The Birdman Atlas is a single-seat, high wing, single engine in pusher configuration, ultralight aircraft that was based upon the Eipper Quicksilver design.
The Atlas was introduced to the marketplace in 1980. Production was curtailed in about 1983 as the company concentrated on producing the newer Birdman WT-11 Chinook instead.
The Atlas was a development of the Quicksilver and as such incorporated many of the Quicksilver's features, such as a 6061-T6 aluminum-framed, single-surface Dacron-covered, wire-braced high wing, with the ground wires suspended from a kingpost. The fuselage structure was also built from 6061-T6 aluminum tube.
The early Atlas XC variants used weight shift for control supplemented with a rudder, whereas the later 3-A versions (for 3-Axis) utilized a conventional control system with elevator and rudder, and spoilers for roll control.
Atlas 215 XC
Foot-launchable single place ultralight powered by a 20 hp (15 kW) 215 cc single cylinder Cuyuna 215 engine. Control system is weight shift, plus rudder. Landing gear includes a shimmy-damped, shock-absorbing tailwheel unit. Available in kit form.
Atlas 250 XC
Foot-launchable single place ultralight powered by a 25 hp (19 kW) 250 cc twin cylinder Rotax engine. Control system is weight shift, plus rudder. Landing gear includes a shimmy-damped, shock-absorbing tailwheel unit. Available in kit form.
Atlas 215 3-A
Non-foot-launchable single place ultralight powered by a 20 hp (15 kW) 215 cc single cylinder Cuyuna 215 engine. Conventional three-axis control system utilizing spoilers for roll-control. Seat is adjustable fore and aft for balance. Due to company concerns about rigging requirements it was only supplied as a completed aircraft.
Atlas 250 3-A
Non-foot-launchable single place ultralight powered by a 25 hp (19 kW) 250 cc twin cylinder Rotax engine. Conventional three-axis control system utilizing spoilers for roll-control. Due to company concerns about rigging requirements it was only supplied as a completed aircraft.
Data from Janes All the Worlds Aircraft 1982-83
General characteristics
Crew: one
Length: 14 ft 0 in (4.27 m)
Wingspan: 32 ft 0 in (9.75 m)
Wing area: 160 sq ft (15 m2)
Aspect ratio: 6.4
Empty weight: 208 lb (94 kg)
Max takeoff weight: 475 lb (215 kg)
Fuel capacity: 2.8 US gallons (13 litres)
Powerplant: 1 × Cuyuna 215 two stroke snowmobile engine, 20 hp (15 kW)
Propellers: 2-bladed pusher propeller
Performance
Maximum speed: 46 mph (74 km/h; 40 kn)
Cruise speed: 41 mph (36 kn; 66 km/h)
Stall speed: 20 mph (17 kn; 32 km/h)
Range: 85 mi (74 nmi; 137 km)
Endurance: 3 hours 6 minutes
Rate of climb: 350 ft/min (1.8 m/s) at 2400 feet (732 m) with 150 lb (68 kg) pilot
Wing loading: 3.1 lb/sq ft (15 kg/m2)
