ICP VENTURA YY-MM-62 Series Owner's manual

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
PAGE: 1/60
Manufacturer:
ICP S.r.l.
Address:
S.P. 16 km 15,150
Castelnuovo Don Bosco (AT)
ITALY
14022
Contacts:
Phone: [phone]
Fax: [phone]
Web: www.icp.it
Email: in[email protected]
The technical data and the information embodied therein are property of I.C.P. Srl and shall not be
disclosed in whole or in part to third parties, without prior written permission of I.C.P. Srl. The manual
must remain with the aircraft in case of sale.
Serial Number
YY-MM-62-XXXX-Z
Year 20YY

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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SUMMARY
1. GENERAL INFORMATION .................................................................................................. 7
1.1. CERTIFICATION CRITERIA ............................................................................................. 8
1.2. WARNING, CAUTION AND NOTE DEFINITIONS ............................................................ 9
1.3. SYMBOLS, ABBREVIATIONS AND GLOSSARY ............................................................. 9
1.4. UNIT CONVERSION TABLE .......................................................................................... 10
1.5. INSTALLED OPTIONAL / ADDITIONAL EQUIPMENT ................................................... 11
2. AIRPLANE AND SYSTEM DESCRIPTION ........................................................................ 11
2.1. ENGINE .............................................................................................................................. 11
2.1. COOLING SYSTEM........................................................................................................ 12
2.2. LUBRICATION SYSTEM ................................................................................................ 12
2.3. PROPELLER .................................................................................................................. 12
2.4. FUEL SYSTEM ............................................................................................................... 13
2.5. STRUCTURE.................................................................................................................. 15
2.6. LANDING GEAR ............................................................................................................. 16
2.7. FLIGHT CONTROLS ...................................................................................................... 17
2.8. ELECTRICAL SYSTEM .................................................................................................. 18
2.9. CABIN AND INSTRUMENTS .......................................................................................... 21
2.10. TECHNICAL SPECIFICATIONS ................................................................................. 24
2.11. THREE-VIEW DRAWING ............................................................................................ 26
3. OPERATING LIMITATIONS ............................................................................................... 27
3.1. STALL SPEEDS (VS1 AND VS0) .......................................................................................... 27
3.1. FLAP EXTENDED SPEED (VFE) ..................................................................................... 27
3.2. MANEUVERING SPEED (VA) ......................................................................................... 27
3.3. NEVER EXCEED SPEED (VNE) ...................................................................................... 27
3.4. CROSSWIND AND WIND LIMITATIONS ....................................................................... 27
3.5. SERVICE CEILING ......................................................................................................... 27
3.6. DESIGN LOAD FACTORS ............................................................................................. 28
3.7. PROHIBITED MANEUVERS .......................................................................................... 28
3.8. ENGINE LIMITATIONS (data source: Rotax manuals) ................................................... 28
3.9. WEIGHT AND BALANCE LIMITATIONS ........................................................................ 29
3.10. CREW ......................................................................................................................... 29

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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4. WEIGHT AND BALANCE ................................................................................................... 31
4.1. LIST OF STANDARD COMPONENTS INSTALLED ....................................................... 31
4.2. WIGHT AND EMPTY BALANCE DETERMINATION ...................................................... 32
4.3. PRE-FLIGHT WEIGHT AND BALANCE TABLE ............................................................. 33
5. PERFORMANCES ............................................................................................................. 37
5.1. TAKE-OFF AND LANDING DISTANCES (ROTAX 912ULS) .............................................. 37
5.1. RATE OF CLIMB (ROTAX 912ULS) ............................................................................... 38
5.2. CRUISING SPEED ......................................................................................................... 38
5.3. STALL SPEED................................................................................................................ 39
5.4. ENGINE RPM ................................................................................................................. 39
5.5. FUEL CONSUMPTION ................................................................................................... 40
5.6. OTHER ........................................................................................................................... 40
6. EMERGENCY PROCEDURES .......................................................................................... 41
6.1. ENGINE FAILURE DURING TAKE-OFF RUN ................................................................ 41
6.2. ENGINE FAILURE IMMEDIATELY AFTER TAKE-OFF .................................................. 41
6.3. ENGINE FALURE IN FLIGHT ......................................................................................... 42
6.4. FIRE IN THE ENGINE COMPARTMENT ........................................................................ 42
6.4.1. FIRE ON GROUND ................................................................................................. 42
6.4.2. FIRE IN FLIGHT ...................................................................................................... 43
6.5. EXCESSIVE ENGINE ROUGHNESS ............................................................................. 43
6.6. LOW OIL PRESSURE .................................................................................................... 43
6.7. LOW FUEL PRESSURE ................................................................................................. 43
6.8. ALTERNATOR FAILURE ................................................................................................ 43
6.9. EMERGENCY LANDING WITH ENGINE OFF ............................................................... 44
6.10. EMERGENCY LANDING WITH ENGINE ON .............................................................. 44
6.11. UNINTENTIONAL SPIN RECOVERY ......................................................................... 45
6.12. BALLISTIC RECOVERY SYSTEM .............................................................................. 45
7. NORMAL PROCEDURES .................................................................................................. 47
7.1. PRE-FLIGHT .................................................................................................................. 47
7.2. ENGINE START ............................................................................................................. 50
7.3. TAXI ............................................................................................................................... 50
7.4. BEFORE TAKE-OFF ...................................................................................................... 50
7.5. NORMAL TAKE-OFF ...................................................................................................... 51
7.6. SHORT TAKE-OFF / SOFT GROUND RUNWAY ........................................................... 52
7.7. APPROACH AND LANDING .......................................................................................... 52

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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7.8. ENGINE STOP ............................................................................................................... 53
7.9. PARKING / TYING-DONW ............................................................................................. 53
8. GROUND MANEUVERS AND SERVICE PROCESURES ................................................. 55
8.1. TOWING / AIRCRAFT HANDLING ................................................................................. 55
8.2. AIRCRAFT GROUND MOORING ................................................................................... 55
8.3. AIRCRAFT REFUELING ................................................................................................ 56
9. LABELS AND INDICTIONS REQUIRED ............................................................................ 57
9.1. AIRSPEED INDICATOR MARKINGS ............................................................................. 57
9.2. OPERATING LIMITATIONS ON THE INSTRUMENTS ................................................... 57
9.3. CREW INDICATIONS ..................................................................................................... 57
9.4. IDENTIFICATION PLATE ............................................................................................... 58
LIST OF REVISIONS .................................................................................................................... 59
FIGURE SUMMARY
Figure 1: Fuel system, firewall backward ...................................................................................... 14
Figure 2: Fuel System, firewall forward ......................................................................................... 14
Figure 3: Electrical system, firewall backward ............................................................................... 19
Figure 4: Electrical System, firewall forward .................................................................................. 20
Figure 5: VenturaTM Three view ..................................................................................................... 26
Figure 6: VenturaTM empty weighing and balancing scheme ......................................................... 33
Figure 7: VenturaTM W&B [kg x m]................................................................................................. 35
Figure 8: VenturaTM W&B [lbs x ft] ................................................................................................. 35

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
PAGE: 7/60
1. GENERAL INFORMATION
The aircraft to which this manual refers is intended for recreational or tourism flying and for flight
school purposes too.
This ultralight aircraft can be used for aerial work only where permitted.
This Pilot’s Operating Handbook provides information useful for the safe and efficient operation of
Ventura aircraft. It also contains supplemental data supplied by the aircraft manufacturer.
WARNING
READ CAREFULLY THIS MANUAL BEFORE THE
FIRST FLIGHT.
The VenturaTM aircraft is supplied with the Pilot’s Operating Handbook (this one), the Maintenance
Manual and the Spare Part Catalogue. These documents must be considered an integral part of the
aircraft and must follow the airplane during its all operational life and must be kept on board.
This manual must be carefully read, the pilot must know the meaning and understand the limitations,
the specifications and the systems of the airplane.
All the provisions concerning the pre-flight and daily checks, must be observed.
A separate Maintenance Manual is provided with this airplane; every instruction reported in must be
done within the specified deadlines with the scope of maintain an acceptable safety level of the
airplane.
For engine maintenance, for ballistic rescue system (if installed) and for any other additional
equipment, please refer to the original manufacturer's manuals of components.
WARNING
THE VENTURATM ULTRALIGHT IS AN
ULTRALIGHT AIRCRAFT INTENDEND FOR VFR
FLIGHT OPERATIONS ONLY. FLYING WITH
INSTRUMENTAL METEOROLOGICAL CONDITION
(IMC) IS STRICTLY FORBIDDEN AND CAN BE
EXTREMELY DANGEROUS. AVOID FLYING WITH
STRONG WIND, MORE THAN 30 KNOTS AND
EXCESSIVE GUST. THE VENTURATM IS NOT AN
AEROBATIC AIRPLANE, SO EVERY
AEROBATICS MANEUVER IS FORBIDDEN,
INCLUDED SPINS.
WARNING
ROTAX ENGINE HAS NOT BEEN CERTIFIED AS
AN AIRCRAFT ENGINE AND ITS FAILURE MAY
OCCUR AT ANY TIME. THE PILOT IS FULLY
RESPONSIBLE FOR CONSEQUENCES OF SUCH
A FAILURE.

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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WARNING
THE PILOT/OWNER IS ALSO RESPONSIBLE FOR
THE MAINTENANCE OF THE ENGINE.
EVEN THOUGH THESE ENGINES HAVE SHOWN
REMARKABLE RELIABILITY, ROTAX DRAWS
THE OWNER’S ATTENTION TO
MALFUNCTIONING ISSUE THAT CAN BE
REQUEST AN EMERGENCY LANDING.
THE RISK OF ENGINE FAILURE MUST BE
ALWAYS PLANNED DURING THE FLIGHT. THE
USERS MUST ALSO CHECK THAT THE ENGINE
MAINTENANCE WAS DONE AS THE
MAINTENANCE MANUAL OF THE ENGINE
INDICATES.
1.1. CERTIFICATION CRITERIA
The VenturaTM to which this manual refers, falls within the limits set by Italian law n°106 of
25.03.1985, and must therefore be considered as an ultralight airplane. The Maximum Take-Off
Weight allowed by Italian regulation is 472.5 Kg with a ballistic parachute system installed. In the
worst weather condition and maximum load condition, the VenturaTM has a maximum stall speed
less than 65 Km/h.
The Aero Club Italia allows the circulation of the ultralight according to the owner’s declaration that
the ultralight is complaint with the previous stated specifications. Since the Italian regulations do not
provide detailed design standards, construction and maintenance program of the ultralight, ICP Srl
has chosen to follow the EASA CS-VLA technical specifications with the purpose of assuring flight
safety.
The ultralight’s design MTOW (Maximum Take-Off Weight) is up to 600 Kg according to the CS-LSA
specification.
VenturaTM is available with many different accessories and options. It is the responsibility of the
owner to install accessories that do not exceed the maximum weight allowed in the country where
the airplane is registered. Do not exceed the design MTOW of 600 Kg, taking into consideration the
weight of the added accessories to the standard configuration, including weight of the occupants,
baggage and fuel.
Each modification made to the airplane without written approval from ICP Srl, will
automatically involve the loss of guarantee and relieves ICP Srl from all responsibility.

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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1.2. WARNING, CAUTION AND NOTE DEFINITIONS
The following definitions are applied to “warning”, “caution” and “note” in the Pilot’s Operating
Handbook.
WARNING
WARNING MEANS THAT THE NON-
OBSERVATION OF THE CORRESPONDING
PROCEDURE (PRACTICE, STATEMENT, FLIGHT
BEHAVIOR, ETC...) LEADS TO AN IMMEDIATE OR
IMPORTANT DEGRADATION OF THE FLIGHT
SAFETY, EVEN INCLUDED PERSONAL INJURY
OR LOSS OF LIFE.
CAUTION
CAUTION MEANS THAT THE NON-
OBSERVATION OF THE CORRESPONDING
PROCEDURE (PRACTICE, STATEMENT, FLIGHT
BEHAVIOR, ETC...) LEADS TO A MINOR OR TO A
MORE OR LESS LONG TERM DEGRADATION OF
THE FLIGHT SAFETY.
NOTE
Note means to draw the attention to any special item
not directly related to safety but which is important or
unusual.
1.3. SYMBOLS, ABBREVIATIONS AND GLOSSARY
CAS
-
Calibrated Air speed: airspeed in standard atmosphere and at sea level,
corrected by the positioning error of the sensing system.
IAS
-
Indicated Air speed: air speed, as indicated by the air speed indicator.
TAS
-
True Air speed: effective air speed.
VA
-
Manoeuvring speed: maximum speed at which full deflection of flight
controls is allowed without generating excessive load on the airframe.
VFE
-
Maximum flaps extended speed: maximum speed with the flaps extended.
Indicated by the upper white arc limit on the air speed indicator.
VNO
-
Maximum structural cruising speed: speed which must not be exceeded in
turbulent conditions. Indicated by the lower yellow arc limit on the air speed
indicator.
VNE
-
Never exceed speed: speed that should never been exceeded. Indicated
by the red line on the air speed indicator.

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
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VS
-
Stall speed (clean): minimum speed at which the aircraft can be maintained
in level flight with the flaps retracted. Indicated by lower green arc limit on
the airspeed indicator.
VS0
-
Minimum speed at which the aircraft can be maintained in level flight with
the flaps extended. Indicated by the lower white arc limit on the airspeed
indicator.
Standard
temperature
-
15°C (59°F) at Medium Sea Level
RPM
-
Revolutions per minute: engine rotation speed, in order to obtain propeller
rotation speed use gear ratio.
MAP
-
Manifold air pressure: pressure of the fuel/air supplied to the engine
measured by in the cylinders intake manifold.
G
-
Load factor: Ratio between aircraft generated lift and weight, is an
indication of airframe stress.
C.G.
-
Centre of gravity: the point where the resultant of the weight force is
applied.
ARM
-
Longitudinal distance from an item’s centre of gravity to the reference
datum.
MOMENTUM
-
Item weight multiplied by its arm.
C.G. LIMITS
-
Extreme positions of the centre of gravity that allows safe aircraft operation.
1.4. UNIT CONVERSION TABLE
Speed:
1 Km/h
0.54 Kt
1 Km/h
0.621 Mph
1 Kt
1.852 Km/h
1 Mph
1.609 Km/h
Distance:
1 m
3.28 ft
1 feet
0.3048 m
Pressure:
1 PSI
68.95 mbar
1 PSI
51.75 mmHg
1 mbar
0.0145 PSI
1 mmHg
0.019 PSI
Mass:
1 Kg
2.205 Lbs

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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1.5. INSTALLED OPTIONAL / ADDITIONAL EQUIPMENT
This manual describes the VenturaTM in the standard configuration and the most common optional /
additional equipment. Other optional / additional equipment not covered in this document, can be
described in an addendum or Technical Specification to the Pilot’s Operating Handbook.
It is the owner responsibility to produce such documentation and check that optional / additional
equipment is properly installed and satisfy applicable to regulations, POH prescriptions and weight
and balance limit of the aircraft.
WARNING
ADDITIONAL EQUIPMENT CAN BE AFFECT THE
EMPTY WEIGHT AND BALANCE OF THE
AIRPLANE CAUSING NOT CORRECT AND
DANGEROUS CONDITION DURIN PAYLOAD
WEIHTING AND BALANCING. IT IS THE PILOT’S
RESPONDIBILITY TO VERIFY THE W&B BEFORE
TAKE-OFF.
2. AIRPLANE AND SYSTEM DESCRIPTION
2.1. ENGINE
VenturaTM is equipped with a Rotax 912UL 912ULS, 912iS, 914UL or 915iS engine models.
Concerning use and limitations of engine and propeller, refer to Chapter 3.8 of this manual and to
engine User Manuals. All indications and communications provided by engine manufacturer, have
priority over this manual.
CAUTION
BECAUSE OF THE CONTINUOUS ISSUING OF
SERVICE BULLETIN AND SERVICE INFORMATION BY
BRP-ROTAX, ICP SRL DOES NOT INTEND TO
FORWARD SUCH INFORMATION TO THE OWNERS OF
ROTAX ENGINES.
THIS INFORMATION ARE AVAILABLE ON THE
WEBSITE WWW.ROTAX-AIRCRAFT-ENGINES.COM IN
THE “DOCUMENTATION” SECTION; ICP Srl ALSO
RECOMMEND CONTACTING THE OFFICIAL ROTAX
DEALER IN YOUR COUNTRY FOR ANY OTHER DETAIL.
ICP Srl DOES NOT TAKE ANY RESPONSIBILITY FOR
ANY DAMAGE TO PEOPLE AND/OR PROPERTY DUE
TO FAILURES IN APPLYING ROTAX INSTRUCTIONS.

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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2.1. COOLING SYSTEM
The engine is cooled by air, water and oil (mainly used as a lubricant) systems. The engine is
equipped with water and oil radiators. Air intakes on the engine cowling ensure the correct air
distribution around cylinders and radiators. Air flow around radiators and engine cooling surfaces is
assured by the low air pressure generated by the extraction lip on the lowest part of the engine
cowling. The cylinder heads are cooled by cooling liquid that is circulated by mechanical pump built
into the engine.
NOTE
For engine liquid specification refer to engine supplier
documentation.
CAUTION
WATER OR COOLANT CONTAINING WATER
MUST NEVER BE ADDED TO WATERLESS
COOLANT (E.G. EVANS). FOR COMPLETE
COOLANT SPECIFICATIONS REFER TO ROTAX
DOCUMENTATION.
2.2. LUBRICATION SYSTEM
The lubrication is ensured by a circulation of oil which is pressurized by a mechanical oil pump. An
oil tank is attached on the left side of engine mount. The oil pump sucks the motor oil from the oil
tank, via the oil cooler, and forces it through the oil filter to the points of lubrication in the engine.
Minimum and maximum quantity of lubricant at take-off is 2 - 3 liters.
NOTE
The specifications of the motor fluids are contained in
the documentation provided by ROTAX.
2.3. PROPELLER
The aircraft is equipped with the following propellers:
Standard configuration:
DUC Helice FLASH: 3 carbon fiber blades, variable pitch on the ground
Optional:
Ivoprop Medium: 3 blades in composite material, in flight electric variable pitch.

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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2.4. FUEL SYSTEM
The fuel is contained in two 36 liter each plastic tanks, 72 liters in total, located in the half-wing in
the first compartments behind the main spar and rear spar. The tanks are equipped with at sight
level indicator and are ventilated by a vent pipe placed on the cap and a further ventilation which
connects the tanks between the two wings.
The delivery of the two half-wing tanks is interconnected by a tube tied to the cockpit roof, from which
the fuel line (rear right side of the cabin) goes down through a T-junction towards a cylindrical 6 liters
tank, called Collector or Nourice, located in the fuselage behind the passenger seat.
This tank collects the fuel coming from the half-wings by fall, as final reserve. When the wing tanks
are empty, the fuel level in the Nourice starts decreasing and a float activates a warning light in the
cabin that indicates the reserve condition.
The collector tank output line leads to the power plant through an on/off valve that can be operated
from the cabin, by the pilot. The fuel return from the engine is also connected to the collector tank
which is then ventilated via a pipe connected to the upper left fuel tank.
On the bottom of the Nourice, in lowest point of the fuel system, there is a fuel sump with drain valve.
WARNING
USE THE ORIGINAL TANK CAP ONLY. THE
TANKS VENTILATION TAKES PLACE THROUGH
THE CAP VENT, ALWAYS CHECK THE
EFFICIENCY OF THE VENT DURING PRE-FLIGHT
CHECKS.
Pressure to the fuel system is given by a main engine driven fuel pump. The system is equipped
also with an auxiliary electric pump placed in series with a mechanical one located near the gearbox
of the engine. Turbocharged and injected engine are equipped with two electric fuel pump, on as
main pump and the other as auxiliary.
The system is also equipped with fuel macro-filters at each exit of the main tanks, a micro-filter
placed before the auxiliary electric pump at the front of the firewall and a further filter at each
carburetor line.
A double blue tank capacity is also available as an optional system.
WARNING
TAKE-OFF AND OPERATION WITH ON/OFF
VALVE IN CLOSED POSITION, CAUSES THE
ENGINE TO STOP. THE ENGINE CAN STOP
AFTER MORE THAN 60 SECONDS, SO CHECK
THE FUEL VALVE BEFORE TAKE-OFF AS
PRESCRIBED IN PROCEDURES CHAPTER 7.1.
Usable fuel quantity
70 liters
Not usable fuel quantity
2 liters

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
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Figure 1: Fuel system, firewall backward
Figure 2: Fuel System, firewall forward

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
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Approved fuel types:
MOGAS
912 UL/A/F
912 ULS / iS / 914 UL / 915iS
European standard
EN 228 Normal 1)
EN 228 Super 1)
EN 228 Super2)
EN 228 Super plus1)
EN 228 Super plus2)
Canadian standard
CAN/CGSB-3.5
Quality 13)
CAN/CGSB-3.5
Quality 34)
US standard
ASTM D4814
ASTM D4814
AVGAS
912 UL/A/F
912 ULS / iS / 914 UL / 915iS
US standard
AVGAS 100LL
(ASTM D910)
AVGAS 100LL
(ASTM D910)
1) Min. ROZ 90
2) Min. ROZ 95
3) Min. AKI*87
4) Min. AKI 91
The AVGAS 100LL fuel produces more stress on the valve seats due to its higher lead content, it
promotes deposits formation in the combustion chamber and it produces sediment in the lubrication
system. Therefore this fuel should only be used in case of evaporation problems (high altitude flight)
or when other types of fuel are not available.
According to the bulletin SI-912-016 R2 issued by Rotax, all the 912 series engines are compatible
with the use of E10 fuel (automotive unleaded petrol added with 10% ethanol). The engine and fuel
system have not been tested with fuels containing more than 10% ethanol, so their use is not
permitted.
WARNING
FOR COMPLETE SPECIFICATIONS OF USABLE
FUELS, PLEASE REFER ALSO TO THE ROTAX
OPERATOR'S MANUAL AND SERVICE
BULLETINS ISSUED BY ROTAX.
2.5. STRUCTURE
The VenturaTM aircraft is a monoplane controlled on three axes, it has airframe with side-by-side
seats, high wing braced by uprights and conventional tail surfaces. Most of the structure is made of
aluminum Al 6061 T6, with riveted joints. This aluminum alloy has a good resistance to corrosion,
but it may still not be sufficient under very aggressive conditions of use such as maritime
environments. In this case it is advisable to protect the inside of the structure with a complete primer.
All the skins and other elements are protected in the contact areas by applying a light layer of water-
based primer. Welded components are made of 25CrMo4 or AISI304 steel, while some plates or
angulars subject to high stresses are made of Al 2024 T3 aluminum alloy.
The fuselage (front and rear) is made of aluminum alloy AL6061 T6, with a semimonocoque structure
consisting of panels, bulkhead and stringers joined by blind rivets and solid rivets. The firewall
bulkhead is made of galvanized sheet.

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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The wing has a Riblett GA35A-418 profile with Junkers type flaperons that guarantee lateral
controllability even at low speeds. In order to reduce stall speed, plastic vortex generators are applied
to the nose of the wing. The wing has a rectangular plan, is not twisted and has a dihedral angle.
The wing structure is made up of spars, ribs and coverings, all in aluminum alloy AL 6061 T6. The
horizontal empennage has a symmetrical biconvex profile with a fixed stabilizer and a mobile
elevator fitted on its left side with an "antibalance TAB" with electric trim adjustment.
The horizontal tail has a rectangular plan, it is not warped and has no dihedral angle. It is made in
aluminum alloy AL 6061 T6.
The front and rear spars of the stabilizer are bolted to mounting plates on the fuselage.
The vertical empennage consists of a fixed fin and a movable rudder. The front spar of the fin is
bolted to the front spar of the stabilizer, while the rear spar is bolted to the fuselage. The rudder is
connected to the fin by three hinges. The connection between fuselage and fin is made up of a dorsal
cover called “Anti-spin” which increases directional stability. All these surfaces described are made
in Al 6061 T6.
The engine mount is a welded 25CrMo4 steel tubes framework, divided into a part fixed on the
fuselage and a second part fixed to the engine, with the interposition of silentblocks.
2.6. LANDING GEAR
The main landing gear consists of a single 7075 aluminum alloy leaf spring. The nose gear consists
of a steering leg with shock absorbing made by rubber pads; it is steered in order to facilitate taxiing.
The brakes are hydraulic disc brakes, with actuators on the pilot side pedals only (actuators on co-
pilot side available as an option). Brakes are independent on the two wheels and controlled by rudder
pedals (brake levers upper the rudder pedals), there is no brakes on the front wheel.
The parking brake (optional) consists of a shut-off valve placed in series with the brake pumps. To
engage parking brake apply pressure on the pedals, then turn the lever to the "BRAKE ON" position.
Use the parking brake for short periods only; in the event of prolonged stop, block the wheels of the
aircraft with chocks or tie down the aircraft according to the procedure provided.
WARNING
IF PARKING BRAKE LEVER IS TURNED TO
"BRAKE ON" POSITION WITHOUT FIRST
APPLYING PRESSURE TO THE BRAKE PEDALS,
THE AIRCRAFT WILL NOT BE BRAKED AND THE
PEDALS WILL BE NOT EFFICIENT.
THE BREAKING SYSTEM WILL OPERABLE BY
REMOVING THE PARKING BRAKE ONLY.
Brake fluid:
mineral based oil (Renofluid 3.000 IT, Fiat TUTELA GI/A);
(DO NOT USE SYNTHETIC OIL such as DOT4).
Standard wheel dimensions:
6.00’’x4.00’’
6.00’’x6.00’’ (Tundra tires and fairing wheels are optional)

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Ultralight Aircraft
Pilot’s Operating Handbook
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FIRST ISSUE: 04/05/2018
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2.7. FLIGHT CONTROLS
The aircraft is equipped with single "Y" stick (double stick available as optional) and double rudder
pedals.
Pitch control
The elevator is moved by a Ø 3.2 mm steel cable system, the tension of the cables is adjustable
through a special register reachable through the inspection trapdoor located on the bottom of the
rear fuselage.
Elevator deflection:
+25° / -25° ±2°
Roll control
Full-opening flaperons are driven by rigid rods and bell crank connected to a torsion tube rotated by
the stick.
Flaperons deflection (flaps retracted):
+15,5° / -15,5° ±2°
Yaw control
The rudder is moved by a Ø 3.2 mm steel cable system, the tension of the cables is adjustable by a
special register placed near the pedals.
Rudder deflection:
+28° / -28° ±2°
Flaps control
Full-opening flaperons are controlled by the flap mixer, rigid rods and bell crank connection. The flap
mixer is moved by an electric actuator, the flaps are controlled by a switch located on the instrument
panel.
Flaperons deflection (with a centered aileron):
0°, 13,5° e 27° ±2°
Trim Elevator
The aircraft is equipped with an electrically controlled longitudinal trim that moves the neutral position
of the "antibalance TAB" mounted on the elevator. The trim is controlled by a switch on the instrument
panel (stick control with LED indicator of position on the panel is available as option).
Engine control
Engine controls are:
- Double rigid rod type throttle with adjustable clutch;
- Starting Enrichment (Choke), positioned next to the pilot's throttle;

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
VENTURA-POH-ENG
Rev. 00
SERIAL NUMBER:
YY-MM-62-XXXX-Z
FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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- Hot Air Control for Airbox (standard on Rotax 912ULS/iS, 914UL and 915iS, optional on
Rotax 912 UL);
- Auxiliary electric fuel pump;
- On/off fuel valve, placed on the floor;
- Magnetos Key switch 1 and 2;
- Master switch that connects the electrical system to the 12V battery.
The engine can also work with MASTER in OFF position because the ignition system is independent
and can only be switched off via the Magnetos Key. Is it also possible to shut off the engine by
closing the fuel shut off valve. In case of MASTER in OFF position, the instruments and the electrical
systems cannot work. For safety reasons, the key must be removed when the engine is switched
off.
WARNING
THE ENGINE CAN BE STARTED EVEN IF THE
MASTER IS IN OFF POSITION. IT IS SUFFICIENT
THAT THERE IS ONLY ONE SWITCH OF THE
MAGNETS IN THE ON POSITION AND THAT THE
PROPELLER IS ROTATED MANUALLY, TO HAVE
A START.
ONE MAGNETO SWITCH IN ON POSITION CAN
BE SUFFICIENT TO START THE ENGINE IF THE
PROPELLER IS MANUALLY ROTATED.
FOR THAT REASON ALWAYS VERIFY THAT THE
MAGNETOS ARE IN OFF POSITION BEFORE
ROTATING THE PROPELLER MANUALLY.
The MASTER switch is located under to the pilot's throttle, in the bottom strip. All the switches and/or
the engine controls are activated by moving UP or FORWARD, with the exception of Choke and
Airbox Hot Air which are activated by pulling the command BACK.
2.8. ELECTRICAL SYSTEM
The following diagram shows the electrical system:

VENTURATM
Ultralight Aircraft
Pilot’s Operating Handbook
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SERIAL NUMBER:
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FIRST ISSUE: 04/05/2018
REVISION 00: 04/05/2018 NOT CONTROLLED COPY
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Figure 3: Electrical system, firewall backward

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Ultralight Aircraft
Pilot’s Operating Handbook
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Rev. 00
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Figure 4: Electrical System, firewall forward
Electrical system and standard panel layout in Rotax 914UL and Rotax 912iS/915iS engine
installations are different. Refer to the engine installation or operator manual and/or Technical
Specification for detailed scheme and configuration of the system.