André Starck continued construction of a range of eight aircraft after 1945: AS-37, AS-57/3, AS-57 / 4, AS-57/5, AS-70 “Jac” AS-71 AS-80 “Holiday” and AS-90 “New Look”.
The AS.80 was a tandem two-seat cabin monoplane of wooden construction with fabric covering, designed primarily for construction from kits of parts by amateurs.
Engine: 75 hp Regnier 4D2 Max speed: 98 mph Cruise: 88 mph ROC: 590 fpm Range: 200 mi Empty weight: 720 lb Loaded weight: 1210 lb Wingspan: 32 ft 10 in Length: 21 ft 7.5 in Height: 6 ft 3 in
First flown on 23 May 1945, the AS-70 was developed during 1945 as a single-seat light low-wing monoplane aircraft to serve the early postwar needs of French private pilots and aero clubs. It is of mixed welded steel tube and wooden construction with fabric covering, and is fully aerobatic.
A small series of 19 Jacs was constructed by Avions Starck. These were fitted with a range of engines with power outputs of between 45 to 65 hp (34 to 48 kW). Different designations were given to aircraft powered by the various engines.
AS.71 Jac
The Jac proved to be a popular aircraft with private pilots and aero clubs and four examples remained in service in 2009.
Starck AS-70
Variants:
AS-70 fitted with 45 hp (34 kW) Salmson 9 Adb radial engine
AS-71 fitted with 65 hp (48 kW) Walter Mikron II engine
AS-72 fitted with Salmson 9 ADr radial engine
AS-72/1 fitted with a Percy II engine.
AS-75 fitted with 65 hp (48 kW) Continental A65-8S engine
Specifications:
Starck AS-70 Engine: Salmson 9Adb, 45 hp Wingspan: 7.40 m / 24 ft 3 in Length: 5.33m / 17 ft 7 in Wing area: 8 sq.m / 86 sq.ft Empty weight: 202 kg / 467 lb Maximum weight: 300 Kg / 705 lb Max speed: 115 mph Cruise: 185 km / h / 104 mph Ceiling: 6200 m Range: 420 km / 260 mi
Starck AS-75 Engine: 1 × Continental A65-8S, 65 hp (48 kW) Length: 17 ft 7 in (5.36 m) Wingspan: 24 ft 3 in (7.39 m) Wing area: 86 sq ft (8.0 m2) Height: 5 ft 3 in (1.60 m) Empty weight: 435 lb (197 kg) Gross weight: 698 lb (317 kg) Maximum speed: 126 mph (203 km/h; 109 kn) Cruise speed: 115 mph (100 kn; 185 km/h) Range: 320 mi (278 nmi; 515 km) Crew: one Capacity: one passenger
André Starck continued construction of a range of eight aircraft after 1945: AS-37, AS-57/3, AS-57 / 4, AS-57/5, AS-70 “Jac” AS-71 AS-80 “Holiday” and AS-90 “New Look”.
AS-57/3 Engine: 95 hp Regnier 4-EO Wingspan: 28 ft Wing area: 118 sq.ft Length: 21 ft 2 in Empty weight: 683 lb Loaded weight: 1322 lb Max speed: 123 mph Cruise: 115 mph Ceiling: 19,000 ft Range: 497 mi
Similar to the Tristar except with a conventional three-axis aerodynamic control system, nosewheel has suspension and a nosewheel brake. The prototype of the TX 1000 had its first public showing at Sun’n’Fun in March 1983 at Lakeland, Florida. Described by Dick Turner as a development of the Tristar, this newcomer uses the same wing with 5 degrees of dihedral and double skin over 30% of the chord. However, it uses a different engine, a Rotax unit.
It also has a considerably reinforced structure, the leading edge spars being 2 inch (51 mm) diameter, and the compression tubes and trailing edge spars 1.5 inch (38mm). There are other differences from the Tristar too: the horizontal tail is stiffened in flight by V struts and on the ground by stainless steel cables instead of just the cables of its predecessor. On this model a braked steerable nosewheel is standard. There is a black epoxy coating on all exposed airframe parts, bonded to the tubing and baked to a glass finish.
The TX 1000 was sold as a kit requiring 40 h for assembly for $5195 in 1983, options being electric start and a hand deployed parachute.
Manufactured by Spectrum Aircraft Inc.
Engine: Rotax 377, 34 hp at 6500 rpm Propeller diameter and pitch 54 x 27 inch, 1.37 x 0.69 m Belt reduction, ratio 2.1/1 Max static thrust 250 lb, 113 kg Power per unit area 0.20 hp/sq.ft, 2.2 hp/sq.m Fuel capacity 4.5 US gal, 3.8 Imp gal, 17.0 litre Length overall 15.0ft, 4.57m Height overall 9.0 ft, 2.74 m Wing span 33.0 ft, 10.05 m Constant chord 5.0ft, 1.52m Dihedral 5 deg Sweepback 0 deg Total wing area 165 sq.ft, 15.3 sq.m Wing aspect ratio 6.6/1 Nosewheel diameter overall 16 inch, 41 cm Main wheels diameter overall 16 inch, 41 cm Fin height 8.0 ft, 2.44 m Total elevator area 25.0sq.ft, 2.32 sq.m Empty weight 252 lb, 114kg Max take off weight 502 lb, 228 kg Payload 250 lb, 113 kg Max wing loading 3.14 lb/sq.ft, 14.8 kg/sq.m Max power loading 14.8 1b/hp, 6.7kg/hp Load factors; +5.8, 3.6 ultimate Max level speed 60 mph, 97 kph Never exceed speed 75 mph, 121 kph Max cruising speed 45 mph, 72 kph Economic cruising speed 32 mph, 51 kph Stalling speed 21 mph, 34 kph Max climb rate at sea level 800 ft/min, 4.1 m/s Min sink rate 320 ft/min at 30 mph, 1.6 m/s at 48 kph Best glide ratio with power off 7.14 at 32mph, 51 kph Take off distance 50 ft, 15 m Landing distance 50 ft, 15 m Service ceiling 12,000 ft, 3660 m Range at average cruising speed 90 mile, 145 km
The aircraft was designed before the US FAR 103 Ultralight Vehicles rules were brought into effect, but all models comply with them anyway, including the category’s maximum empty weight of 254 lb (115 kg). The Tristar, for instance, has a standard empty weight of 220 lb (100 kg). The line of aircraft all feature a cable-braced high-wing, a single-seat, open cockpit, tricycle landing gear and a single engine in pusher configuration.
The aircraft is made from bolted-together aluminium tubing, with the flying surfaces covered in Dacron sailcloth. Its 33 ft (10.1 m) span wing is cable-braced from a single element kingpost. The landing gear features a steerable nose wheel with a bicycle-style rim brake. The powerplant is mounted underneath the wing and drives a pusher propeller.
Single seat single engined high wing mono¬plane with conventional three axis control (two axis optional). Wing has unswept leading and trailing edges, and constant chord; cruci¬form tail. Pitch control by elevator on tail; yaw control by fully flying rudder; roll control by spoilerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile; 30% double surface. Undercarriage has three wheels in tricycle formation; with tailskid; glass fibre suspension on main wheels. Push right go¬-right nosewheel steering connected to yaw control. No brakes. Aluminium tube framework, without pod. Engine mounted below wing driving pusher propeller.
The Tristar also put in its appearance in 1982 but it is not just a three axis version of the Starfire with spoiler¬ons and elevators added to the rudder of the earlier model. The framework of the Tristar is considerably changed from that of the Starfire and the manufacturer has obviously made an important design effort, not being purely content to develop a three axis machine directly from a hybrid. The wing characteris¬tics, for example, have been considerably altered by double surfacing the first third of the chord. In fact, the Tristar does not have to be bought in three axis form as the manufac¬turer offers a two axis version as a no cost option.
The Tristar model took 25 hours to build from the factory-supplied assembly kit. Sold as a kit requiring 25 h for completion at a price of $4750 in 1983, the Tristar in standard form uses a Cuyuna 430R 30hp engine, in which form we detail it below. However, for $100 less it can befitted with the Cuyuna 215R 20hp unit. Other options include storage covers and wheel fairings ($150).
Tristar Model designed in 1980, with a conventional three-axis aerodynamic control system, using a side stick and spoilers for roll control. Revised fuselage for new control system. The standard engine supplied was the 30 hp (22 kW) Cuyuna 430R.
SC-1000 Improved model
AC-2000 Improved model introduced in 1984.
Tristar Engine: Cuyuna 430R, 30 hp (22 kW) at 5500 rpm Propeller diameter and pitch 52 x 27 inch, 1.32 x 0.69 m Belt reduction, ratio 2.0/1 Power per unit area 0.18 hp/sq.ft, 2.0hp/sq.m Fuel capacity 2.5 US gal, 2.1 Imp gal, 9.5 litre main tank; 2.5 US gal, 2.1 Imp gal, 9.5 litre res (opt) Length overall 15.0ft, 4.57m Height overall 9.0 ft, 2.74 m Wing span 33.0 ft, 10.05 m Constant chord 5.0ft, 1.52m Dihedral 5 deg Sweepback 0 deg Total wing area 165 sq.ft, 15.3 sq.m Wing aspect ratio 6.6/1 Nosewheel diameter overall 16 inch, 41 cm Main wheels diameter overall 16 inch, 41 cm Empty weight 220 lb, 100kg Max take off weight 470 lb, 213kg Payload 250 lb, 113kg Max wing loading 2.85 lb/sq.ft, 13.9 kg/sq.m Max power loading 15.7 lb/hp, 7.1kg/hp Load factors; +5.0, 3.0 ultimate Max level speed 55mph, 88kph, 48 kt Never exceed speed 55mph, 88 kph Max cruising speed 38 mph, 61 kph, 33 kt Economic cruising speed 35mph, 56kph Stalling speed 21 mph, 34 kph, 18 kt Max climb rate at sea level 750 ft/min, 3.8 m/s Min sink rate 350ft/min, 1.8m/s Best glide ratio with power off 7/1 Take off distance 75 ft, 23 m (on gravel) Landing distance 100ft, 30m (on gravel) Service ceiling 10,000ft, 3050m Range at average cruising speed 60 mile, 97 km Crew: one
The aircraft was designed before the US FAR 103 Ultralight Vehicles rules were brought into effect, but all models comply with them anyway, including the category’s maximum empty weight of 254 lb (115 kg). The line of aircraft all feature a cable-braced high-wing, a single-seat, open cockpit, tricycle landing gear and a single engine in pusher configuration.
The Star Flight Starfire is the first aircraft in a large family of American ultralight aircraft that was designed by Dick Turner and produced by Star Flight Manufacturing, introduced in 1979. The aircraft were all supplied as kits for amateur construction.
The aircraft is made from bolted-together aluminium tubing, with the flying surfaces covered in Dacron sailcloth. Its 33 ft (10.1 m) span wing is cable-braced from a single element kingpost. The landing gear features a steerable nose wheel with a bicycle-style rim brake. The powerplant is mounted underneath the wing and drives a pusher propeller. Single seat single engined high wing mono¬plane with hybrid control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by weight¬shift; yaw control by fully flying rudder; no separate roll control; control inputs through weight shift for pitch/yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile; single surface.
Undercarriage has three wheels in tricycle formation; with additional tailskid; glass fibre suspen¬sion on main wheels. No ground steering. No brakes. Aluminium tube framework, without pod. Engine mounted below wing driving pusher propeller.
Up to the beginning of 1983 the Star Flight Aircraft company belong¬ing to Dick Turner was called Starflight Manufacturing. His basic model, the Starfire made its appearance in 1982 and was sold as a kit requiring 16 h for assembly at a price of $3995, with options including wheel fairing for $150.
However, in common with other manufac¬turers, Dick Turner has found that the market is moving away from hybrid control to stick operated machines. As a result, the Starfire was discontinued in 1983.
Engine: Cuyuna 215R engine Max power 20 hp at 6000 rpm Propeller diameter and pitch 52 x 24 inch, 1.32 x 0.60 in Belt reduction, ratio 2.4/1 Power per unit area 0.12 hp/sq.ft, 1.3 hp/sq.m Fuel capacity 2.5 US gal, 2.1 Imp gal, 9.5 litre Length overall 9.0ft, 2.74m Height overall 16.0ft, 4.87m Wing span 33.0ft, 10.05m Constant chord 5.0ft, 1.52m Dihedral 5 deg Sweepback 0 deg Total wing area 165 sq.ft, 15.3 sq.m Wing aspect ratio 6.6/1 Nosewheel diameter overall 16 inch, 41 cm Main wheels diameter overall 16 inch, 41 cm Empty weight 175 lb, 79kg Max take off weight 475 lb, 215 kg Payload 300 lb, 136 kg Max wing loading 2.87 lb/sq.ft, 14.0 kg/sq.m Max power loading 23.8 lb/hp, 10.83kg/hp Max level speed 42mph, 68kph Never exceed speed 55mph, 88kph Max cruising speed 30mph, 48kph Stalling speed 19 mph, 31 kph Max climb rate at sea level 450 ft/min, 2.3 m/s Best glide ratio with power off 6/1 Take off distance 100 ft, 30 m Landing distance 50 ft, 15 m
The Starfire Firebolt, sometimes called the Starfire Firebolt Convertible, due to its removable canopy, is an American homebuilt aerobatic biplane that was designed by G. H. “Mac” McKenzie and produced by Starfire Aviation of Tempe, Arizona. When it was available the aircraft was supplied in the form of plans for amateur construction, with some pre-fabricated parts available.
Developed from the Steen Skybolt and first flying on 15 May 1987, at least nine were built. Plans were sold for US$275.00 in 1998.
Engine: Lycoming IO-540-K1A5, 340 hp Speed max: 214 mph Cruise: 202 mph Range: 600 sm Stall: 61 mph ROC: 4000 fpm Take-off dist: 400 ft Landing dist: 850 ft Service ceiling: 18,500 ft Fuel cap: 39 USG Weight empty: 1354 lbs Gross: 2000 lbs Height: 7.6 ft Length: 21 ft Wing span: 24 ft Wing area: 150 sq.ft Seats: 2 Landing gear: tail wheel
A single seat open frame helicopter first flown on 16 October 1990. Aluminium tube frame with all parts bolted or pop riveted together. Engine: 64-110 hp Rotax or Hirth.
Engine: 88 hp Max speed: 95 mph Cruise speed: 65 mph Range: 105 sm ROC: 1000 fpm Service ceiling: 9,000 ft Fuel cap: 8 USG Empty wt: 430 lbs Gross wt: 895 lbs Height: 7.33 ft Length: 13.5 ft Disk span: 20 ft Disk area: 314 sq.ft Seats: 1
The Star Aircraft division of Phillips Petroleum was formed at Bartlesville, Oklahoma in 1928. Designers E A “Gus” Riggs and William “Billy” Parker prepared plans for a two-passenger high-wing light private owner aircraft intended for the lower cost end of the market. The advertised cost was $3,450 with a 90hp Lambert R-266 engine. They were also advertised with a 60hp LeBlond or 75hp Velie engine for $2,985. Three Cavalier A planes were delivered in 1928.
The Cavalier B (ATC 138) followed in 1929 fitted with a lower powered 55 hp Velie M-5 engine and 15 examples were sold at $2,895 to owners of more modest means. Some were fitted with 80hp Genet and 90hp Lambert R-266 engines. The fifteen included NC24B, NC263K, NC331H, NC350M and 351M, NC451, NC453, NC450, NC941E, NC960H, NC990H, NC7239 and N7249.
Cavalier B
A single example of the Cavalier C (ATC 255) followed. The Cavalier C NC993H was powered by a 60hp LeBlond 5D engine for $2,985.
Star Cavalier C NC993H
Two examples of the 1929 Cavalier D (ATC 2-191) were built, powered by 80hp Genet engines.
Star Cavalier E NC71W
The next to secure modest success was the Cavalier E (ATC 321) of 1930 which had a 90 h.p. Lambert R-266 and was fitted with a taller, more angular, tail fin. Priced at $3,450 thirteen were sold (NC9E, NC13E, NC71W, NC350V, NC397V, NC636W, NC678W, NC980N, NC10359, NC10535, NC10583, NC10585, and NC11007).
Star Cavalier E Wing antennae NC10359
The last of the Cavalier series was the single 1930 F model N69W with a Warner Jr engine.
The several Cavalier models served private owners in the touring role until the curtailment of civil flying in the USA in late 1941. Five Cavaliers remain on the U.S. civil aircraft register in mid-2009. Cavalier B N14860 of 1930 was on public display, in airworthy condition, at the Historic Aircraft Restoration Museum at Dauster Field, Creve Coeur, Missouri near St Louis.
Cavalier B Engine: 1 × Velie M-5, 55 hp (41 kW) Wingspan: 31 ft 6 in (9.60 m) Wing profile: Clark Y Length: 19 ft 11 in (6.07 m) Useful lift: 538 lb ( kg) Maximum speed: 100 mph (161 km/h) Cruise speed: 85 mph (137 km/h) Stall speed: 40 mph (64 km/h) Range: 500 miles (800 km) Crew: 1 Capacity: 1 passenger
Cavalier B Engine: 80 h.p. Armstrong Siddeley Genet Seats: 2
Cavalier B Engine: 90 h.p. Lambert R-266 Seats: 2
Cavalier C Engine: 60 h.p. LeBlond 5D Seats: 2
Cavalier D Engine: 60 h.p LeBlond. Seats: 2
Cavalier D Engine: 80hp Genet Seats: 2
Cavalier E Engine: 90 h.p. Lambert R-266 Length: 19’8″ Useful load: 550 lb Max speed: 105 mph Cruise: 87 mph Stall: 38 mph Range: 360 mi Seats: 2
All Aero 