1 engine

Agusta AB.102

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Agusta had gained experience from licenced building of the Agusta/Bell-47. Agusta designed a new fuselage around the Bell-47 that increased its capacity to eight passengers. The first prototype flew on 3 February 1959 and was seen in military colours at the 1959 Paris Airshow. Designed to fill the growing civilian helicopter market, the A.102 sold to several Italian commercial companies, powered by a Pratt & Whitney R-1340 piston engine developing 600hp, mounted in the aft cabin, had a range of 400km and a cruising speed of 160kph.
The name Agusta-Bell was applied because Agusta used in this aircraft a Bell two-blade main rotor system complete with stabilising bar below and at right angles to the rotor blades. In other respects it was of conventional pod and boom configuration, the tail pylon mounting a two-blade anti-torque rotor. Tubular skid landing gear was provided. The forward cabin was furnished to accommodate a pilot and 7/9 passengers. Up to 880kg of freight could be carried internally in an all-cargo role. An electric hoist was also available optionally for use in SAR operations.
The Elivie company, which was already running flights with AB-47J helicopters between Naples and the islands, took delivery of a couple of A.102s in spring 1961, to operate a regular service between the center of Turin and Milan airports. The availability of new turbine-powered helicopters, however, soon rendered the A.102 obsolete.

AB-102
Engine: 1 x Pratt & Whitney R-1340-S1H4 radial, 600 hp / 447kW
Main rotor diameter: 14.5m
Length: 17.92m
Height: 3.23m
Take-off weight: 3025kg
Empty weight: 1810kg
Max speed: 177km/h
Cruising speed: 160km/h
Service ceiling: 3900m
Range: 400km
Crew: 1
Passengers: 7-9

Agrocopteros MXP-740 / ICP MXP-740 Savannah

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In development since 1990, Agrocopteros redesigned and built from scratch modified versions of the Zenair Zodiac CH 601HD and STOL CH 701 kitplanes, designating them MXP-640 and MXP-740.

The 740 features a Mitsubishi auto turbocharger fitted to a Rotax 912, increasing power from 80 hp to 118 hp. Electronically operated full-span flaperons are interlocked with elevator trim, and span 8 ft 8 in with 10 inch chord. They travel 18 deg down and 24 deg up. The vertical tail is a one piece, all moving type. Undercarriage is shock-absorbing spring aluminium.
An Italian distributor in Turin acquired 18 MXP-740s.

The ICP MXP-740 Savannah is a two-seat, single-engine, all metal shoulder-wing microlight airplane with a fixed tricycle undercarriage with steerable nosewheel wheel.

Engine: Rotax 912 turbo, 118 hp
Prop: Ivoprop vp.
Length: 10 ft 7 in.
Cruise: 4000rpm 34 in/ 130 mph.
Cockpit width: 45 in.
Baggage cap: 40 lbs.
Fuel cap: 14 USG usable.
Wing: NACA 65018

Agrocopteros MXP-640

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In development since 1990, Agrocopteros redesigned and built from scratch modified versions of the Zenair Zodiac CH 601HD and STOL CH 701 kitplanes, designating them MXP-640 and MXP-740.
The 640’s primary structure is aluminium alloy extrusions or sheel, with the ribs, frames, extrusions, stringers, rigid hinges, reinforcements and skin panels all sharing the structural load. The wing is a single piece main spar with no sweep, with two fuel tanks. The fuselage is a semi-monocoque with steel firewall, and fibreglass fairings and cowl.
The fixed, tricycle undercarriage employs bungee-cord shock absorbers, and 5.00×5 tyres.

MXP-640T
Engine: Rotax 912 turbo, 118 hp
Prop: Ivoprop vp
Length: 9 ft
Wings: NACA 65018, 12% thickness
Aspect ration: 5.2-1
Fuel cap: 27 USG usable
Empty wt: 660 lb
Mtow: 1300 lb
Load: +5/-4g
Max cruise: 135 mph
Vne: 170 mph
Econ cruise: 120 mph
Range @ 120 mph: 600 mile
Max Maneuver: 120 mph
Max flap ext: 80 mph
Stall: 45 mph
ROC: 1230 fpm @ 95 mph
ROC @ 10,000ft: 870 fpm
TO dist: 250 ft
Ldg dist: 330 ft

Agriplane Condor 2090

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Single seat single engined flex wing aircraft with weight shift control. Rogallo wing with keel pocket. Pilot suspended below wing in trike unit, using bar to control pitch and yaw/roll by altering relative positions of trike unit and wing. Wing braced from above by kingpost and cables, from below by cables; rigid cross tube construction with single surface (33% double surface optional); not enclosing cross tube; pre formed ribs. Undercarriage has three wheels in tricycle formation; rubber suspension on all wheels. Push-right go left nosewheel steering independent from yaw control. Brake on nosewheel. Aluminium tube trike unit, without pod. Engine mounted below wing driving pusher propeller.
Designed by Patrice Renaud with the assistance of M Michelot and C Cardineau, the prototype Agriplane flew for the first time in February 1981, which makes it the first agricultural weight shift microlight in the world. Patrice was the victim of an accident in the course of a flight on another machine which laid him up for a long time, which explains why the machine was shown at the aeronautical and space salon at Le Bourget in June 1981, even though the first Agriplane Condors were not sold until March 1982.
Essentially intended for use as an agricultural tool, this microlight can nevertheless be fitted with a second seat and used as a tandem two seater dual control machine. A kit allows for this dual control adaption. The Condor is supplied with a glass fibre seat with a foam covering which forms the 23.8 US gal (19.8 Imp gal, 90.0 litre) tank for the spray medium. An autonomous hand controlled electric pump supplies the medium to the two spray booms mounted either side of the trike. Three lengths of boom were offered 19.8, 26.6 and 39.5ft (6.0, 9.0 and 12.0 m) fitted together with quick release couplings, which allows their fitment in 3 min. Interchangeable atomisers allow the amount of product sprayed to be varied between 1.0 and 2.0 US gal/acre (0.84.6 Imp gal/acre, 15.30 litre/ hectare).

Engine: Hirth, 46 hp at 7800 rpm.
Toothed¬ belt reduction.
Power per unit area 0.19hp/sq.ft, 2.0hp/sq.m.
Fuel capacity 5.8 US gal, 4.8 Imp gal, 22.0 litre.
Length overall 13.1 ft, 4.0 m.
Height overall 11.6 ft, 3.50 m.
Wing span 32.8 ft, 10.0 m.
Dihedral 4 degs.
Nose angle 135 degs.
Total wing area 248 sq.ft, 23.0 sq.m.
Wing aspect ratio 4.3/1.
Wheel track 5.7ft, 1.70 m.
Nosewheel dia¬meter overall 16 inch, 40 cm.
Main wheels diameter overall 16 inch, 40cm.
Empty weight 298 lb, 135kg.
Max take off weight 696 lb, 315kg.
Payload 398 lb, 180kg.
Max wing loading 2.80 lb/sq.ft, 13.7 kg/sq.m.
Max power loading 15.1 lb/hp, 6.8kg/hp.
Load factors; +5.5, 2.8 ultimate.
Max level speed 47mph, 75kph.
Never exceed speed 53mph, 85kph.
Max cruising speed 40mph, 65kph.
Economic cruising speed 34mph, 55kph.
Stalling speed 23 mph, 38 kph.
Max climb rate at sea level 600 ft/min, 3.0 m/ls.
Best Wide ratio power off 7/1 at 34 mph, 55 kph.
Take off distance 82 ft, 25 m.
Landing distance 50 ft, 15 m.
Range average cruise 68 mile, 110 km.

Ago C.IV

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The C.IV was a two-seat reconnaissance aircraft, with a conventional cross-axle landing gear and tapered biplane wings. Powered by a 220hp Benz Bz.IV engine driving a two-blade propeller fitted with a spinner, armament was a forward-firing Spandau and a rear-mounted Parabellum machine-gun. About 70 production aircraft became operational from early 1917, although large orders had been placed with three manufacturers.

Ago C.I / C.II      

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C.II

Designed by Swiss engineer A. Haefeli (earlier with Farman) the C.I and C.II series of twin-boom reconnaissance biplanes were each armed with one machine-gun in the nose. C.I and C.II land-planes had a four-wheel landing gear under the central two crew nacelle and a tailskid under each boom. Power was provided by a 160hp Mercedes D.III and 150hp Benz III or 220hp Benz Bz.IV pusher engine respectively.

C.Is and C.IIs became operational over the Western Front in the latter half of 1915. Serving just a short span, the C.II performed from 1915 on, replaced by more conventional and modernised types before the end of the war.

The similarly powered C.I-W (one built) and C.II-W (two built) twin-float seaplane versions were operated by the German Navy in a coastal reconnaissance and defence role.

Aerowerke Gustav Otto AGO C.II
Engine: 1 x Benz IV 6-cylinder liquid-cooled inline, 220hp.
Length: 32.28ft (9.84m)
Wingspan: 47.57ft (14.50m)
Height: 10.40ft (3.17m)
Empty Weight: 2,998lbs (1,360kg)
Maximum Take-Off Weight: 4,290lbs (1,946kg)
Maximum Speed: 80mph (128kmh; 69kts)
Maximum Range: 360miles (580km)
Service Ceiling: 14,764ft (4,500m)
Armament: 1 x 7.92 Parabellum machine gun
Accommodation: 2

Affordable Aircraft Affordaplane

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The Affordaplane was introduced in 2001 as a simple to build, affordable ultralight. Featuring three axis control, full span ailerons, and classic lines, the Affordaplane can be built in 250 hours with no welding involved. 2009 price was US$3000. Designed by Dave Edwards this aircraft is for the first time builder and plans are available.

Length: 17’3”
Height 5’0”
Wingspan 27’6”
Wing Area 117 sq. ft
Empty Weight: 115 kg / 254 lbs
MTOW: 245 kg / 540 lbs
Stall: 23 kt / 27 mph / 43 kmh
Cruise: 56 kt / 65 mph / 105 kmh
VNE: 74 kt / 85 mph / 137 kmh