Engineering:Maule M-5
| M-5 | |
|---|---|
| |
| Maule M-5-235C | |
| Role | Four-seat cabin monoplane |
| National origin | United States |
| Manufacturer | Maule Aircraft Company |
| Designer | Belford Maule |
| First flight | 1971 |
| Introduction | 1974 |
| Produced | 1974-1983 |
| Number built | over 855 |
| Developed from | Maule M-4 |
The Maule M-5 is an American four-seat cabin monoplane designed and built by the Maule Aircraft Company.
Design and development
The M-5 was a development of the earlier Maule M-4 with improved STOL performance. It has a 30% increase in flap area and enlarged tail surfaces.
Two prototype M-5s flew in 1971, one powered by a 210-hp (157 kW) engine, the other with a 220-hp (164 kW) engine.
The M-5 is a steel-tube and fabric high-wing braced-monoplane with a cantilever tailplane with a single fin and rudder. It has a fixed-tailwheel landing gear and an enclosed cabin with two rows of side-by-side seating for a pilot and three passengers. The aircraft entered production in 1974 and was named the Strata Rocket and the Lunar Rocket. A generally similar M-6 Super Rocket was also developed with a 3-foot-longer (0.91 m) wingspan and more fuel capacity, smaller ailerons and larger flaps.
Variants
- M-5-180C
- Initial production variant with a 180-horsepower (134 kW) Lycoming O-360-C1F engine, more than 94 built.
- M-5-200
- One aircraft modified with a 200-horsepower (149 kW) engine.
- M-5-210C Strata Rocket
- 180C with a 210-horsepower (157 kW) Continental IO-360-D engine in a revised cowling, 206 built.
- M-5-210TC Lunar Rocket
- 210C fitted with a turbocharged 210-horsepower (157 kW) Lycoming TO-360 engine, 10 built.
- M-5-220C Lunar Rocket
- 210C fitted with a 220-horsepower (164 kW) Franklin 6A-350-C1 engine, 57 built.
- M-5-235C Lunar Rocket
- 210C fitted with a 235-horsepower (175 kW) Lycoming O-540-J1A5D engine, more than 379 built.
- M-6-235C Super Rocket
- 235C with a 3-foot-longer (0.91 m) wingspan and more fuel capacity, smaller ailerons and larger flaps, 136 built.
Specifications (M-5-235C Lunar Rocket)
Data from Jane's All the World's Aircraft 1982–83[1]
General characteristics
- Crew: 1
- Capacity: 3 passengers
- Length: 23 ft 6 in (7.16 m)
- Wingspan: 30 ft 10 in (9.40 m)
- Height: 6 ft 2 1⁄2 in (1.892 m)
- Wing area: 157.9 sq ft (14.67 m2)
- Aspect ratio: 6.02:1
- Airfoil: USA 35B (modified)
- Empty weight: 1,400 lb (635 kg)
- Gross weight: 2,300 lb (1,043 kg)
- Fuel capacity: 63 US gal (52 imp gal; 240 L)
- Powerplant: 1 × Lycoming O-540-J1A5D air-cooled flat-six piston engine, 235 hp (175 kW)
- Propellers: 2-bladed Hartzell constant-speed propeller, 6 ft 6 in (1.98 m) diameter
Performance
- Maximum speed: 172 mph (277 km/h, 149 kn)
- Cruise speed: 160 mph (260 km/h, 140 kn) (econ. cruise) CAS
- Range: 550 mi (890 km, 480 nmi) (max standard fuel)
- Service ceiling: 20,000 ft (6,100 m)
- Rate of climb: 1,350 ft/min (6.9 m/s)
References
- ↑ Taylor 1982, pp. 412–413
- Taylor, John W. R., ed (1982). Jane's All The World's Aircraft 1982–83. London: Jane's Yearbooks. ISBN 0-7106-0748-2.
- Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions.
- Simpson, R.W. (1991). Airlife's General Aviation. England: Airlife Publishing. pp. 190. ISBN 1-85310-194-X.
- The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing. 1985.
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