AP 68 TP – 300 Spartacus I-VULE S.N. 8011

1 AP 68 TP 300 SpartacusI- vule 8011 PresentationAll 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 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 : ALL DATA IN THIS PRESENTATION FOR GENERAL INFORMATIONAL PURPOSES ONLY, SUBJECT TO VERIFICATION BY CUSTOMER AT AIRCRAFT INSPECTION2AP 68 TP 300 SpartacusAirframe S/N 8011 total time approx 1839 hrs. Left engine total time 1839 hrs.

2 Right engine total time 1839 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 paxNEW unit installed!One (1) Garmin GTX 327 NEW unit installed!One (1) ADF KR87 One (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 910 AOne (1) Weather Radar Sperry PrimusOther 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 OPERATION3 Main FeaturesWind tunnel-tested Aerodynamic Design4 Clean High-wing configuration4 Low drag fixed landing gear4 Simple un-pressurized structure Well-proven, Efficient Power Plants 42 x Rolls Royce 250 B17C Turbines42 x Hartzell Feathering and Reversible Pitch PropellersSimple Unsophisticated Systems4 Two Integral fuel tanks systems in each wing4 Cable and rod operated Flight Controls, electrically operated Flaps4 Pneumatic Boot De-Icing for wing and tail.

3 Thermo-electric Anti-Icing for Propellers4 Electrical System consists of 3 Bus Bars fed by 2 Starter/Generators and 1 Battery 4 Hydraulically operated brakesAvionics and Instrumentation4 Standard General Aviation Instrumentation is installed4A choice of state-of-the-art avionics is offeredALL OF THESE FEATURES ADD UP TO EXCEPTIONALLY LOW OPERATING COSTS AND HIGH RELIABILITY FOR THE Spartacus 4 Cockpit5 Three View4 Clean high wing configuration4 Excellent visibility4 Three doors for easy access to cabin6 Three View4 Clean high wing configuration4 Excellent visibility4 Three doors for easy access to cabin7 GeneralThe Spartacusis 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 simplicity, aerodynamic efficiency and lack of complicated systems are the principal characteristics of the Spartacuswhich benefits from the service experience throughout the world of more than 400 Vulcanair-Partenavia P68s from which the aircraft is derived.

4 Landing Gear4 The fixed landing gear is particularly suitable for semi prepared strips and hard working conditions, and is an important factor in reducing maintenance costs. Power Plant4 The Spartacus is powered by two Rolls Royce 250 B17C turboprop engines flat-rated to 328 engine drives a metal Hartzell HC-B3TF-7 AJT 101 73F-21 R full and automatic feathering, three blades, reversible pitch propeller. Fuel System4 Independent 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. 8 General System4 Primary electrical power is supplied by two50A 28 V/DC Starter/generators which operate two bus bars in parallel or isolated. 4A 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.

5 4A voltage regulator for each bus bar provides under voltage, over voltage and reverse current. Flight Control System4 The flight controls are of the mechanical type and are operated by cables and tabs are fitted for control about all three axes. All tabs are operated by hand-wheels. 4 The flaps are electrically operated. Anti-icing System4 The 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. 4 The engine air intake de-icing is achieved by means of electrical resistances. Cabin Heating System4 Cabin 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 4 Electrical power and panel space are available to accommodate a choice of avionic equipment to the highest standards for world-wide all weather operations. 9 Civil Version The Spartacushas 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 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 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 aircraft is approved for flight operations with the rear door removedfor parachuting, etc.

6 10 Basic DataLength ft m Wing span ft m Height ft m Wing area sq. ft 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 Rdiameter 80 - m 11 Performance Data Take-off distance (to 50 ft obstacle - ISA) 1267 ft 386 m Rate of climb (2 engines ) 2057 ft/min 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 ( ISA) 1405 ft 428 m 12 Spartacus Performance Data4 Outstanding one-engine out performance assure an high degree of take-off and landing performance assure the safest utilization for all missions.

7 Take-off distance (to 50 ft obstacle - ISA) 1267 ft 386 m Rate of climb (2 engines ) 2057 ft/min m/s Rate of climb (1 engine ) 520 ft/min 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 ( ISA) 1405 ft 428 m 13 Performance Data4 Max Rate of Climb 4 Both Engines Operating4 Rate of Climb 4 One Engine Inoperative14 Performance Data4 Take-off Distance4 Landing Distance15 Performance Data4 Block Fuel - Block Time16 Standard Configuration47 + 1 seats436" pitch17 Cargo Configuration4135 cu. ft. of freight compartment, separated from the cockpit18 Power Plant4 Each engine drives a metal Hartzell HC-B3TF-7 AJT 101 73F-21 R full and automatic feathering, three blades, reversible pitch Spartacus is powered by two Rolls Royce 250 B17C turboprop engines flat-rated to 328 Support4 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 design philosophy aims at the ease of maintenance at low cost and this achieved in the following manner:4 Systems simplicity4 Exceptionally easy access to the primary structures, systems, and instrumentation4 The high-wing configuration reduces dust and foreign object ingestion into the engine and damages to the propeller4A further major cost saving is achieved through the use of a maintenance free steel spring landing gear4 Rolls Royce engines enjoy 3,500 hrs.

8 TBO:4twice the TBO of a piston engine4 Engine flat-rating means low operating stress levels and yields long engine life 4 Hartzell propellers have 1,500 hrs. TBO450-hrs. and 100-hrs. inspection takes only 6 and 10 man-hours respectively21 PICTURES OF 8011 REG. I-VULE