Tecnam P2006T Technical specifications

1st Edition, Rev. 0 – 2009, May 25th
Page 0 - 1
Aircraft Flight Manual
Doc. No. 2006/044[EV]
1st Edition – 2009, May 25th
Rev. 0
TECNAM P2006T
MANUFACTURER: COSTRUZIONI AERONAUTICHE TECNAM S.r.l.
AIRCRAFT MODEL: P2006T
EASA TYPE CERTIFICATE NO:A.185 (DATED 2009, JUIN 5TH)
SERIAL NUMBER:………………………………………………………
BUILD YEAR:………….……………………………………………….
REGISTRATION MARKINGS:……..……………………………………..
THIS DOCUMENT IS THE ENGLISH TRANSLATION OF
P2006T AIRCRAFT FLIGHT MANUAL –DOC.NO.2006/044,
WRITTEN IN ITALIAN AND APPROVED BY EASA ON 25 MAY 2009
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 has to be operated in compliance with procedures and limitations
contained herein.
Costruzioni Aeronautiche TECNAM srl
Via Maiorise
CAPUA (CE) – Italy
Tel. [phone]
WEB: www.tecnam.com

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1st Edition, Rev. 0 - 2009, May 25th
Aircraft Flight Manual
INDEX
INDEX
01. Record of Revisions...................................................................................... 3
02. List of Effective Pages.................................................................................. 5
03. Foreword....................................................................................................... 7
04. Sections Index.............................................................................................. 8

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1st Edition, Rev. 0 - 2009, May 25th
Aircraft Flight Manual
RECORD OF REVISIONS
01. RECORD OF REVISIONS
Any revision to the present Manual, except actual weighing data, is 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; Revision No. and date will be shown on the right-hand
side of the amended page.
Revisions will be distributed whenever necessary as complete page replacements
or additions and shall be inserted into the manual in accordance with the instruc-
tions given below:
a. Revision pages will replace only pages with the same page number.
b. Insert all additional pages in proper numerical order within each section.
NOTE: It is the responsibility of the owner to maintain this handbook in a current
status when it is being used for operational purposes.
Rev.
Sec.
Page
Date
Tecnam Approval
EASA Approval Or
Under DOA
Privileges
Date
D.O.
OofA
HDO

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Aircraft Flight Manual
RECORD OF REVISIONS
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1st Edition, Rev. 0 - 2009, May 25th
Aircraft Flight Manual
LIST OF EFFECTIVE PAGES
02. LIST OF EFFECTIVE PAGES
Section Pages Rev. Date
Section 0 Page 1 to 8 Rev 0 May 25 2009
Section 1 Page 1 to 12 Rev 0 May 25 2009
Section 2 Page 1 to 16 Rev 0 May 25 2009
Section 3 Page 1 to 28 Rev 0 May 25 2009
Section 4 Page 1 to 14 Rev 0 May 25 2009
Section 5 Page 1 to 16 Rev 0 May 25 2009
Section 6 Page 1 to 14 Rev 0 May 25 2009
Section 7 Page 1 to 18 Rev 0 May 25 2009
Section 8 Page 1 to 6 Rev 0 May 25 2009
Section 9 Page 1 to 18 Rev 0 May 25 2009

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Aircraft Flight Manual
LIST OF EFFECTIVE PAGES
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1st Edition, Rev. 0 - 2009, May 25th
Aircraft Flight Manual
FOREWORD
03. FOREWORD
Tecnam P2006T is a twin-engine four-seat aircraft with high cantilevered wing and tri-
cycle retractable landing gear.
Section 1 supplies general information and it contains definitions, symbols explanations,
acronyms and terminology used.
Before using the aircraft, you are recommended to read carefully this manual: a deep
knowledge of aircraft features and limitations will allow you for operating the aircraft
safely.
For further information, please contact:
COSTRUZIONI AERONAUTICHE TECNAM s.r.l.
Via MAIORISE
CAPUA (CE) - ITALY
+39 (0) 823.62.01.34 www.tecnam.com

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1st Edition, Rev. 0 - 2009, May 25th
Aircraft Flight Manual
SECTIONS INDEX
04. SECTIONS INDEX
General Section 1
Limitations Section 2
Emergency Procedures Section 3
Normal Procedures Section 4
Performances Section 5
Weight and Balance Section 6
Airframe and Systems description Section 7
Aircraft Care and Maintenance Section 8
Supplements Section 9

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Section 1 – General
1st Edition – 2009, May 25th
SECTION 1 - GENERAL
INDEX
01. Introduction..................................................................................................... 2
02. Warning – Caution – Note ................................................................................ 2
03. Three-views Drawings..................................................................................... 3
04. Dimensions...................................................................................................... 4
05. Control Surfaces Travel Limits ....................................................................... 4
06. Engine ............................................................................................................. 5
07. Propeller.......................................................................................................... 5
08. Governor.......................................................................................................... 5
09. Fuel ................................................................................................................. 5
10. Lubrication ...................................................................................................... 6
11. Cooling ............................................................................................................ 6
12. Maximum weights ........................................................................................... 6
13. Standard weights ............................................................................................ 6
14. Specific loadings............................................................................................. 7
15. Acronyms and terminology.............................................................................. 7
16. Unit conversion chart.................................................................................... 10
17. Liters / US gallons conversion chart ............................................................. 11

Section 1 – General
ACRONYMS AND TERMINOLOGY
Page 1 - 2
1st Edition – 2009, May 25th
01. INTRODUCTION
The Aircraft Flight Manual has been implemented to provide the owners with in-
formation for a safe and efficient use of the aircraft TECNAM P2006T.
02. WARNING –CAUTION –NOTE
Following definitions apply to warnings, cautions and notes used in the Aircraft
Flight Manual.
The non-observation of the corresponding procedure can lead, as
immediate effect, to a significant reduction of the flight safety.
WARNING
The non-observation of the corresponding procedure can lead to
an equipment damage which leads to a reduction of the flight
safety in a short or longer time interval.
CAUTION
Draws the attention to a procedure not directly related to safety of
flight.
.
NOTE

Section 1 – General
ACRONYMS AND TERMINOLOGY
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1st Edition – 2009, May 25th
03. THREE-VIEWS DRAWINGS
Figure 1 – General views

Section 1 – General
ACRONYMS AND TERMINOLOGY
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1st Edition – 2009, May 25th
04. DIMENSIONS
Overall dimensions
Wingspan 11,4 m 37,4 ft
Length 8,7 m 28,5 ft
Overall height 2,85 m 9,35 ft
Wing
Wing surface 14,76 m2158,9 ft2
Mean Geometric Chord 1,295 m 4,25 ft
Dihedral 1°
Aspect ratio 8,80
Main Landing Gear
Track 2.0 m
Wheelbase 2.9 m
Tire (Air Trac) 6.00-6
Wheel rim assembly (Cleveland) P/N 40-59
05. CONTROL SURFACES TRAVEL LIMITS
Nose Landing Gear
Tire (Air Trac) 5.00 – 5
Wheel rim assembly (Cleveland) P/N 40-77A
Ailerons Up 20° Down 17 ° (±2°)
Stabilator Up 15° Down 4° (±2°)
Stabilator trim tab Up 8°; Down 22° (±2°)
Rudder RH 26° LH 26° (±2°)
Rudder trim tab RH 20° LH 210° (±2°)
Flaps 0°; 40° (- 2°)

Section 1 – General
ACRONYMS AND TERMINOLOGY
Page 1 - 5
1st Edition – 2009, May 25th
06. ENGINE
Manufacturer Bombardier-Rotax GmbH
Model 912 S3
Certification basis FAR 33 - Amendment 15
Type Certificate EASA TCDS no. E.121 dated 1 April
2008
Engine type 4 cylinders
horizontally opposed with
1352 c.c. of overall displacement, liquid
cooled cylinder heads, ram-air cooled cy-
linders, two carburetors, integrated re-
duction gear box with shock absorber.
Maximum power (at declared rpm)73.5 kW (98.6hp) @ 5800 rpm –5
minutes maximum.
69.0 kW (92.5hp) @ 5500 rpm (continu-
ous)
07. PROPELLER
Manufacturer MT Propeller
Type Certificate LBA 32.130/086 (MTV-21 series)
Model MTV-21-A-C-F/CF178-05
Blades/hub 2 wood/composite blades – aluminum
hub
Diameter 1780 mm (no reduction allowed)
Type Variable pitch - hydraulically controlled
08. GOVERNOR
Manufacturer Mt Propeller
Model P-875-12
Type Hydraulic
09. FUEL
Fuel type Min. RON 95
EN 228 Premium
EN 228 Premium plus
AVGAS 100LL (see Section.2)

Section 1 – General
ACRONYMS AND TERMINOLOGY
Page 1 - 6
1st Edition – 2009, May 25th
Fuel tanks Two integrated tanks (one in each
wing) fitted with drainable sump
and drain valve
Capacity of each wing tan 100 litres (26,42 US gallons))
Tanks overall capacity 200 litres (52,8 US gallons)
Overall usable fuel 194.4 litres (51,35 US gallons)
Overall unusable fuel 5.6 litres (1,48 US gallons)
10. LUBRICATION
Lubrication system Forced type with external reservoir
Oil Refer to “Rotax Operator’s Manual”
and related documents
Oil capacity Max. 3.0 litres – min. 2.0 litres (per
tank)
11. COOLING
Cooling system Ram-air cooled cylinders, liquid
cooled cylinder heads (closed and
pressurized circuit)
Coolant liquid Make reference to “Rotax Operator’s
Manual” and related documents
Overall circuit capacity 1410 cm3
12. MAXIMUM WEIGHTS
Maximum takeoff weight 1180 kg (2601 lb)
Maximum landing weight 1180 kg (2601 lb)
Maximum baggage weight 80 kg (176 lb)
13. STANDARD WEIGHTS
Standard Empty Weight 760 kg (1676 lb)
Maximum useful load 420 kg (926 lb)

Section 1 – General
ACRONYMS AND TERMINOLOGY
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1st Edition – 2009, May 25th
14. SPECIFIC LOADINGS
Wing Loading 80 kg/m2(16.4 lb/ft2)
Power Loading 6.02 kg/hp
15. ACRONYMS AND TERMINOLOGY
KCAS Calibrated Airspeed
KIAS
is the indicated airspeed expressed in knots,
corrected taking into account the errors related to the instrument
itself and its installation.
Indicated Airspeed
KTAS
is the speed shown on the airspeed indicator
and it is expressed in knots.
True Airspeed
VA
is the KCAS airspeed corrected taking into ac-
count altitude and temperature.
Manoeuvring speed
VFE
is the speed above the which it is not al-
lowed to make full or abrupt control movement.
Maximum Flap Extended speed
VLO
is the highest speed permissible
with flaps extended.
Maximum Landing gear Operating speed
VLE
is the maximum speed
allowed to retract or to extend the landing gear.
Maximum Landing gear Extended speed
VMC
is the maximum speed
allowed with the landing gear extended.
Minimum control speed
VNO
: is the minimum speed necessary to en-
sure an efficient aircraft control in case of one engine inopera-
tive.
Maximum Structural Cruising Speed
VNE
is the speed that should not
be exceeded, except in smooth air and only with caution.
Never Exceed Speed
VS
is the speed limit that may not be exceeded
at any time.
VS0
Stall Speed.
Stall Speed in landing configuration
VS1
(flaps and landing gear ex-
tended).
VX
Stalling speed in clean configuration (flaps 0°).
Best Angle-of-Climb Speed
VY
is the speed which results in the
greatest gain of altitude with respect to a given horizontal dis-
tance.
Best Rate-of-Climb Speed is the speed which results in the great-
est gain in altitude in a given time.

Section 1 – General
ACRONYMS AND TERMINOLOGY
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1st Edition – 2009, May 25th
VRRotation speed
VLOF
: is the speed at which the aircraft rotates about
the pitch axis during takeoff
Lift off speed:
Vobs
is the speed at which the aircraft generally lifts off
from the ground.
Obstacle speed:
VYSE
is the speed at which the aircraft flies over a 15m
obstacle during takeoff or landing.
Best Rate-of-Climb speed in case of one engine inoperative.
Meteorological terminology
ISA International Standard Atmosphere
QFE
: is the air atmospheric standard
condition at sea level, at 15°C (59°F) and at 1013.25hPa
(29.92inHg).
Official atmospheric pressure at airport level:
QNH
it indicates the air-
craft absolute altitude with respect to the official airport level.
Theoretical atmospheric pressure at sea level:
OAT
is the atmospheric
pressure reported at the medium sea level, through the standard air
pressure-altitude relationship, starting from the airport QFE.
Outside Air Temperature
TS
is the air static temperature expressed in
degrees Celsius (°C).
Standard Temperature
HP
is 15°C at sea level pressure altitude and
decreased by 2°C for each 1000 ft of altitude.
Pressure Altitude
Aircraft performance and flight planning terminology
is the altitude read from an altimeter when the
barometric subscale has been set to 1013 mb.
Crosswind Velocity is the velocity of the crosswind component
for the which adequate control of the air-
plane during takeoff and landing is assured.
Usable fuel is the fuel available for flight planning.
Unusable fuel is the quantity of fuel that cannot be safely
used in flight.
g is the acceleration of gravity.
TOR is the takeoff distance measured from actual
start to 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.

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Section 1 – General
ACRONYMS AND TERMINOLOGY
1st Edition – 2009, May 25th
LD is the distance measured during landing,
from 15m obstacle clearing to actual stop.
S/R is the specific range, that is the distance (in
nautical miles) which can be expected at a
specific power setting and/or flight configu-
ration per kilo of fuel used.
Weight and balance terminology
Datum “Reference datum” is an imaginary vertical
plane from which all horizontal distances are
measured for balance purposes.
Arm is the horizontal distance of an item meas-
ured from the reference datum.
Moment is the product of the weight of an item mul-
tiplied by its arm.
C.G. Center of Gravity
Standard Empty Weight
is the point at which the
airplane, or equipment, would balance if
suspended. Its distance from the reference
datum is found by dividing the total moment
by the total weight of the aircraft.
is the weight of the aircraft with engine flu-
ids and oil at operating levels.
Basic Empty Weight is the standard empty weight to which it is
added the optional equipment weight.
Useful Load is the difference between maximum takeoff
weight and the basic empty weight.
Maximum Takeoff Weight is the maximum weight approved to perform
the takeoff.
Maximum Landing Weight is the maximum weight approved for the
landing touchdown (for P2006T it is equiv-
alent to the Maximum Takeoff Weight).

Page 1 - 10
Section 1 – General
UNIT CONVERSION CHART
1st Edition – 2009, May 25th
UNIT CONVERSION CHART
MOLTIPLYING
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 Kilometres / hour [km/h]
Kilometres / hour [km/h] 0.5396 Knots [kts]
PRESSURE
Atmosphere [atm] 14.7 Pounds / sq. in [psi]
Pounds / sq. in [psi] 0.068 Atmosphere [atm]
LENGTH
Kilometres [km] 0.5396 Nautical miles [nm]
Nautical miles [nm] 1.853 Kilometres [km]
Meters [m] 3.281 Feet [ft]
Feet [ft] 0.3048 Meters [m]
Centimetres [cm] 0.3937 Inches [in]
Inches [in] 2.540 Centimetres [cm]
VOLUME
Litres [l] 0.2642 U.S. Gallons [US Gal]
U.S. Gallons [US Gal] 3.785 Litres [l]
AREA
Square meters [m2] 10.76 Square feet [sq ft]
Square feet [sq ft] 0.0929 Square meters [m2]

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Section 1 – General
LITRES / US GALLONS CONVERSION CHART
1st Edition – 2009, May 25th
16. LITRES /US GALLONS CONVERSION CHART
Litres US Gallons US Gallons Litres
5 1.3 1 3.8
10 2.6 2 7.6
15 4.0 3 11.4
20 5.3 4 15.1
25 6.6 6 22.7
30 7.9 8 30.3
35 9.2 10 37.9
40 10.6 12 45.4
45 11.9 14 53.0
50 13.2 16 60.6
60 15.9 18 68.1
70 18.5 20 75.7
80 21.1 22 83.3
90 23.8 24 90.9
100 26.4 26 98.4
110 29.1 28 106.0
120 31.7 30 113.6
130 34.3 32 121.1
140 37.7 34 128.7
150 39.6 36 136.3
160 42.3 38 143.8
170 44.9 40 151.4
180 47.6 45 170.3
190 50.2 50 189.3
200 52.8 55 208.2

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