TYPE: Sidebyside kitbuilt
PROGRAMME: Designed by Arlington Aircraft Developments and produced until 2000 by StoddardHamilton. Prototype (N824G) first flew 29 November 1994; deliveres of kits started 1995. Over 1,400 hours flown by December 1998. Prototype converted to tailwheel configuration and then back to tricycle. Chosen by EAA as flagship aircraft for Young Eagle junior pilot scheme; first customerbuilt aircraft completed in July 1996. Early examples had a 93 kW (125 hp) Teledyne Continental IO240. "Jumpstart" kits introduced in 2003, reducing build time by estimated 400 hours. FAA certified version being built in Germany as OMF Symphony. Fourseat, Four Winds versions produced in US.
CURRENT VERSIONS: Glastar: Basic model; as described.
Sportsman 2+2: Introduced mid2003 in anticipation of US Sport Pilot legislation; strengthened wings, saftey cage and landing gear. First kit delivered October 2003 to builder in New Hampshire.
CUSTOMERS: Over 900 kits sold in 16 countries up to October 2002; over 300 flying by February 2002. Total of 205 registered in USA alone by December 2001 increasing to 229 in October 2002.
COSTS: Glastar US$24,705; Sportsman 2+2 US$31,950 per kit, excluding engine, instruments, upholstery and paint (2003).
DESIGN FEATURES: Conceived as inexpensive twoseat personal lightplane with wide performance envelope. Convertible landing gear, float compatible. Wings fold (oneperson, threeminute task) and horizontal tail surfaces removable for compact hangarage or for trailer mounting. Quoted build time 1,500 to 2,000 hours. "Jumpstart" options introduced in November 1998 to reduce time by half; wing kits for this option are assembled in the Czech Republic.
Braced, high wing of constant chord, unswept. Tailplane has root extensions; tail, sweptback fin. Wing section LS(I)0413.
FLYING CONTROLS: Conventional and manual. Frise ailerons; Fowler flaps. Elevator tab for pitch trim. Groundadjustable tab on ailerons. Threeposition flaps: 0,20 and 40^{0}. Vortex generators added to wings in front of ailerons and at wingroots, and root strakes to horizontal stabiliser. Optional electric elevator trim.
STRUCTURE: Fuselage construction of GFRP with 4130 steel tube frame surrounding cockpit section. Wings and tail surfaces of 2024T3 aluminium. Twospar wings have six full ribs per side, plus stiffeners.
LANDING GEAR: Fixed nosewheel type with spats; steerable tailwheel or Aerocet 2200, Wipline, Bilmar and Montana float versions; no differences in airframe among landing gear alternatives. Tailwheel (15 cm; 6 in tyre) conversion effected in 3 hours; choice of three mainwheel sizes: 5.005 (with speed fairings), 6.006 and 8.006. Optional Scott 3200 20 cm (8 in) tailwheel with larger mainwheels.
POWER PLANT: Glastar: One 119 kW (160hp) Textron Lycoming O320D1F flatfour, driving a Sensenich fixedpitch or Hartzell constantspeed twoblade propeller: or 112 kW (150hp) 0320E1A and 134kW (180 hp) 0320A1A; power plants in the range 93168 kW (125225 hp) are in use with around 100 aircraft fitted with Subaru 2.2 and 2.5 litre motorcar engine conversions. Usable fuel capacity 104 litres (27.6 US gallons; 23.0 Imp gallons). Optional 66 litre (17.5 US gallon; 14.6 Imp gallon) auxiliary tank.
Sportsman 2+2: Prototype has one 134 kW (180 hp) Textron Lycoming 0360 engine driving twoblade Hartzell constantspeed propeller. Usable fuel capacity 114 litres (30.0 US gallons; 25.0 Imp gallons); can be increased by optional auxiliary tanks to 189 litres (50.0 US gallons; 41.6 Imp gallons).
ACCOMMODATION: Two persons side by side; seats adjust for pilot heights between 1.52 and 1.98 m (5 ft 0 in and 6 ft 6 in). Door each side. Baggage compartment behind crew with separate baggage door on port side.
SYSTEMS: Electrical system: 12 V 30 Ah battery; alternator fit appropriate to engine.
AVIONICS: To customer's specification.
DIMENSIONS, EXTERNAL (A: Glastar; B: Sportsman):  
Wing span: both  10.67 m (35 ft 0 in) 
Wing chord, constant: both  1.12 m (3 ft 8 in) 
Wing aspect ratio: A  9.6 
B  9.4 
Length: fuselage: A  6.78 m (22 ft 3 in) 
overall, Lycoming O320  6.95 m (22 ft 9^{1}/_{2} in) 
wings folded  7.47 m (24 ft 6 in) 
B  7.01 m (23 ft 0 in) 
wings folded  7.52 m (24 ft 8 in) 
Height overall: tricycle: A  2.77 m (9 ft 1 in) 
B  2.84 m (9 ft 4 in) 
tailwheel: A, B  2.11 m (6 ft 11 in) 
Tailplane span  3.28 m (10 ft 9 in) 
Propeller diameter  1.83 m (6 ft 0 in) 
Doors (each): Height  0.80 m (2 ft 7^{1}/_{2} in) 
Width  0.94 m (3 ft 1 in) 
Height to still  0.84 m (2 ft 9 in) 
DIMENSIONS, INTERNAL:  
Cabin max width: A, B  1.17 m (3 ft 10 in) 
Baggage compartment volume: A  0.91 m^{3} (32.0 cu ft) 
B  1.05 m^{3} (37.0 cu ft) 
AREAS:  
Wings, gross: A  11.89 m^{2} (128.0 sq ft) 
B  12.17 m^{2} (131.0 sq ft) 
Ailerons (total)  0.37 m^{2} (3.97 sq ft) 
Trailingedge flaps (total)  0.65 m^{2} (6.95 sq ft) 
Fin  1.29 m^{2} (13.92 sq ft) 
Rudder  0.47 m^{2} (5.08 sq ft) 
Tailplane  1.11 m^{2} (12.00 sq ft) 
Elevators (total)  0.99 m^{2} (10.67 sq ft) 
WEIGHTS AND LOADINGS:  
Weight empty: A  544 kg (1,200 lb) 
B  635 kg (1,400 lb) 
Fuel weight  92 kg (203 lb) 
Baggage capacity  113kg (250 Ib) 
Max TO weight: landplane: A  889 kg (1,960 Ib) 
B  1,043 kg ( 2,300 Ib) 
floatplane  952 kg ( 2,100 Ib) 
Max wing loading : landplane  
A  74.8 kg/m^{2}(15.31 Ib/sq ft) 
B  85.7 kg/m^{2}(17.56 Ib/sq ft) 
floatplane  80.1 kg/m^{2}(16.41 Ib/sq ft) 
Max power loading : landplane:  
A  7.46 kg/kW (12.25 Ib/hp) 
B  7.78 kg/kW (12.78 Ib/hp) 
floatplane  7.99 kg/kW (13.13 Ib/hp) 
PERFORMANCE (A: 119 kW,160 hp, engine,constantspeed propeller, B : 134 kW, 180 hp engine constantspeed propeller): 

Never – exceed speed (V_{NE}) :  
A,B  162 kt ( 300 km/h; 186 mph) 
Max level speed : A  145 kt ( 269 km/h; 167 mph) 
B  140 kt ( 259 km/h; 161 mph) 
Max cruising speed at 75% power :  
A  140 kt ( 259 km/h; 161 mph) 
B  135 kt ( 249 km/h; 155 mph) 
Econ cruising speed at 65% power :  
A  133 kt ( 246 km/h; 153 mph) 
B  129 kt ( 240 km/h; 149 mph) 
Stalling speed,power off :  
flaps up : A  49 kt ( 91 km/h; 57 mph) 
B  51 kt ( 94 km/h; 58 mph) 
flaps down : A  43 kt ( 79 km/h; 49 mph) 
B  42 kt ( 78 km/h; 48 mph) 
Max rate of climb at S\L : A  632 m (2,075 ft)/min 
B  594 m (1,950 ft)/min 
Service ceiling : A,B  6,096 m (20,000 ft) 
TO run : A  88 m (290 ft) 
B  107 m (350 ft) 
TO to 15 m (50ft)  155 m (510 ft) 
Landing from 15 m (50 ft)  168 m (550 ft) 
Landing run : A , B  79 m (260 ft) 
Range : with standard fuel :  
A  481 n miles (890 km ; 553 miles) 
B  391 n miles (724 km ; 450 miles) 
With max fuel : A  828 n miles (1,533 km ; 953 miles) 
B  699 n miles (1,295 km ; 805 miles) 
Endurance with max fuel  6h 
g limits : both  +3.8/1.5 