Maule M-5

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Maule M-5-235C C-GPYC 01.JPG
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[edit]

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.


Initial production variant with a 180-horsepower (134 kW) Lycoming O-360-C1F engine, more than 94 built.
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 Rocker
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 Strata Rocket)[edit]

Data from The Illustrated Encyclopedia of Aircraft[1]

General characteristics

  • Crew: 1
  • Capacity: 3
  • Length: 23 ft 6 in (7.16 m)
  • Wingspan: 30 ft 10 in (9.40 m)
  • Height: 6 ft 2½ in (1.89 m)
  • Wing area: 157.90 ft2 (14.67 m2)
  • Empty weight: 1400 lb (635 kg)
  • Gross weight: 2300 lb (1043 kg)
  • Powerplant: 1 × Lycoming O-540-J1A5D flat-six piston engine, 235 hp (175 kW)


  • Maximum speed: 172 mph (277 km/h)
  • Range: 550 miles (885 km)
  • Service ceiling: 20000 ft (6096 m)


  1. ^ Orbis 1985, p 2435
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. 
  • Simpson, R.W. Airlife's General Aviation. England: Airlife Publishing. p. 190. ISBN 1-85310-194-X. 
  • The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing. 1985.