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The Acrolite 2M aircraft was designed in 1991 and built in 1991 to 1994, it had its first flight in June of 1994. It is a high wing two place tandem seat monoplane powered by a Rotax 582, 65 hp engine. Originally designed for the Rotax 912, performance is surprisingly good with the smaller engine. It was designed as per TP10141 the Canadian specifications for advanced ultralight aircraft and also meets the U.S. Sport Pilot requirements. The aircraft is stressed for this category with a 4 g. limit load and 6 g. ultimate load. The aircraft was designed with strength, ability to take abuse, ease of repair, good short field performance and stable flight characteristics as the most important features with aircraft grade materials used throughout. Tandem seating was selected and most of the popular ultralight twin cylinder two stroke engines can be used from 60 hp on up and the lighter four cylinder aircraft engines like the 80 hp four cylinder Rotax 912 and the 80 hp Jabiru. With an engine of 65 hp or more the aircraft is easily capable of carrying two 180 lb persons of over 6 ft. in height and full fuel. The fuselage is long for better stability and is constructed of welded 4130 chrome moly steel as per standard aircraft methods and covered with Polyfiber 1.7 oz. fabric. The tail assembly is constructed of 6061 aluminum tube riveted together with 2024-T3 aluminum gusset plates and fabric covered. This type construction allows a full cantilever empennage with low drag and light weight. Control linkages to the ailerons and elevator are push-pull rods with bearings on each end for positive control and friction free operation. Rudder and steerable tailwheel control is via a common cable. The wing is of stressed skin construction with a box section main spar, a channel section rear spar and strut braced. It is built entirely of 2024-T3 aluminum, fully sheeted and flush riveted with 1/8 inch diameter stainless steel blind rivets. The ailerons are full span aluminum tube, fabric covered and static balanced. The landing gear is one piece spring aluminum clamped and bolted directly to the bottom of the fuselage with four bolts. This type landing gear has low drag is easy to construct and handles hard landings and rough ground well. The wheels and tires are 600 X 5 aircraft type with cable operated drum brakes. Optionally hydraulic operated disk brakes can also be used. Floats and skis can also be used with a minimum of adapting. On November 2002 the 582 engine was removed for installation in the new Triplane and a new Rotax 912U engine was purchased for it. During the next year the 912 engine was installed, modifications were made to the airframe to strengthen the landing gear area, the fuselage was recovered, wheel fairings were added and the aircraft was painted. The first flight with the new engine was made on Nov. 8, 2003. A set of skis were fitted and flew it on skis through the winter of 2004/2005. After over 200 hours on the airframe, all the restrictions had been flown off and the flight testing had been completed, and the construction drawings and builders manual were completed and the design offered for sale.
Engine: Rotax 912, 80 hp Reduction: 2.23 to 1 Propeller: 68 x 48 Airfoil: GA30U-412 Wingspan: 28.4 ft Wing area: 141 sq.ft Wing chord: 5 ft Aspect ratio: 5.7 to 1 Length: 20.3 ft Height: 6.5 ft Fuel capacity: 14 gal U.S. Wheel & tire size: 600 x 6 Empty weight: 600 lb Gross weight: 1200 lb Span loading: 20.0 lb/ft Wing loading: 8.5 lb/sq.ft Power loading: 15 lb/bhp Power off stall speed: 44 mph Power on stall speed: 40 mph Landing speed: 60 mph Maneuvering speed: 85 mph Maximum level speed: 130 mph Never exceed speed: 150 mph Cruise speed: 110 mph@ 5000 rpm Best glide speed: 75 mph Best rate of climb: 1100 fpm Best climb rate speed: 80 mph Range: 250 sm Take off distance: 750 ft Landing distance: 500 ft Cockpit width: 30 in Engine: Rotax 618, 75 hp Reduction: 2.58 to 1 Propeller: 66 x 46 Airfoil: GA30U-412 Wingspan: 28.4 ft Wing area: 141 sq.ft Wing chord: 5 ft Aspect ratio: 5.7 to 1 Length: 20.3 ft Height: 6.5 ft Fuel capacity: 14 gal U.S. Wheel & tire size: 600 x 6 Empty weight: 575 lbs Gross weight: 1100 lbs Span loading: 18.7 lb./ft Wing loading: 7.8 lb/sq. ft. Power loading: 14.7 lb/bhp Power off stall speed: 42 mph. Power on stall speed: 38 mph Landing speed: 57 mph Maneuvering speed: 85 mph Maximum level speed: 125 mph Never exceed speed: 150 mph Cruise speed: 105 mph@ 5800 Best glide speed: 75 mph Best rate of climb: 1000 fpm Best climb rate speed: 80 mph Range: 250 sm Take off distance: 750 ft Landing distance: 500 ft Engine: Rotax 582, 65 hp Reduction: 2.58 to 1 Propeller: 64 x 44 Airfoil: GA30U-412 Wingspan: 28.4 ft Wing area: 141 sq.ft Wing chord: 5 ft Aspect ratio: 5.7 to 1 Length: 20.3 ft Height: 6.5 ft Fuel capacity: 14 gal U.S. Wheel & tire size: 600 x 6 Empty weight: 575 lbs Gross weight: 1100 lbs Span loading: 18.7 lb/ft Wing loading: 7.8 lb./sq. ft. Power loading: 16.9 lb/bhp Maneuvering speed: 85 mph Maximum level speed: 110 mph Never exceed speed: 150 mph Cruise speed: 90 mph Best glide speed: 75 mph Best rate of climb: 750 fpm Best climb rate speed: 80 mph Range: 250 sm Take off distance: 750 ft Landing distance: 500 ft |
