AP 68 TP – 300 SpartacusI-VULE S.N. 8011

Presentation

All reasonable care has been taken by VULCANAIR to ensure the accuracy of the information contained in the present document. However, the material presented is provided to acquaint you with the general characteristics of our products; it is not an offer and does not constitute a commitment, a warranty, or a representation.No liability is accepted for inaccuracies or omissions or any direct, indirect, special or consequential damages, or other damages whatsoever resulting from the use of any information contained in this document. Duplication of such document is authorised for private and informational purposes only, and any other duplication or use thereof is expressly prohibited.

NOTE: ALL DATA IN THIS PRESENTATION FOR GENERAL INFORMATIONAL PURPOSES ONLY, SUBJECT TO VERIFICATION BY CUSTOMER AT AIRCRAFT

INSPECTION

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AP 68 TP – 300 SpartacusAirframe S/N 8011 total time approx 1839 hrs.

Left engine total time 1839 hrs. Right engine total time 1839 hrs.Left propeller total time 985 hrs. Right propeller total time 985 hrs

Avionics: Two (2) Garmin GNS430 NEW units installed!One (1) Garmin GMA340 with Pilot/co-pilot and 4 pax NEW unit installed!One (1) Garmin GTX 327 NEW unit installed!One (1) ADF KR87One (1) DME KN63 One (1) RMI 229 One (1) 2nd VOR KI 209A One (1) KCS55A One (1) A/P (autopilot) KAP 150 with Kg258 One (1) Encoding Altimeter KEA130 One (1) ELT Narco 910AOne (1) Weather Radar Sperry Primus

Other main optional equipment installed on aircraft: BF Goodrich Pneumatic De-Icing on wings, tail surfaceEngine inlet de-icingLeather seats, rehuphosltered with new Muirhead leatherNew carpeting throughoutNew Paint Job2 New Altimeters will be installed for IFR OPERATION

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Main FeaturesWind tunnel-tested Aerodynamic Design

Clean High-wing configurationLow drag fixed landing gearSimple un-pressurized structure

Well-proven, Efficient Power Plants 2 x Rolls Royce 250 B17C Turbines2 x Hartzell Feathering and Reversible Pitch Propellers

Simple Unsophisticated SystemsTwo Integral fuel tanks systems in each wingCable and rod operated Flight Controls, electrically operated FlapsPneumatic Boot De-Icing for wing and tail. Thermo-electric Anti-Icing for PropellersElectrical System consists of 3 Bus Bars fed by 2 Starter/Generators and 1 Battery Hydraulically operated brakes

Avionics and InstrumentationStandard U.S. General Aviation Instrumentation is installedA choice of «state-of-the-art» avionics is offered

ALL OF THESE FEATURES ADD UP TO EXCEPTIONALLY LOW OPERATING COSTS AND HIGH RELIABILITY FOR THE SPARTACUS

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Cockpit

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Three View

Clean high wing configurationExcellent visibilityThree doors for easy access to cabin

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Three View

Clean high wing configurationExcellent visibilityThree doors for easy access to cabin

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GeneralThe Spartacus is the Vulcanair solution to the problems of those aircraft operators

wishing to step up to turbine aircraft at the least cost and, at the same time, have a need of a genuine multipurpose and economic aircraft.

Structural simplicity, aerodynamic efficiency and lack of complicated systems are the principal characteristics of the Spartacus which benefits from the service experience throughout the world of more than 400 Vulcanair-Partenavia P68s from which the aircraft is derived.

Landing GearThe fixed landing gear is particularly suitable for semi prepared strips and hard working conditions, and is an important factor in reducing maintenance costs.

Power PlantThe Spartacus is powered by two Rolls Royce 250 B17C turboprop engines flat-rated to 328 SHP.Each engine drives a metal Hartzell HC-B3TF-7AJT 101 73F-21 R full and automatic feathering, three blades, reversible pitch propeller.

Fuel SystemIndependent wing tanks of 386 lit (102 USG) capacity, one per wing, and one 38 lit (10 USG) additional tank per nacelle, feed each power plant and may be interconnected for cross feed operations.

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General cont.Electrical System

Primary electrical power is supplied by two 50A 28 V/DC Starter/generators which operate two bus bars in parallel or isolated. A battery of sufficient capacity for engine starting purposes and a DC/AC inverter unit supply 28 V/DC and 115 V/AC power, assuring electrical power in case of loss of all the primary power sources. A voltage regulator for each bus bar provides under voltage, over voltage and reverse current.

Flight Control SystemThe flight controls are of the mechanical type and are operated by cables and push-rods.Trim tabs are fitted for control about all three axes. All tabs are operated by hand-wheels. The flaps are electrically operated.

Anti-icing SystemThe anti-icing system is of the pneumatic boot type for both the wings and tail surfaces and of the electro-thermal type for the propellers. The engine air intake de-icing is achieved by means of electrical resistances.

Cabin Heating SystemCabin heating is achieved by mixing ram air, heated by a muff located around the hottest zone of the engine, with fresh air to get the desired cabin temperature.

Avionics Electrical power and panel space are available to accommodate a choice of avionic equipment to the highest standards for world-wide all weather operations.

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Civil Version The Spartacus has been designed to provide the most cost-effective

operations for air taxi, charter, executive-VIP, aero medical transport, aero photogrammetry, training, commuter and light cargo transport.

The pilot enters the cockpit through the pilot door on the starboard side; passengers enter through a door on the left side and through the large rear door on the right hand side which also provides access to the baggage compartment behind the rear seats.The large dimensions of the rear door coupled with the flat cabin floor, make the aircraft very suitable for the transport of light freight and aero medical transport.The aircraft is approved for flight operations with the rear door removedfor parachuting, etc.

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Basic DataLength 32.48 ft 9.90 m

Wing span 39.37 ft 12.00 m

Height 11.98 ft 3.65 m

Wing area 200.21 sq. ft 18.60 sq. m

I-VULE Empty weight 3862 lb 1752 kg

Max ramp weight 5787 lb 2625 kg

Max TO. weight 5732 lb 2600 kg

Max landing weight 5445 lb 2470 kg

Max 0-fuel 5300 lb 2404 kg

Passengers 7/8 + 1 pilot

Engines Allison 250 B17C (328 SHP ea.)

Propellers Hartzell HC-B3TF-7A/T 101 73F-21 R

diameter 80” - 2.032 m

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Performance Data

Take-off distance (to 50 ft obstacle - ISA) 1267 ft 386 m

Rate of climb (2 engines S.L.) 2057 ft/min 10.45 m/s

Service ceiling 25000 ft 7620 m

Service ceiling (1 engine) 14000 ft 4270 m

Max speed at 12000 ft 209 ktas 387 km/h

Long range cruise speed at 12000 ft 180 ktas 333 km/h

Stalling speed (clean conf.) 75 ktas 139 km/h

Stalling speed (landing cent.) 65 ktas 120 km/h

Landing distance from 50 ft obstacle (S.L. ISA) 1405 ft 428 m

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Spartacus Performance Data

Outstanding one-engine out performance assure an high degree of safety.Superior take-off and landing performance assure the safest utilization for all missions.

Take-off distance (to 50 ft obstacle - ISA) 1267 ft 386 m Rate of climb (2 engines s.l.) 2057 ft/min 10.45 m/s Rate of climb (1 engine s.l.) 520 ft/min 2.65 m/s Service ceiling 25000 ft 7620 m Service ceiling (1 engine) 15000 ft 4572 m Max cruise speed at 10000 ft 210 KTAS 389 km/h Long range cruise speed at 12000 ft 165 KTAS 306 km/h Stall speed (flaps up) 75 KTAS 139 km/h Stall speed (flaps down) 65 KTAS 120 km/h Landing distance from 50 ft obstacle (s.l. ISA) 1405 ft 428 m

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Performance DataMax Rate of Climb

Both Engines OperatingRate of Climb

One Engine Inoperative

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Performance DataTake-off Distance Landing Distance

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Performance DataBlock Fuel - Block Time

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Standard Configuration7 + 1 seats36" pitch

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Cargo Configuration

135 cu. ft. of freight compartment, separated from the cockpit

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Power Plant

Each engine drives a metal Hartzell HC-B3TF-7AJT 101 73F-21 R full and automatic feathering, three blades, reversible pitch propeller.

The Spartacus is powered by two Rolls Royce 250 B17C turboprop engines flat-rated to 328 SHP.

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Engine Support

Rolls Royce gas turbine engine division assures a worldwide network of authorized service centres for the most reliable and complete support of the 250 B17C engine.

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Maintenance

The design philosophy aims at the ease of maintenance at low cost and this achieved in the following manner:

Systems simplicityExceptionally easy access to the primary structures, systems, and instrumentationThe high-wing configuration reduces dust and foreign object ingestion into the engine and damages to the propeller

A further major cost saving is achieved through the use of a maintenance free steel spring landing gearRolls Royce engines enjoy 3,500 hrs. TBO:

twice the TBO of a piston engineEngine flat-rating means low operating stress levels and yields long engine life Hartzell propellers have 1,500 hrs. TBO50-hrs. and 100-hrs. inspection takes only 6 and 10 man-hours respectively

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PICTURES OF S.N. 8011 REG. I-VULE