Tecnam P92 Echo MKII Technical specifications

Aircraft Flight Manual
Doc. No. 92/265
1stEdition –Rev. 0
2020, February 26th
TECNAM P92 EchoMKII
MANUFACTURER: COSTRUZIONI AERONAUTICHE TECNAMS.p.A.
AIRCRAFT MODEL:P92 Echo MKII
SERIAL NUMBER: ……………..............
BUILD YEAR:……….………................
REGISTRATION MARKINGS: ……………..
This manual contains information to be furnished to the pilot as required by
LTF-UL 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.
Costruzioni Aeronautiche TECNAM S.p.A.
Via Maiorise
CAPUA (CE) –Italy
Tel. [phone]
WEB:www.tecnam.com
This document and the information thereon is the property of Costruzioni Aeronautiche Tecnam S.p.A., and may only be used for the purpose for which
Tecnam products are supplied, and/or use and maintenance of Tecnam Aircraft.
Reproduction or use of the data, information, drawings thereon, in whole or in part, is strictly prohibited without the express written permission of
Costruzioni Aeronautiche Tecnam.

Page 0 - 2
Aircraft Flight Manual
INDEX
1st Edition - Rev.0
Section 0
INDEX
1. Record of Revisions............................................................... 3
2. List Of effective Pages ..........................................................5
3. Foreword................................................................................ 6
4. Section Lists..........................................................................7

Page 0 - 3
Aircraft Flight Manual
RECORD OF REVISIONS
1st Edition - Rev.0
1. RECORD OF REVISIONS
Any revision to the present Manual, except actual weighing data, is recorded: a
Record of Revisions is provided at the front of this manual and the operator is ad-
vised to make sure that the record is kept up-to-date.
The Manual issue is identified byEdition and Revision codes reported on each page,
lower right side.
The revision code is numerical and consists of the number "0"; subsequent revisions
are identified by the change of the code from "0" to "1" for the first revision to the
basic publication, "2" for the second one, etc.
Should be necessary to completely reissue a publication for contents and format
changes, the Edition code will change to the next number (“2” for the second edi-
tion, “3” for the third edition etc).
Additions, deletions and revisions to existing text will be identified by a revision
bar (black line) in the left-hand margin of the page, adjacent to the change.
When technical changes cause expansion or deletion of text which results in un-
changed text appearing on a different page, a revision bar will be placed in the right-
hand margin adjacent to the page number of all affected pages providing no other
revision bar appears on the page.
These pages will be updated to the current regular revision date.
In order to be constantly updated on change on this document from TECNAM, It is
the responsibility of the owner to register on TECNAM website at:
www.tecnam.com
NOTE: It is the responsibility of the owner to maintain this handbook in a current
status when it is being used for operational purposes.

Page 0 - 4
Aircraft Flight Manual
RECORD OF REVISIONS
1st Edition - Rev.0
Rev
Revised page
Description of
Revision
0
All
First issue

Page 0 - 5
Aircraft Flight Manual
LIST OF EFFECTIVE PAGES
1st Edition - Rev.0
2. LIST OF EFFECTIVE PAGES
The List of Effective Pages (LOEP), applicable to manuals of every operator, lists all the
basic AFM pages: each manual could contain either basic pages or one variant of these
pages when the pages of some Supplements are embodied.
Pages affected by the current revision are indicated by an asterisk (*) following the revi-
sion code.
1st Edition, Rev.0
February 26h 2020
Section
Pages
Revision
Section 0
All
Rev 0
Section 1
All
Rev 0
Section 2
All
Rev 0
Section 3
All
Rev 0
Section 4
All
Rev 0
Section 5
All
Rev 0
Section 6
All
Rev 0
Section 7
All
Rev 0
Section 8
All
Rev 0
Section 9
All
Rev 0

Page 0 - 6
Aircraft Flight Manual
FOREWORD
1st Edition - Rev.0
3. FOREWORD
The P92 MKII is a twin seat, single engine light aircraft with a strut braced high wing and
tricycle fixed landing gear with steerable nose wheel.
Section 1 supplies general information and it contains definitions, symbols explanations,
acronyms and terminology used.
Before using the airplane, you are recommended to read carefully this manual: a deep
knowledge of airplane features and limitations will allow you for operating the airplane
safely.
For further information, please contact:
COSTRUZIONI AERONAUTICHE TECNAMS.p.A.
Via MAIORISE
CAPUA (CE) - ITALY
+39 (0)823.62.22.97[e-mail]

Page 0 - 7
Aircraft Flight Manual
SECTION LISTS
1st Edition - Rev.0
4. SECTION LISTS
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
Ground Handling, Servicing and
Maintenance
Section 8
Supplements
Section 9

Page 0 - 8
Aircraft Flight Manual
SECTION LISTS
1st Edition - Rev.0
Intentionally left blank

Page 1 - 1
Section 1 - General
INDEX
1st Edition - Rev.0
Section 1 - GENERAL
INDEX
INDEX ................................................................................................. 1
1Introduction .................................................................................. 2
Warning –Caution –Note .......................................................... 2
2Three View and Dimensions ........................................................ 3
Three View ................................................................................ 3
Dimensions ................................................................................ 4
3General Features.......................................................................... 5
Control Surfaces Travel Limits ................................................. 5
Engine ........................................................................................ 5
Propeller .................................................................................... 5
Fuel ............................................................................................ 6
Lubrication ................................................................................ 6
Cooling....................................................................................... 6
weights ...................................................................................... 7
Standard weights ...................................................................... 7
Specific Loading........................................................................ 7
4Acronyms and terminology .......................................................... 8
General Airspeed Terminology And Symbols........................... 8
Meteorological terminology ...................................................... 9
Engine Power terminology ........................................................ 9
Aircraft performance and flight planning terminology .......... 10
Weight and balance terminology ............................................ 11
5Unit conversion chart................................................................. 12
6Litres / US gallons conversion chart ......................................... 13

Page 2 - 1
Section 1 - General
INTRODUCTION
1st Edition - Rev.0
1INTRODUCTION
The Aircraft Flight Manual has been implemented to provide the owners with in-
formation for a safe and efficient use of the aircraft TECNAM P92 Echo MKII.
The P92 Echo MkII is a twin seat, single engine light aircraft with a strut braced high
wing and tricycle fixed landing gear with steerable nose wheel.
This Flight Manual has been prepared to provide pilots and instructors with infor-
mation for the safe and efficient operation of this aeroplane.
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
CAUTION
The non-observation of the corresponding procedure can lead toan
equipment damage which leads to a reduction of the flight safety in
a short or longer time interval.
NOTE
Draws the attention to a procedure not directly related to safety of
flight.

Page 3 - 1
Section 1 - General
THREE VIEW AND DIMENSIONS
1st Edition - Rev.0
2THREE VIEW AND DIMENSIONS
THREE VIEW
Fig. 1.1 –General views
Dimensions shown refer to normal operating tire pressure.
Propeller ground clearance 336 mm
Propeller ground clearance with deflated front tire and nose wheel shock ab-
sorber compressed 84mm

Page 1 -4
Section 1 - General
THREE VIEW AND DIMENSIONS
1st Edition - Rev.0
DIMENSIONS
Overall dimensions
Wingspan
8.77 m /28.77 ft
Length
6.81 m/22.34 ft
Overall height
2.66 m/8.72 ft
Wing
Wing surface
12.1 m2/130.24 ft2
Mean Geometric Chord
1.40 m/4.59 ft
Dihedral
1°30’
Aspect ratio
6.35
Main Landing Gear
Wheel Track
1.84 m/6.04 ft
Wheelbase
1.74 m
Tire (Air Trac)
5.00-5
Nose Landing Gear
Tire (Air Trac)
5.00-5

Page 1 -5
Section 1 - General
GENERAL FEATURES
1st Edition - Rev.0
3GENERAL FEATURES
CONTROL SURFACES TRAVEL LIMITS
The control surfaces travel limits are reported in the Aircraft Maintenance Manual.
ENGINE
Manufacturer
Bombardier Rotax GmbH
Model
912 ULS2
Engine type
4 cylinder horizontally-opposed twins
with overall displacement of 1352 c.c.,
mixed cooling, (water-cooled heads and
air-cooled cylinders), twin carburetors,
integrated reduction gear with torque
damper.
Maximum power (at declared rpm)
73.5kW (98.5hp) @5800rpm (max.5’)
69.0kW (92.5hp) @5500rpm (cont.)
PROPELLER
Manufacturer
Sensenich
Model
W68T2ET-70J
Number of blades:
2
Diameter
1730 mm (no reduction allowed)
Type
Fixed pitch –wood

Page 1 -6
Section 1 - General
THE CONTROL SURFACES TRAVEL
LIMITS ARE REPORTED IN THE
AIRCRAFT MAINTENANCE MANUAL.
1st Edition - Rev.0
FUEL
Approved fuel: MOGAS ASTM D4814
MOGAS EN 228 Super/Super Plus (Min RON 95)
AVGAS 100LL (ASTM D910)
(see also Section 2)
Fuel tanks
Two wing tanks integrated within the wing’s
leading edge. Equipped with finger strainers
outlet and with drain fittings.
Capacity of each wing tank
45 litres
Tanks overall capacity
90 litres
Overall usable fuel
86.9 litres
Overall unusable fuel
3.1 litre
LUBRICATION
Lubrication system
Forced type with external reservoir
Oil
Lubricant specifications and grade are detailed
into the “Rotax Operators Manual” and in its re-
lated documents.
Oil capacity
Max. 3 litres –min. 2.0 litres
COOLING
Cooling system
Mixed air and liquid pressurized closed circuit
system
Coolant liquid
Coolant type and specifications are detailed into
the “Rotax Operator’s Manual” and in its related
documents.

Page 1 -7
Section 1 - General
THE CONTROL SURFACES TRAVEL
LIMITS ARE REPORTED IN THE
AIRCRAFT MAINTENANCE MANUAL.
1st Edition - Rev.0
WEIGHTS
See Section 2.
STANDARD WEIGHTS
Empty Weight: see weighing record on Section 6.
SPECIFIC LOADING
MTOW 600 kg
Wing Loading
49.6 kg/m2
Power Loading
6.1 kg/hp

Page 1 -8
Section 1 - General
ACRONYMS AND TERMINOLOGY
1st Edition - Rev.0
4ACRONYMS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
CAS
Calibrated Airspeed is the indicated airspeed, corrected taking
into account the errors related to the instrument itself and its
installation.
IAS
Indicated Airspeed is the speed shown on the airspeed indicator.
TAS
TrueAirspeed is theCAS airspeed corrected taking into account
altitude and temperature.
VA
Design Manoeuvring speed is the speed above the which it is
not allowed to make full or abrupt control movement.
VFE
Maximum Flap Extended speed is the highest speed permissible
with flaps extended.
VNO
MaximumStructural CruisingSpeedisthe speed thatshouldnot
be exceeded, except in smooth air and only with caution.
VNE
Never Exceed Speed is the speed limit that maynot be exceeded
at anytime.
VS
Stall Speed.
VS0
Stall Speed in landing configuration (full flaps).
VS1
Stall speed in the given flap configuration.
VX
BestAngle-of-Climb Speed isthespeedwhich allowsbest ramp
climb performances.
VY
Best Rate-of-Climb Speed is the speed which allows the best
gain in altitude over a given time.
VR
Rotation speed: is the speed at which the aircraft rotates about
the pitch axis during take-off

Page 1 -9
Section 1 - General
ACRONYMS AND TERMINOLOGY
1st Edition - Rev.0
METEOROLOGICAL TERMINOLOGY
ISA
International Standard Atmosphere: is the air atmospheric standard
condition at sea level, at 15°C (59°F) and at 1013.25hPa
(29.92inHg).
QFE
Official atmospheric pressure at airport level: it indicates the air-
craft absolute altitude with respect to the official airport level.
QNH
Theoretical atmospheric pressure at sea level: is the atmospheric
pressure reported at the medium sea level, through the standard air
pressure-altitude relationship, starting from the airport QFE.
OAT
Outside Air Temperature is the air static temperature expressed in
degrees Celsius (°C).
TS
Standard Temperature is 15°C at sea level pressure altitude and de-
creased by 2°C for each 1000 ft of altitude.
HP
Pressure 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 engine.

Page 1 -10
Section 1 - General
ACRONYMS AND TERMINOLOGY
1st Edition - Rev.0
AIRCRAFT PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
Crosswind Velocity
is the velocity of the crosswind component
for which adequate control of the airplane
during take-off 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.

Page 1 -11
Section 1 - General
ACRONYMS AND TERMINOLOGY
1st Edition - Rev.0
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 measured
from the reference datum.
Moment
is the product of the weight of an item multi-
plied by its arm.
C.G.
Center of Gravity is the point at which the
airplane, or equipment, would balance if sus-
pended. Its distance from the reference datum
is found by dividing the total moment by the
total weight of the aircraft.
Standard Empty Weight
is the weight of the aircraft with engine fluids
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 take-off
weight and the basic empty weight.
Maximum Take-off Weight
is the maximum weight approved to perform
the take-off.
Maximum Landing Weight
is the maximum weight approved for the land-
ing touchdown (for P92 Echo MKII it is
equivalent to the Maximum Takeoff Weight).
Tare
is the weight of chocks, blocks, stands, etc.
used when weighing an airplane, and is in-
cluded in the scale readings. Tare is deducted
from the scale reading to obtain the actual
(net) airplane weight.

Page 1 - 12
Section 1 - General
UNIT CONVERSION CHART
1st Edition - Rev.0
5UNIT CONVERSION CHART
MOLTIPLYING
BY 
YIELDS
TEMPERATURE
Fahrenheit
[°F]
5 F 32
9
Celsius
[°C]
Celsius
[°C]
 9  

 C

 32
 5 

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]
1.852
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]