YUMA ROTAX 912 UL - 912 ULS - 914 UL YUMA

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YUMA ROTAX 912 UL - 912 ULS - 914 UL YUMA
YUMA
SEMIFINISHED VERSION
The semifinished YUMA is already structurally assembled:
- The fuselage is comprised of a welded tubular alloy-steel
cockpit structure and riveted aluminum tail cone
(with internal anti-corrosion primer).
- Riveted aluminium-alloy wings, horizontal and vertical
stabilizers.
- All control surfaces and flaps are of aluminum alloy
covered with 90 gr/m2 Dacron fabric.
- Engine mount and wing struts in CroMoly steel,
cockpit door frames in aluminum-alloy.
- Alloy-steel exhaust system.
- Fuel quick drain.
- Battery.
- Polycarbonate side windows, ceiling and windshield.
- Aluminum wing tanks and 5 liter header tank.
- Composite wing tips, stabilizer tips, cowling and internal
panels.
- Blank instrument panel.
- Leaf spring main gear, front fork and wheels complete
with disk brakes.
- Rudder pedals, flap control system and joysticks.
- Control cables, small parts for the complete assembly.
YUMA
ROTAX 912 UL - 912 ULS - 914 UL
- Padded leather seats.
Approximately 200 hours are required to complete
the aircraft. Not included in the kit: engine, propeller,
instruments and paint.
YUMA
SEMIFINISHED
Via Confalonieri 22 - 23894 Cremella (Lecco) Italy
Phone +39 039.9212128 - Fax +39 039.9212130
www.alisport.com - [email protected]
Silent Alisport LLC
Tullahoma Regional Airport - P.O. Box 996 - Tullahoma, TN 37388, USA
Phone +931.455.5994 - Cellular +931.434.3434
www.alisport.com - [email protected]
1006
alisport srl
YUMA
SINGLE ENGINE,
TWO-SEATER SIDE-BY-SIDE
-
Steerable telescopic nose strut (steering horn).
Heat-treated tapered leaf-spring main landing gear.
Wheels with hydroconic brakes.
Main landing gear tyres 8.00/6” 6Ply.
Streamlined alloy-steel wing struts.
Alloy-steel exhaust system.
Engine cowling.
Powerplant complete with fluids.
G.T. wooden two-blade propeller with spinner or, by
request, three-bladed IDROVARIO variable pitch propeller.
The fuselage is comprised of a welded tubular alloy-steel
cockpit structure and riveted aluminium alloy tail cone.
The wings and horizontal & vertical stabilizers are riveted
aluminium alloy. The slats are in carbon fiber. All movable
surfaces: ailerons, flaps, rudder and elevator are aluminium
alloy covered with 90gr/m2 DacronTM fabric. The windshield,
door windows and cockpit roof are 2 mm transparent
polycarbonate. The cockpit doors are of square aluminium
alloy tubing. The wingtips and stabilizer tips are composite.
1,18 m
COCKPIT AND CONTROLS
1,74 m
6,45 m
2,80 m
0,80 m
Dual rudder pedals with cable connection to the rudder.
Padded leather seats with three-point safety harness.
Aluminium alloy instrument panel.
Baggage compartment behind seats.
Dual flight controls.
Dual throttle control.
Electric or manual flaps.
Combined single lever wheel-brake (steerable via pedals)
and parking brake.
- Electric trim (pitch).
- Steerable nose wheel.
- Cabin heat.
Airspeed indicator.
Altimeter.
Vertical speed indicator.
Bank indicator.
Magnetic compass.
Tachometer.
Hour meter.
Voltmeter.
Oil and cylinder-head temperature gauge.
Oil pressure gauge.
Fuel pressure gauge.
Fuel level gauges.
Alternator indicator light.
Flap switch with indicator lights.
Strobe light.
ELECTRIC SYSTEM
-
15A alternator integral with the engine.
Voltage regulator.
Starter motor.
Circuit breakers.
Master switch.
Battery quick-disconnect.
FUEL SYSTEM
- Gravity feed.
- Two 40 liter wing tanks and one 5 liter header tank;
total 85 liters.
- Mechanical fuel pump (engine mounted).
- Auxiliary electrical fuel pump.
- Gascolator with fuel drain.
TECHNICAL DATA
2,00 m
9,75 m
2,45 m
-
-
- 12V – 17 Ah battery.
FUSELAGE AND WINGS
2,46 m
The fuel system is comprised of two wing tanks and a
header tank at the firewall providing a total endurance of
up to six hours. To maximize the results possible with the
aircraft, Alisport provides its clients with complete technical
assistance and specialized flight training to both refine the
pilot’s flying techniques and make full use of the YUMA’s
capability. The training includes take-offs and landings on
difficult terrain, obstacle clearance, mountain flying, plus
unusual attitude recovery and emergency procedures. The
program is design to give the pilot intimate knowledge of the
aircraft and addresses all aspects of flight safety.
EXTERIOR
1,49 m
The flight characteristics of the YUMA are enhanced by an
optimized wing profile and carbon-fiber leading edge slats
(Handley-Page type) that directly adress the requirements of
S.T.O.L. flight. The ability to perform challenging landings in
confined spaces is further enhanced by generous sizing of the
control surfaces which provide exceptional maneuverability
and do not lose control effectiveness at very low airspeeds.
Additionally, the large flaps permit steep final approaches
to facilitate descent over tall obstacles at the edges of an
airfield without wasting valuable field length. The cockpit
layout provides both comfort and unobstructed visibility that
an aircraft of this type must provide whether used for sport
flying or aerial observation.
INSTRUMENTS
1,52 m
The development of the Yuma began in 1994 with the goal of
surpassing the technical and flight characteristics of existing
light S.T.O.L (Short Take-Off & Landing) aircraft. The project
focused on the following design requirements:
- assurance of an aircraft designed and constructed to the
most stringent aeronautical specifications;
- ability to take-off and land from virtually any field having
obstructions or limited space without sacrificing good cruise
speed;
The techniques and materials used throughout the
construction of the YUMA are typical of the certified aircraft
industry.
Wing span
Cabin width
Length
Height
Wheelbase
Wing area
Aspect ratio
Empty weight
Maximum takeoff weight
Wing loading
9,75 m
1,18 m
6,45 m
2,45 m
2,00 m
13,4 m2
6,6
282 kg
450 kg
33,5 kg/m2
PERFORMANCE
ROTAX 912 UL (80 hp)
ROTAX 912 ULS (100 hp)
ROTAX 914 UL (115 hp)
Maximum speed
Cruise speed 75%
Stall speed (without flaps)
Stall speed (with flaps)
Rate of climb
Takeoff distance (with 1 person)
Takeoff distance (full load)
Landing distance
Max ceiling
Fuel capacity
Endurance with max paylod at
cruise speed 75%
175 km/h
150 km/h
55 km/h
50 km/h
6 m/s
40 m
45 m
55 m
5000 m
85 l
5,2 h
185 km/h
160 km/h
55 km/h
50 km/h
8 m/s
30 m
40 m
55 m
5000 m
85 l
4,5 h
195 km/h
170 km/h
55 km/h
50 km/h
10 m/s
30 m
40 m
55 m
7000 m
85 l
4,1 h
YUMA
SINGLE ENGINE,
TWO-SEATER SIDE-BY-SIDE
-
Steerable telescopic nose strut (steering horn).
Heat-treated tapered leaf-spring main landing gear.
Wheels with hydroconic brakes.
Main landing gear tyres 8.00/6” 6Ply.
Streamlined alloy-steel wing struts.
Alloy-steel exhaust system.
Engine cowling.
Powerplant complete with fluids.
G.T. wooden two-blade propeller with spinner or, by
request, three-bladed IDROVARIO variable pitch propeller.
The fuselage is comprised of a welded tubular alloy-steel
cockpit structure and riveted aluminium alloy tail cone.
The wings and horizontal & vertical stabilizers are riveted
aluminium alloy. The slats are in carbon fiber. All movable
surfaces: ailerons, flaps, rudder and elevator are aluminium
alloy covered with 90gr/m2 DacronTM fabric. The windshield,
door windows and cockpit roof are 2 mm transparent
polycarbonate. The cockpit doors are of square aluminium
alloy tubing. The wingtips and stabilizer tips are composite.
1,18 m
COCKPIT AND CONTROLS
1,74 m
6,45 m
2,80 m
0,80 m
Dual rudder pedals with cable connection to the rudder.
Padded leather seats with three-point safety harness.
Aluminium alloy instrument panel.
Baggage compartment behind seats.
Dual flight controls.
Dual throttle control.
Electric or manual flaps.
Combined single lever wheel-brake (steerable via pedals)
and parking brake.
- Electric trim (pitch).
- Steerable nose wheel.
- Cabin heat.
Airspeed indicator.
Altimeter.
Vertical speed indicator.
Bank indicator.
Magnetic compass.
Tachometer.
Hour meter.
Voltmeter.
Oil and cylinder-head temperature gauge.
Oil pressure gauge.
Fuel pressure gauge.
Fuel level gauges.
Alternator indicator light.
Flap switch with indicator lights.
Strobe light.
ELECTRIC SYSTEM
-
15A alternator integral with the engine.
Voltage regulator.
Starter motor.
Circuit breakers.
Master switch.
Battery quick-disconnect.
FUEL SYSTEM
- Gravity feed.
- Two 40 liter wing tanks and one 5 liter header tank;
total 85 liters.
- Mechanical fuel pump (engine mounted).
- Auxiliary electrical fuel pump.
- Gascolator with fuel drain.
TECHNICAL DATA
2,00 m
9,75 m
2,45 m
-
-
- 12V – 17 Ah battery.
FUSELAGE AND WINGS
2,46 m
The fuel system is comprised of two wing tanks and a
header tank at the firewall providing a total endurance of
up to six hours. To maximize the results possible with the
aircraft, Alisport provides its clients with complete technical
assistance and specialized flight training to both refine the
pilot’s flying techniques and make full use of the YUMA’s
capability. The training includes take-offs and landings on
difficult terrain, obstacle clearance, mountain flying, plus
unusual attitude recovery and emergency procedures. The
program is design to give the pilot intimate knowledge of the
aircraft and addresses all aspects of flight safety.
EXTERIOR
1,49 m
The flight characteristics of the YUMA are enhanced by an
optimized wing profile and carbon-fiber leading edge slats
(Handley-Page type) that directly adress the requirements of
S.T.O.L. flight. The ability to perform challenging landings in
confined spaces is further enhanced by generous sizing of the
control surfaces which provide exceptional maneuverability
and do not lose control effectiveness at very low airspeeds.
Additionally, the large flaps permit steep final approaches
to facilitate descent over tall obstacles at the edges of an
airfield without wasting valuable field length. The cockpit
layout provides both comfort and unobstructed visibility that
an aircraft of this type must provide whether used for sport
flying or aerial observation.
INSTRUMENTS
1,52 m
The development of the Yuma began in 1994 with the goal of
surpassing the technical and flight characteristics of existing
light S.T.O.L (Short Take-Off & Landing) aircraft. The project
focused on the following design requirements:
- assurance of an aircraft designed and constructed to the
most stringent aeronautical specifications;
- ability to take-off and land from virtually any field having
obstructions or limited space without sacrificing good cruise
speed;
The techniques and materials used throughout the
construction of the YUMA are typical of the certified aircraft
industry.
Wing span
Cabin width
Length
Height
Wheelbase
Wing area
Aspect ratio
Empty weight
Maximum takeoff weight
Wing loading
9,75 m
1,18 m
6,45 m
2,45 m
2,00 m
13,4 m2
6,6
282 kg
450 kg
33,5 kg/m2
PERFORMANCE
ROTAX 912 UL (80 hp)
ROTAX 912 ULS (100 hp)
ROTAX 914 UL (115 hp)
Maximum speed
Cruise speed 75%
Stall speed (without flaps)
Stall speed (with flaps)
Rate of climb
Takeoff distance (with 1 person)
Takeoff distance (full load)
Landing distance
Max ceiling
Fuel capacity
Endurance with max paylod at
cruise speed 75%
175 km/h
150 km/h
55 km/h
50 km/h
6 m/s
40 m
45 m
55 m
5000 m
85 l
5,2 h
185 km/h
160 km/h
55 km/h
50 km/h
8 m/s
30 m
40 m
55 m
5000 m
85 l
4,5 h
195 km/h
170 km/h
55 km/h
50 km/h
10 m/s
30 m
40 m
55 m
7000 m
85 l
4,1 h
YUMA
SEMIFINISHED VERSION
The semifinished YUMA is already structurally assembled:
- The fuselage is comprised of a welded tubular alloy-steel
cockpit structure and riveted aluminum tail cone
(with internal anti-corrosion primer).
- Riveted aluminium-alloy wings, horizontal and vertical
stabilizers.
- All control surfaces and flaps are of aluminum alloy
covered with 90 gr/m2 Dacron fabric.
- Engine mount and wing struts in CroMoly steel,
cockpit door frames in aluminum-alloy.
- Alloy-steel exhaust system.
- Fuel quick drain.
- Battery.
- Polycarbonate side windows, ceiling and windshield.
- Aluminum wing tanks and 5 liter header tank.
- Composite wing tips, stabilizer tips, cowling and internal
panels.
- Blank instrument panel.
- Leaf spring main gear, front fork and wheels complete
with disk brakes.
- Rudder pedals, flap control system and joysticks.
- Control cables, small parts for the complete assembly.
YUMA
ROTAX 912 UL - 912 ULS - 914 UL
- Padded leather seats.
Approximately 200 hours are required to complete
the aircraft. Not included in the kit: engine, propeller,
instruments and paint.
YUMA
SEMIFINISHED
Via Confalonieri 22 - 23894 Cremella (Lecco) Italy
Phone +39 039.9212128 - Fax +39 039.9212130
www.alisport.com - [email protected]
Silent Alisport LLC
Tullahoma Regional Airport - P.O. Box 996 - Tullahoma, TN 37388, USA
Phone +931.455.5994 - Cellular +931.434.3434
www.alisport.com - [email protected]
1006
alisport srl

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