TYPE: Side-by-side kitbuilt
PROGRAMME: Designed by Arlington Aircraft Developments and produced until 2000 by Stoddard-Hamilton. 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 customer-built aircraft completed in July 1996. Early examples had a 93 kW (125 hp) Teledyne Continental IO-240. "Jumpstart" kits introduced in 2003, reducing build time by estimated 400 hours. FAA certified version being built in Germany as OMF Symphony. Four-seat, Four Winds versions produced in US.
CURRENT VERSIONS: Glastar: Basic model; as described.
Sportsman 2+2: Introduced mid-2003 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 two-seat personal lightplane with wide performance envelope. Convertible landing gear, float compatible. Wings fold (one-person, three-minute 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. Ground-adjustable tab on ailerons. Three-position flaps: 0,20 and 400. 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 2024-T3 aluminium. Two-spar 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: 5.00-5 (with speed fairings), 6.00-6 and 8.00-6. Optional Scott 3200 20 cm (8 in) tailwheel with larger mainwheels.
POWER PLANT: Glastar: One 119 kW (160hp) Textron Lycoming O-320-D1F flat-four, driving a Sensenich fixed-pitch or Hartzell constant-speed two-blade propeller: or 112 kW (150hp) 0-320-E1A and 134kW (180 hp) 0-320-A1A; power plants in the range 93-168 kW (125-225 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 0-360 engine driving two-blade Hartzell constant-speed 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|
|Length: fuselage: A||6.78 m (22 ft 3 in)|
|overall, Lycoming O-320||6.95 m (22 ft 91/2 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 71/2 in)|
|Width||0.94 m (3 ft 1 in)|
|Height to still||0.84 m (2 ft 9 in)|
|Cabin max width: A, B||1.17 m (3 ft 10 in)|
|Baggage compartment volume: A||0.91 m3 (32.0 cu ft)|
|B||1.05 m3 (37.0 cu ft)|
|Wings, gross: A||11.89 m2 (128.0 sq ft)|
|B||12.17 m2 (131.0 sq ft)|
|Ailerons (total)||0.37 m2 (3.97 sq ft)|
|Trailing-edge flaps (total)||0.65 m2 (6.95 sq ft)|
|Fin||1.29 m2 (13.92 sq ft)|
|Rudder||0.47 m2 (5.08 sq ft)|
|Tailplane||1.11 m2 (12.00 sq ft)|
|Elevators (total)||0.99 m2 (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 T-O 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/m2(15.31 Ib/sq ft)|
|B||85.7 kg/m2(17.56 Ib/sq ft)|
|floatplane||80.1 kg/m2(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,constant-speed
propeller, B : 134 kW, 180 hp engine constant-speed
|Never – exceed speed (VNE) :|
|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)|
|T-O run : A||88 m (290 ft)|
|B||107 m (350 ft)|
|T-O 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|