Tecnam ROTAX 912UL 80Hp Technical specifications

2
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edition, October 2004 Doc. n° 92-13-021-01
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P92 Echo Super
I N T R O D U C T I O N
F LIG HT MANUAL
FLIGHT MANUAL
P92 ECHO SUPER
Powered by ROTAX 912UL 80Hp or ROTAX 912ULS 100Hp.
M ANUFACTURER : COSTRUZIONI AERONAUTICHE TECNAM S.r.l.
A IRCRAFT TYPE : P92 E CHO S UPER
S ERIAL NUMBER :...............................................................
M ANUFACTURING DATE :.....................................................................
WARNING
The Flight Manual must always be kept on board the aircraft. The aircraft
described herein is to be operated in accordance with procedures and limitations
described in this Flight Manual.
T HIS MANUAL IS VALID FOR THE P92 E CHO S UPER WITH EITHER R OTAX 912 80 H P
ENGINE OR R OTAX 912S 100 H P ENGINE .
F OR EVIDENT SAFETY REASONS AND UPON READING THIS MANUAL FOR THE FIRST TIME , IT
IS NECESSARY TO UNDERLINE ( PERHAPS ALSO HIGHLIGHT WITH A COLORED MARKER ) ANY
DIFFERENCES IN CHARTS AND TABLES AS APPLICABLE TO PERSONAL AIRCRAFT .
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RECORD OF REVISIONS
All revisions to the current Manual, except for actual weighing data, must be
recorded in the following table.
New text or amendments to revised pages shall be clearly marked by a vertical
black line on the left hand margin, with revision N° and date indicated on left
side of page.
RECORD OF REVISIONS
Rev N° Affected
Sections
Affected
Pages
Date
1 i i-1,3,4
14th April 2008
1 1 1-5, 6,7
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1 2 2-7,8
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TABLE OF CONTENTS
General Section 1
Limitations Section 2
Emergency procedures Section 3
Normal procedures Section 4
Performance Section 5
Weight and balance Section 6
Systems description Section 7
Ground handling and servicing Section 8
Supplements Section 9

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SECTION 1
GENERAL
TABLE OF CONTENTS
INTRODUCTION .......................................................................................................2
WARNINGS - CAUTIONS - NOTES............................................................................2
THREE VIEW DRAWING...........................................................................................3
DESCRIPTIVE DATA.................................................................................................4
CONTROL SURFACES TRAVEL LIMITS..................................................................4
ENGINE......................................................................................................................5
PROPELLER..............................................................................................................5
FUEL .........................................................................................................................6
OIL .............................................................................................................................6
COOLING ..................................................................................................................6
WEIGHTS ..................................................................................................................7
SPECIFIC LOADINGS...............................................................................................7
ABBREVIATIONS AND TERMINOLOGY..................................................................8
UNIT CONVERSION FACTORS ..............................................................................11

P92 Echo Super
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INTRODUCTION
The P92 E CHO S UPER is a twin seat single engine aircraft with a strut-braced
rectangular high wing, fixed main landing gear and steerable nose wheel.
This Flight Manual has been prepared to provide pilots and instructors with
information for the safe and efficient operation of this aircraft.
This Flight Manual contains 8 sections. Section 1 provides basic data and in-
formation of general interest in addition to definitions and explanations of
symbols, abbreviations and terminology commonly used.
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 degrada-
tion 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 re-
lated to safety but which is important or unusual.
WARNING
CAUTION
NOTE

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THREE VIEW DRAWING
• Dimensions shown refer to aircraft weight of 450 kg and normal operat-
ing tire pressure.
• Propeller clearance 360mm
• Propeller clearance with deflated front tire and compressed shock ab-
sorber 142mm
• Minimum ground steering radius 5.5m

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DESCRIPTIVE DATA
WING
Wing span: 8.7 m
Wing chord 1.4 m
Wing surface 12.0 m
2
Wing loading 37.5 kg/m
2
Aspect ratio 6.3
Taper ratio 1.0
Dihedral 1.5°
FUSELAGE
Overall length 6.4 m
Overall width 1.1 m
Overall height 2.5 m
EMPENNAGE
Stabilator span 2.9 m
Vertical tail span 1.2 m
LANDING GEAR
Wheel track: 1.8 m
Wheel base: 1.6 m
Main gear tire. Air Trac
Wheel hub and brake Marc Ingegno 5.00-5
Nose gear tire Sava 4.00-6
CONTROL SURFACES TRAVEL LIMITS
Ailerons Up 20° down 15° ± 2°
Stabilator Up 18° down 3° ± 1°
Trim-Tab 2° / 12° ±1°
Rudder RS 25° LS 25° ± 1°
Flaps 0° - 38° ±1°

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ENGINE
P92 Echo Super (80 Hp) P92 Echo Super 100 (100 Hp)
Manufacturer: Bombardier-Rotax GmbH Bombardier-Rotax GmbH
Model 912 UL 912 ULS
Engine type: Four cylinder horizontally-
opposed twins with overall
displacement of 1211.2 c.c.,
mixed cooling, (water-
cooled heads and air-cooled
cylinders), twin carburetors,
integrated reduction gear,
(2.273:1) with torque
damper. Compression ratio:
9.0:1.
Four cylinder horizontally-
opposed twins with overall dis-
placement of 1352 c.c., mixed
cooling, (water-cooled heads and
air-cooled cylinders), twin carbu-
retors, integrated reduction gear,
(2.4286:1) with torque damper.
Compression ratio: 10.3:1.
Maximum power: 81Hp (59.6 kW ) at 5800
rpm - max 5 min.. 100 Hp (73.5 kW) at 5800 rpm - max 5 min..
PROPELLER
P92 Echo Super
(80 Hp) P92 Echo Super 100 (100 Hp)
Manufacturer: F.lli Tonini Giancarlo
& Felice S.n.c. F.lli Tonini Giancarlo & Fe- lice S.n.c.
Model: GT-2/166/VSU-FW
101 SRTC GT-2/173/VRR-FW 101 SRTC
Number of blades: 2 2
Diameter: 1660 mm 1730 mm
Type: Fixed pitch - wood Fixed pitch – wood
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FUEL
Fuel grade: •High octane gasoline DIN 51600, O-NORM
1103 (red)
•Unleaded gasoline DIN 51603, O-NORM
1101
•AVGAS 100LL
Fuel tanks: 2 wing tanks integrated within the wing's leading
edge with drainage reservoir located in engine
cowling
Capacity of each wing tank 45 liters
Total capacity 90 liters
OIL
Oil system: Forced, with external oil reservoir
Oil: Automotive grade type oil type API "SF" or
"SG" preferably synthetic or semi-synthetic
Oil Capacity: 2.5 liters
COOLING
Cooling system: Mixed air and liquid pressurized closed circuit
system
Coolant: Antifreeze and water liquid mixture
Capacity 3 liters
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WEIGHTS
Maximum takeoff: 450 kg
Standard empty weight 289 kg
SPECIFIC LOADINGS
P92 Echo Super
(80 Hp) P92 Echo Super 100 (100 Hp)
Wing Loading 37.5 kg/m
2
37.5 kg/m
2
Power Loading 5.5 kg/hp 4.5 kg/hp
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ABBREVIATIONS AND TERMINOLOGY
AIRSPEED TERMINOLOGY AND SYMBOLS
CAS Calibrated Airspeed is indicated airspeed corrected for position and
instrument error.
IAS Indicated Airspeed: is the speed shown on the on-board airspeed in-
dicator.
TAS True Airspeed: is calibrated airspeed corrected for altitude and tem-
perature.
V
FE
Maximum Flap Extended Speed: is the highest speed permissible
with wing flaps in a prescribed extended position.
V
NO
Maximum Structural Cruising Speed: is the speed that should not be
exceeded except in smooth air, then only with caution.
V
NE
Never Exceed Speed: is the speed limit that may not be exceeded at
any time.
V
S
Stalling Speed.
V
S0
Stalling Speed or the minimum steady flight speed at which the air-
plane is controllable in the landing configuration at the most forward
center of gravity.
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.
Vr Rotation speed: is the speed at which the aircraft rotates about the
pitch axis during takeoff
Vobs Obstacle speed: is the speed at which the aircraft flies over a 15m
obstacle during takeoff or landing

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METEOROLOGICAL TERMINOLOGY
OAT Outside Air Temperature is the free air static temperature expressed in
degrees Celsius (°C).
T
S
Standard Temperature is 15°C at sea level pressure altitude and de-
creased by 2°C for each 1000 ft of altitude.
H
P
Pressure Altitude is the altitude read from an altimeter when the baro-
metric 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 2.273 (912UL) or 2.4286 (912S) 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 was actually
demonstrated.
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 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 con-
figuration per kilo of fuel consumed

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WEIGHT AND BALANCE TERMINOLOGY
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.
Standard
Empty
Weight
is the weight of a standard airplane, including unusable fuel, full oper-
ating fuels and full engine oil.
Basic Empty
Weight is the standard empty weight plus the weight of optional equipment.
Useful Load is the difference between takeoff weight and the basic empty weight.
Maximum
Weight is the maximum weight of the aircraft.
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 FACTORS
M ULTIPLYING BY 

 YIELDS
T EMPERATURE
Fahrenheit [°F]
( )
5
9
32⋅ −F
Celsius [°C]
Celsius [°C]
9
532⋅





+C
Fahrenheit [°F]
F ORCES
Kilograms [kg] 2.205 Pounds [lbs]
Pounds [lbs] 0.4536 Kilograms [kg]
S PEED
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] 1.852 Kilometers / hour [km/h]
Kilometers / hour [km/h] 0.540 Knots [kts]
P RESSURE
Atmosphere [atm] 14.7 Pounds / sq. in [psi]
Pounds / sq. in [psi] 0.068 Atmosphere [atm]
L ENGTH
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]
V OLUME
Liters [l] 0.2642 U.S. Gallons [US Gal]
U.S. Gallons [US Gal] 3.785 Liters [l]
A REA
Square meters [m
2
] 10.76 Square feet [sq ft]
Square feet [sq ft] 0.0929 Square meters [m
2
]

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SECTION 2
LIMITATIONS
TABLE OF CONTENTS
INTRODUCTION .......................................................................................................2
AIRSPEED LIMITATIONS.........................................................................................2
AIRSPEED INDICATOR MARKINGS .......................................................................3
POWERPLANT LIMITATIONS..................................................................................4
PROPELLER..............................................................................................................5
POWERPLANT INSTRUMENT MARKINGS .............................................................6
OTHER INSTRUMENT MARKINGS..........................................................................7
WEIGHT LIMITS........................................................................................................7
CENTER OF GRAVITY LIMITS.................................................................................7
APPROVED MANEUVERS........................................................................................7
FUEL..........................................................................................................................8

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INTRODUCTION
Section 2 includes operating limitations, instrument markings, and basic placards necessary
for safe operation of the P92 E CHO S UPER , its engine, standard systems and standard
equipment.
AIRSPEED LIMITATIONS
For all model
SPEED Km/h IAS REMARKS
V
NE
Never exceed speed
260
Never exceed this speed in any operation.
V
NO
Maximum Structural
Cruising Speed
200
Never exceed this speed unless in smooth
air, and then only with caution.
V
AManeuvering speed
150
Do not make full or abrupt control move-
ments above this speed as this may cause
stress in excess of limit load factor
V
FE
Maximum flap extended
speed
110
Never exceed this speed for any given flap
setting.

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AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code are explained in the following table valid
for P92 Echo Super 80 and P92 Echo Super 100:
For all model
MARKING IAS km/h SIGNIFICANCE
White arc 72 – 110 Flap Operating Range (lower limit is 1.1V
SO
, at maxi-
mum weight and upper limit is maximum speed permis-
sible with flaps extended at 38°)
Green arc 110 – 200 Normal Operating Range (lower limit is V
FE
at maxi-
mum weight and upper limit is maximum structural
speed V
NO
).
Yellow arc 200 – 260 Operations must be conducted with caution and only in
smooth air.
Red line 260 Maximum speed for all operations.

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POWERPLANT LIMITATIONS
The following table lists operating limitations for aircraft installed engine:
E NGINE MANUFACTURER : Bombardier Rotax GmbH.
E NGINE MODEL : 912 UL /912 ULS
M AXIMUM POWER :
Max Power (HP) Max RPM Max time (minuti)
912UL
912 ULS
912UL
912 ULS 912UL 912ULS
Takeoff
81 100 5800 5800 5 5
Max continuous
78 93 5500 5500 / /
TEMPERATURES :
912UL
912 ULS
Coolant, monitored at cylinder heads
150°C 135° C
Maximum Oil:
140°C 130° C
Minimum Oil
50°C 50° C
OIL PRESSURE:
912UL
912 ULS
Minimum
0.8 bar 0.8 bar
Maximum
5 bar 5 bar
CAUTION
Admissible pressure for cold start is 7 bar maximum for short periods.