Mainair Blade 582 Manual

• Mainair Blade 582 Manual Pdf
• Blade 582

The Mainair Blade is a British ultralight trike that was designed and produced by Mainair Sports and later P&M Aviation. The aircraft was supplied as a completed aircraft.^[1][2][3]

In the early 2000s Mainair was merged with rival Pegasus Aviation into P&M Aviation, but production of the Blade continued. As the company rationalized the two aircraft lines, Blade production ended. By 2012 the manufacturer indicated, 'This aircraft is no longer in production...Full spares and support are still available and will remain so for the foreseeable future. Complete aircraft can still be manufactured but by special request only.'^[2][4]

Design and development[edit]

The aircraft was designed as a high-end touring trike, to comply with the Fédération Aéronautique Internationalemicrolight category, including the category's maximum gross weight of 450 kg (992 lb) and is also certified to comply with UK BCAR Section 'S'. The aircraft has a maximum gross weight of 390 kg (860 lb). It features a cable-bracedhang glider-style high-wing, weight-shift controls, a two-seats-in-tandem, open cockpit, tricycle landing gear and a single engine in pusher configuration.^[1]

We are a leading British Microlight Aircraft Manufacturer. P&M Aviation, Elm Tree Park, Manton, Marlborough, Wiltshire. SN8 1PS, United Kingdom. We are a leading British Microlight Aircraft Manufacturer.

Mainair Blade 582 Manual Pdf

The aircraft is made from bolted-together aluminium tubing, with its double-surface wing covered in Dacron sailcloth. Its 10.6 m (34.8 ft) span wing is supported by a single tube-type kingpost and uses an 'A' frame control bar. The occupants are accommodated in tandem seating, with a fibreglasscockpit fairing that includes a small windshield. Engines factory supplied include the 37 kW (50 hp) Rotax 503 twin cylinder, two-stroke, air cooled powerplant as well as the twin cylinder, two-stroke, liquid cooled 48 kW (64 hp) Rotax 582 and the four cylinder, four-stroke 60 kW (80 hp) Rotax 912UL and 74.5 kW (100 hp) Rotax 912ULS.^[1][2]

Operational history[edit]

Blades have been used for a number of microlight record distance flights, including a flight to Australia by Colin Bodill and Simon Reeve and a flight around the world by Bodhill.^[2]

The Blade 912 set the record for London to Sydney by microlight of 49 days (175 hours of flying) at an average speed of 124 km/h (77 mph).^[3]

Variants[edit]

Blade 582

Version powered by a 48 kW (64 hp) Rotax 582 engine. Price in 2003 was £16,450.^[2]

Blade 912

Version powered by a 60 kW (80 hp) Rotax 912UL or the 74.5 kW (100 hp) Rotax 912ULS. In 2003 it was reported that the Blade 912 accounted for the majority of customer orders. Price in 2003 was £21,800.^[2]

Specifications (Blade 912)[edit]

Data from Bertrand and Kitplanes^[2][3]

General characteristics

• Crew: one
• Capacity: one passenger
• Wingspan: 10.6 m (34 ft 9 in)
• Wing area: 15.6 m² (168 sq ft)
• Empty weight: 190 kg (419 lb)
• Gross weight: 390 kg (860 lb)
• Fuel capacity: 65 litres (14 imp gal; 17 US gal)
• Powerplant: 1 × Rotax 912 four cylinder, four-strokeaircraft engine, 60 kW (80 hp)

Performance

• Maximum speed: 145 km (90 mph, 78 kn)
• Cruise speed: 106 km (66 mph, 57 kn)
• Stall speed: 48 km (30 mph, 26 kn)
• Range: 410 km (250 mi, 220 nmi)
• Service ceiling: 3,000 m (10,000 ft)
• Rate of climb: 6.35 m/s (1,250 ft/min)
• Wing loading: 25.0 kg/m² (5.1 lb/sq ft)

References[edit]

Blade 582

1. ^ ^abcCliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, page C-14. Cybair Limited Publishing, 2001. ISBN0-9680628-1-4
2. ^ ^abcdefgBertrand, Noel; Rene Coulon; et al: World Directory of Leisure Aviation 2003-04, page 104. Pagefast Ltd, Lancaster OK, 2003. ISSN1368-485X
3. ^ ^abcDowney, Julia: 2000 Trike and 'Chute Directory, Kitplanes, Volume 17, Number 2, February 2000, page 46 and 47. Kitplanes Acquisition Company. ISSN0891-1851
4. ^P&M Aviation (n.d.). 'The Mainair Blade'. Retrieved 18 January 2012.

External links[edit]

The Rotax 582 is a 48kW (64hp)two-stroke, two-cylinder, rotary intake valve, oil-in-fuel or oil injection pump, liquid-cooled, gear reduction-drive aircraft engine manufactured by BRP-Rotax GmbH & Co. KG. It is for use in non-certified aircraft operating in day visual flight rules.

Development

The Rotax 582 is based upon the earlier Rotax 532 engine design and was designed for ultralight aircraft.^[1][2] The 582 increased the bore from the 532 engine's 72 to 76mm (2.8 to 3.0in) and increased the stroke from 61 to 64mm (2.4 to 2.5in). This increased the displacement from 521.2cc (31.81cuin) to 580.7cc (35.44cuin), an increase of 11%. The increased displacement had the effect of flattening out the 532's torque curve and allowed the 582 to produce useful power over a wider rpm range. Reliability over the 532 was also improved.^[2]

The 582 features liquid-cooled cylinder heads and cylinders with a Rotary Intake Valve. Cooling is via an externally mounted radiator. Lubrication is either by use of pre-mixed fuel and oil or oil injection from an externally mounted oil tank. The 582 has dual independent breakerless, magneto capacitor discharge ignition (CDI) systems and is equipped with two piston-type carburetors. It uses a manifold-driven pneumatic fuel pump to provide fuel pressure. An optional High Altitude Compensation kit is available.^[1][2]

The engine's propeller drive is via a Rotax type B, C or E style gearbox. The standard engine includes a muffler exhaust system with an extra after-muffler as optional. The standard starter is a recoil start type, with an electric starter optional. An integral alternating current generator producing 170watts at 12volts with external rectifier-regulator is optional. The engine includes an intake air filter and can be fitted with an intake silencer system.^[1][2]

Limitations

The manufacturer acknowledges the design limitations of this engine, warning pilots:^[1]

'This engine, by its design, is subject to sudden stoppage. Engine stoppage can result in crash landings, forced landings or no power landings. Such crash landings can lead to serious bodily injury or death...This is not a certificated aircraft engine. It has not received any safety or durability testing, and conforms to no aircraft standards. It is for use in experimental, uncertificated aircraft and vehicles only in which an engine failure will not compromise safety. User assumes all risk of use, and acknowledges by his use that he knows this engine is subject to sudden stoppage...Never fly the aircraft equipped with this engine at locations, airspeeds, altitudes, or other circumstances from which a successful no-power landing cannot be made, after sudden engine stoppage. Aircraft equipped with this engine must only fly in DAYLIGHT VFR conditions.'^[1]

Applications

• Revolution Mini-500 helicopter

Specifications (Rotax 582)

General characteristics

• Type: two-cylinder, two-stroke, rotary valve, oil-in-fuel or oil-injected lubrication, dual carburetors, electronic dual ignition
• Bore: 76 mm (2.99 in)
• Stroke: 64 mm (2.52 in)
• Displacement: 580.7 cm³ (35.44 cu in)
• Dry weight: 50 kg (110 lb) with electric starter, carburetors, fuel pump, air filters and reduction gear

Components

• Fuel type: premium unleaded: RON 90 octane or higher leaded or unleaded or AVGAS 100 LL
• Oil system: oil-in-fuel (pre-mix) or oil injection
• Cooling system: liquid cooled

Performance

• Power output: 48 kW (64.4 hp) at 6,500RPM
• Compression ratio: 11.5 (theoretical) - 5.75 effective

See also

References

1. BRP-Rotax GmbH & Co. KG (2006). 'OPERATORS MANUAL FOR ENGINE TYPES 447, 503 & 582'(PDF). Retrieved 2009-03-09.
2. Raisner, William: LEAF catlog, pages 6-105. Leading Edge Airfoils, 1995.

External links