
minute of the propeller, multiplied by 2.4286 yields engine
RPM.
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
liftoff point
TOD is total takeoff distance measured from start to 15m obstacle
clearing
GR is the distance measured during landing from actual
touchdown to stop point
LD is the distance measured during landing, from 15m obstacle
clearing to actual stop.
S/R is specific range, that is, the distance (in nautical miles)
which can be expected at a specific power setting and/or
flight configuration per kilo of fuel used.

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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 aeroplane with engine
fluids and oil at operating levels.
Useful Load is the difference between takeoff weight and the basic
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 deducted from the scale reading to obtain the actual
(net) airplane weight.

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UNIT CONVERSION CHART
MULTIPLYING BY Î YIELDS
TEMPERATURE
Fahrenheit [°F]
()
5
932⋅−FCelsius [°C]
Celsius [°C]
9
532⋅





+CFahrenheit [°F]
FORCES
Kilograms [kg]
2.205 Pounds [lbs]
Pounds [lbs]
0.4536 Kilograms [kg]
SPEED
Meters per second [m/s] 196.86 Feet per minute [ft/min]
Feet per minute [ft/min] 0.00508 Meters per second. [m/s]
Knots [kts]
1.853 Kilometres / hour [km/h]
Kilometres / hour [km/h] 0.5396 Knots [kts]
PRESSURE
Atmosphere [atm]
14.7 Pounds / sq. in [psi]
Pounds / sq. in [psi] 0.068 Atmosphere [atm]
LENGTH
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]

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FLIGHT MANUAL
P2002-JF
SECTION 2
L imitations
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SECTION 2
LIMITATIONS
TABLE OF CONTENTS
INTRODUCTION....................................................................................................2
AIRSPEED LIMITATIONS ....................................................................................2
AIRSPEED INDICATOR MARKINGS..................................................................3
POWERPLANT LIMITATIONS ............................................................................4
LUBRICANT........................................................................................................... 5
COOLANT............................................................................................................... 6
PROPELLER ...........................................................................................................6
POWERPLANT INSTRUMENT MARKINGS ......................................................7
OTHER INSTRUMENT MARKINGS.................................................................... 7
WEIGHTS................................................................................................................ 8
CENTER OF GRAVITY RANGE........................................................................... 8
APPROVED MANEUVERS ...................................................................................9
MANEUVERING LOAD FACTOR LIMITS ......................................................... 9
FLIGHT CREW ..................................................................................................... 10
KINDS OF OPERATION......................................................................................10
FUEL...................................................................................................................... 11
MAXIMUM PASSENGER SEATING .................................................................11
DEMONSTRATED CROSS WIND SAFE OPERATIONS .................................11
LIMITATION PLACARDS...................................................................................12

FLIGHT MANUAL
P2002-JF
SECTION 2
L imitations
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INTRODUCTION
Section 2 includes operating limitations, instrument markings, and basic
placards necessary for safe operation of the P2002-JF, its engine and
standard systems and equipment.
AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown below:
SPEED KIAS KCAS REMARKS
VNE Never exceed speed 138 135 Never exceed this speed in any
operation.
VNO Maximum Structural
Cruising Speed 110 106 Never exceed this speed unless in
smooth air, and then only with
caution.
VAManoeuvring speed 96 94 Do not make full or abrupt control
movements above this speed as this
may cause stress in excess of limit
load factor
VFE Maximum flap
extended speed 67 69 Never exceed this speed for any
flap setting.