Designed by Jim Maupin and Irv Culver to meet SHA Homebuilt Sailplane Design Contest criteria: easy to built, low cost, soarable, self-launching, safe, the definitive powered Windrose first flew in 1984. The structural backbone is a hollow plywood box with corners longerons which carry the engine mounts, landing gear and fiberglass cockpit shell. The wings are shaped foam covered with fiberglass, but without a conventional spar. The spars are bands of unidirectional roving expoxied into recesses in the upper and lower wing skins, and separated by rows of vertical dowels between the bands to take compression loads off the foam. Ailerons are set inboard from the root to approximately two-thirds span operated by pushrods from the fuselage. The wing structure is free of controls, pushrods, cables etc. Glidepath control is by a triangular spoiler which rises above the wing center section. Both tail surfaces are all-moving. The design comes in 12.65 and 15.0 m models. Windrose was offered as partial or complete kit, or plans only. Plans used to cost $175 in the US and Canada, airmail overseas for $195.
The Windrose II motor glider has an optional shorter wing span or Cuyuna UL-II-02 engine.
Designed by Jim Maupin & Irv Culver, the Carbon Dragon first flew in 1988. Altrough meeting the FAI definition of a hang glider, the Carbon Dragon can be launched by foot, aerotow, or bungee. Roll control and approach control are by full span 30 % chord flaperons, and at least one has been modified by the addition of a pentagonal shaped spoiler in the wing section, similar to that on the Maupin Windrose. It has a fixed main wheel. It complies with U.S. FAA Part 103 rules. In 1994 it became the first sailplane in that class to win against conventional gliders in a scheduled, non-handicapped cross-country contest. An ultralight sailplane, basic wood construction with use of carbon epoxy to reduce weight and improve stiffness. Was available as plans for $150. Price (1998) $ 170 (Plans) Building time estimated at 1500 hours.
Weight: 65 kg / 145 lb Gross Weight: 151kg / 335lb Payload: 85kg / 190lb Wing span: 13.2 m / 44 feet Wing area: 14.25sq.m / 153.34sq.ft Vne: 112 km / 70 mph L/D: 25:1 at 32 mph Stall: 20 mph Min sink: 0.51 m/s / 100 fpm / 0.99 kt at 26 mph. Seats: 1 Wing Load: 10.61 kg/sq.m / 2.18 lb/sq.ft Aspect ratio: 12.62 Airfoil: Culver CD Landing gear: single wheel
In 1981, Maule installed an IO-540-W1A5D out front of the M-5 and began delivering the M-6, also available with EDO floats. Two years later the model would morph into the M-7 and in 1989, the M-8.
In 1981, Maule installed an IO-540-W1A5D out front of the M-5 and began delivering the M-6, also available with EDO floats. Two years later the model would morph into the M-7 and in 1989, the M-8. In 1991, the company experimented with a turbine Maule, installing an Allison 420 shp 250-B17-C and eventually offered the design in both taildragger and tricycle gear configurations. The family continues to create endless variations and improvements on the original airframe, with the original fuselage jig designed by founder B.D. Maule still in use in 1975.
Maule Aircraft have fitted their utility aircraft with Allison 250-B17 engines to create two new models, the M-7 and MX-7. Initial performance estimates include a 196 mph cruise, a partly loaded takeoff distance of 400 feet and a gross weight climb of 3000 feet/minute.
Fuselage: 4130 Chromoly Steel truss structure Covering: Ceconite (a synthetic fabric) covers the fuselage, tail, and tail control surfaces Wing, Flap, Aileron: Aluminum Spar, ribs, and skin Firewall: Stainless Steel Engine Cowling: Fiberglass Doors: Steel frame with aluminum skin Instrument Panel: Aluminum Aircraft Interior: Fully upholstered – standard vinyl/velour seats and trim, velour headliner Fuselage and tail structures are powder-coated for corrosion resistance. Wing lift struts are sealed and internally coated with oil. Wings, flaps, and ailerons are primed inside and out for corrosion resistance. Urethane primer and finish paint used to provide long-lasting beauty, protection, and flexibility for the Ceconite covering. Optional Stainless Steel Kit – This kit provides SS bolts where approved. SS turnbuckles for elevator (Ref. SL#55), SS clevis pins for control surfaces
M-7-235C Engine: Lycoming IO-540-WIA5, 235 hp TBO: 2000 hr Propeller: Const. spd. Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Gross weight: 2500 lb Empty weight: 1600 lb Fuel: 73 USgal Baggage capacity: 250 lb Landing gear type: Conv./Fixed Gear Width: 7 ft 10 in Cruise speed 75% power: 124 kt Cruise speed 65% power: 116 kt Max range (w/ reserve) 75% power: 572 nm Max range (w/ reserve) 65% power: 542 nm Stall speed (gear, flaps down): 39 kt Fuel consumption 75% power: 13 USgph Fuel consumption 65% power:12.5 USgph Flap Settings: -7, 0, 24, 40, 48 degs Best Climb Speed: 90 mph Best rate of climb: 1150 fpm Service ceiling: 20,000 ft Seats: 5 Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Cabin Width Rear Pass Seat: 33” shoulder, 28” hips Cabin height: 37 in Takeoff ground roll: 450 ft Landing ground roll: 550 ft
M-7-260 Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Flap Settings: -7, 0, 24, 40, 48 degs Best Climb Speed: 90 mph Seats: 5 Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Cabin Width Rear Pass Seat: 33” shoulder, 28” hips
M-7-260C Engine: Lycoming IO-540-V4A5, 260 hp TBO: 2000 hr Fuel type:100LL Propeller: 78/79.5 Inch (2 Blade) 78/80 (3 Blade) Landing Gear Configuration: Spring Gear Wing Span: 32 ft 11 in Wing Area: 165.6 sq.ft Length: 23 ft 6 in Height: 8 ft 4 in Wing loading: 9.6 lb/sq. ft Power loading: 15 lb/hp Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Cabin Width Rear Pass Seat: 33” shoulder, 28” hips Cabin height: 46 in Cabin doors: 4 Baggage capacity: 170 lb Seats: 5 Max ramp weight: 2500 lb Gross Weight: 2500 Pounds Landing weight: 2500 lb Empty Weight: 1671 Pounds Useful Load: 829 lb Useful Fuel Capacity: 73 Gal. Stall Speed (Full Flaps/1 Person/ 1/2 Fuel: 40 mph. Rate Of Climb (1 Person/ 1/2 Fuel): 2000 fpm Land at Gross Over 50′ Obstacle: 500 Feet Best Climb Speed: 90 Mph. Service Ceiling: 20,000 Feet Fuel consumption 75% power: 15.0 USgph Fuel consumption 65% power: 13.5 USgph Range, Max (30 Minute Reserve): 782 Miles Cruise (75% Power at Opt. Alt.): 166 Mph. Landing gear type: Fixed/Conv Wheel base: 7 ft 10 in Wheel track: 15.8 ft Wheel size, std: 7.00 x 6 in Flap Settings: -7, 0, 24, 40, 48 degs Takeoff ground roll: 250 ft Takeoff over 50-ft. obstacle: 600 ft Landing ground roll: 300 ft Landing over 50-ft. obstacle: 500 ft
M-7-420 Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Flap Settings: -7, 0, 24, 40, 48 degs Best Climb Speed: 90 mph Seats: 5 Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Cabin Width Rear Pass Seat: 33” shoulder, 28” hips
M-7-420AC Wing Span: 33 ft 8 in Wing Area: 169.2 sq ft Length: 24 ft Height: 6 ft 4 in Gear Width: 7 ft 10 in Flap Settings: -7, 0, 24, 40, 48 degs Best Climb Speed: 90 mph Seats: 5 Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Cabin Width Rear Pass Seat: 33” shoulder, 28” hips
M-7-235/260/420
Maule MT-7
MT-7-235 Engine: Lycoming IO-540-W1A5D Landing Gear Configuration: TriGear Wing Span: 32 ft 11 in Wing Area: 165.6 sq.ft Length: 23 ft 6 in Height: 8 ft 4 in Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Cabin Width Rear Pass Seat: 33” shoulder, 28” hips Seats: 5 Gross Weight: 2500 Pounds Empty Weight: 1625 Pounds Useful Load: 875 Pounds Fuel Capacity: 70 Gal. Stall Speed (Full Flaps/1 Person/ 1/2 Fuel: 40 mph. Take Off (1 Person/ 1/2 Fuel): 200 Feet Take Off at Gross Over 50′ Obstacle: 600 Feet Rate Of Climb (1 Person/ 1/2 Fuel): 1700 fpm Land at Gross Over 50′ Obstacle: 500 Feet Best Climb Speed: 90 mph Service Ceiling: 20,000 Feet Fuel Consumption (65% Power): 12 USGPH Range, Max (30 Minute Reserve): 850 Miles Cruise (75% Power at Opt. Alt.): 160 mph. Gear Width: 7 ft 8 in Flap Settings: -7, 0, 24, 40 degs
MT-7-260 Engine: Lycoming IO-540-V4A5 Landing Gear Configuration: TriGear Wing Span: 32 ft 11 in Wing Area: 165.6 sq.ft Length: 23 ft 6 in Height: 8 ft 4 in Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Cabin Width Rear Pass Seat: 33” shoulder, 28” hips Seats: 5 Gross Weight: 2500 Pounds Fuel Capacity: 73 USGal. Stall Speed (Full Flaps/1 Person/ 1/2 Fuel: 42 Mph. Take Off (1 Person/ 1/2 Fuel): 200 Feet Take Off at Gross Over 50′ Obstacle: 600 Feet Rate Of Climb (1 Person/ 1/2 Fuel): 1350 FPM (Gross) Land at Gross Over 50′ Obstacle: 500 Feet Best Climb Speed: 90 Mph Service Ceiling: 20,000 Feet Cruise (75% Power at Opt. Alt.): 167 Mph. Flap Settings: -7, 0, 24, 40 degs Best Climb Speed: 90 mph
MT-7-420 Engine: Allison 250-B17 Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 24 ft 6 in Height: 8 ft 4 in Landing Gear Configuration: TriGear Gear Width: 7 ft 8 in Flap Settings: -7, 0, 24, 40 degs Best Climb Speed: 90 mph Seats: 5 Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Cabin Width Rear Pass Seat: 33” shoulder, 28” hips Fuel Capacity: 85 US gal
MT-7-235/260/420
Maule MX-7
MX-7-160 Engine: Lycoming O-320-B2D Propeller: Sensenich 74 Inch Landing Gear Configuration: Oleo Strut Taildragger Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Seats: 4 Gross Weight: 2200 Pounds Empty Weight: 1330 Pounds Useful Load: 870 Pounds Fuel Capacity: 40 Gallons (70 optional) Stall Speed (Full Flaps/1 Person/ 1/2 Fuel: 40 Mph. Take Off (1 Person/ 1/2 Fuel): 600 Feet Take Off at Gross Over 50′ Obstacle: 1180 Feet Rate Of Climb (1 Person/ 1/2 Fuel): 825 FPM Land at Gross Over 50′ Obstacle: 500 Feet Best Climb Speed: 90 Mph. Service Ceiling: 13,000 Feet Fuel Consumption (65% Power): 8 USGPH Range, Max (30 Minute Reserve): 540 Miles Cruise (75% Power at Opt. Alt.): 135 Mph. Gear Width: 6 ft Flap Settings: -7, 0, 24, 40, 48 degs
MX-7-180A Engine: Lycoming O-360-C1F/-C4F Propeller: Sensenich 76 Inch Landing Gear Configuration: Oleo Strut Taildragger Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Seats: 4 Gross Weight: 2400 Pounds Empty Weight: 1350 Pounds Useful Load: 1050 Pounds Fuel Capacity: 40 Gallons (70 optional) Stall Speed (Full Flaps/1 Person/ 1/2 Fuel: 40 Mph. Take Off (1 Person/ 1/2 Fuel): 550 Feet Take Off at Gross Over 50′ Obstacle: 1150 Feet Rate Of Climb (1 Person/ 1/2 Fuel): 920 FPM Land at Gross Over 50′ Obstacle: 500 Feet Best Climb Speed: 90 Mph. Service Ceiling: 15,000 Feet Fuel Consumption (65% Power): 9 USGPH Range, Max (30 Minute Reserve): 500 Miles Cruise (75% Power at Opt. Alt.): 140 Mph. Gear Width: 6 ft Flap Settings: -7, 0, 24, 40, 48 degs
MX-7- 180B Engine: Lycoming O-360-C1F Propeller: Sensenich 76″ Landing Gear Configuration: Oleo Strut Taildragger Wing Span: 32 ft 11 in Wing Area: 165.6 sq.ft Length: 23 ft 6 in Height: 6 ft 4 in Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Seats: 4-5 Gross Weight: 2500 Pounds Empty Weight: 1395 Pounds Useful Load: 1105 Pounds Fuel Capacity: 73 USGal. Stall Speed (Full Flaps/1 Person/ 1/2 Fuel: 40 mph Take Off (1 Person/ 1/2 Fuel): 300 Feet Take Off at Gross Over 50′ Obstacle: 600 Feet Rate Of Climb (1 Person/ 1/2 Fuel): 1200 FPM Land at Gross Over 50′ Obstacle: 500 Feet Best Climb Speed: 90 mph. Service Ceiling: 15,000 Feet Fuel Consumption (65% Power): 9 USGPH Range, Max (30 Minute Reserve): 1095 Miles Cruise (75% Power at Opt. Alt.): 145 Mph. Gear Width: 6 ft Flap Settings: -7, 0, 24, 40, 48 degs
MX-7-180AC Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Gear Width: 7 ft 10 in Flap Settings: -7, 0, 24, 40, 48 degs Best Climb Speed: 90 mph Seats: 4 Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips
MX-7-180C Engine: Lycoming: O-360-C1F Propeller: 76 Inch Landing Gear Configuration: Spring Gear Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips Configuration: 4-5 Gross Weight: 2500 Pounds Empty Weight: 1500 Pounds Useful Load: 1000 Pounds Fuel Capacity: 73 Gal. Stall Speed (Full Flaps/1 Person/ 1/2 Fuel: 40 Mph. Rate Of Climb (1 Person/ 1/2 Fuel): 1200 FPM Land at Gross Over 50′ Obstacle: 500 Feet Best Climb Speed: 90 Mph. Service Ceiling: 15,000 Feet Fuel Consumption (65% Power): 9 GPH Range, Max (30 Minute Reserve): 1095 Miles Cruise (75% Power at Opt. Alt.): 145 Mph. Gear Width: 7 ft 10 in Flap Settings: -7, 0, 24, 40, 48 degs
M-7-235 Engine: 235-hp Lycoming O-540-J3A5 Seat 4-5 Gross wt. 2,500 lb Empty wt. 1,500 lb Fuel capacity 40-70 USG Cruise 148 kts Stall 40 kts Initial climb rate 1,350 fpm Range 478 miles Ceiling 20,000 ft Takeoff distance (50′) 600 ft Landing distance (50′) 600 ft
MX-7-235B Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Gear Width: 6 ft Flap Settings: -7, 0, 24, 40, 48 degs Best Climb Speed: 90 mph Seats: 4 Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips
M-7-235C Engine: Lycoming: O-540-J3A5, O-540-B4B5, IO-540-W1A5 Propeller: 81/80 Inch (2/3 Blade) Landing Gear Configuration: Spring Gear Wing Span: 32.9 Feet Wing Area: 165.6 Square Feet Length: 23.5 Feet Height: 6.3 Feet Cabin Width: 42 Inches Configuration: 5 Place Gross Weight: 2500 Pounds Empty Weight: 1600 Pounds Useful Load: 900 Pounds Fuel Capacity: 73 Gal. Stall Speed (Full Flaps/1 Person/ 1/2 Fuel: 40 Mph. Rate Of Climb (1 Person/ 1/2 Fuel): 1800 FPM Land at Gross Over 50′ Obstacle: 500 Feet Best Climb Speed: 90 Mph. Service Ceiling: 20,000 Feet Fuel Consumption (65% Power): 11 (IO) USGPH / 12 (O) USGPH Range, Max (30 Minute Reserve): 935 Miles Cruise (75% Power at Opt. Alt.): 160 Mph. Gear Width: 6 ft Flap Settings: -7, 0, 24, 40, 48 degs
MX-7-260 Wing Span: 32 ft 11 in Wing Area: 165.6 sq ft Length: 23 ft 6 in Height: 6 ft 4 in Gear Width: 7 ft 8 in Flap Settings: -7, 0, 24, 40, 48 degs Best Climb Speed: 90 mph Seats: 4 Cabin Width Front Seats: 42” shoulder, 37” hips Cabin Width Pass. Seats: 38” shoulder, 34” hips
In 1981, Maule installed an IO-540-W1A5D out front of the M-5 and began delivering the M-6, also available with EDO floats. Two years later the model would morph into the M-7
Of tube and fabric construction in the fuselage with metal wings. In essence, the Maule M5 is similar to the M4 but with larger vertical and horizontal tail surfaces and more effective flaps. Apart from the improved STOL capability of the M5, it also possesses a significantly more flexible C of G range.
Belford decided to put the six cylinder, 235 hp Lycoming into his M 5 because of the engine’s reliability. The M 5 is available with a 210 hp engine, but customers have opted for the 235 hp version. The O 540 has a 2,000 hour TBO and has proved remarkably trouble free over the years. The only airworthiness directive that has affected the engine was related to its Bendix magnetos.
The M 5’s skeleton is a steel tube structure, heavily primed against corrosion, since so many Maules end up on floats. With the exception of the aluminium that encases the cockpit and the fiberglass engine cowling, the fuselage is covered with a glass fiber fabric that constitutes a permanent skin, never requiring testing for strength. The special high lift wings are metal covered, and the wingtips, heavily drooped, are of fiberglass. The rugged main landing gear is mounted on pneumatic shock absorbers; the beefed up tailwheel is designed to withstand the shock of chuckholes. There are four doors, one on the left for the pilot and three on the right; the center passenger door and the aft luggage door have no separating post, so that when opened together, they provide a four foot gap for the loading of bulky cargo. As an option, there is a lightweight rear folding benchseat. A pilot could fold the seat flat, carry a full load of cargo to a remote village and unfold it on the return flight to carry a full load of passengers.
The interior of the M 5 is well designed, if a bit narrow, and the work is of a high quality, thanks to an elderly lady at the Maule factory who is “a genius in upholstery.” Overhead, the ceiling is covered with a thick, heavy weave fabric, a welcome change from the plastic of most airplanes. The instrument panel is dark, functional metal, and the switches and gauges are grouped intelligently. Overall, the Maule’s interior, like its exterior, seems tough, built to withstand the rigors of bush flying.
A total of 63 gallons of usable fuel is carried in four wing tanks; the engine feeds directly from two 20 gallon inboard tanks, which can be refilled in flight, with the additional gas pumped electrically from two 11.5 gallon outboard tanks. So, while a full fuel payload is about 462 pounds, the pilot can fill only the mains and load 600 pounds of people and cargo into the cabin. The seaplane version has a gross weight 50 pounds higher, which is more than offset by the weight of the floats. Maule in 1979 was in the process of raising the airplane’s gross weight by 200 pounds to 2,500 pounds a change that would apply retroactively to all M 5s.
The Maule is a workable IFR airplane, and 95 percent of the M 5s go out with full IFR avionics. It cruises well, burning roughly 12 gallons an hour at 65 percent power, which at 8,000 feet gives it a true airspeed of about 134 knots. But other airplanes fly faster on less gas. The Maule’s real strength is its short field ability.
The M 5 was intro¬duced in 1974 and the first M-5 Lunar-Rockets were delivered in 1974 as M-5-21OCs with 210-hp Continental engines. The M-5-220C houses a 220-hp Franklin. These models differ from the earlier M-4s by having four cabin doors for hauling cargo as the “C” in the model number implies; otherwise, the M-5 has a 30% increase in flap area and enlarged tail surfaces to enhance its short-field performance. The 220-hp version was discontinued when the Franklin engine was no longer available, and the M-5-235C was added to the line in 1976 employing a 235-hp Lycoming.
M-5-220C Lunar Rocket
Factory base price was $20,565 in 1975. The 1975 used price range: $13,000 to $16,000 for ’70 through ’72 models, and $17,000 to $19,500 for’73 through ’75 models.
The 1977 M-5 model was fitted with either the 210-hp Continental 10-360-D33A or a 235-hp Lycoming.
The Maule M-5 Rocket, which has been manufactured steadily, if in relatively small numbers, in Moultrie, Ga. since the early sixties, is a STOL airplane designed to fly from short, rough fields. With a stalling speed of only 38 mph, and the ability to takeoff over a 50-ft. obstacle in 550 feet, the Maule is seldom seen on paved runways. Most are at work in Alaska, the American West, and in Latin America. Cruise of the later models is in the 160 + mph class.
M-5-220C Undercarriage: conv. oleo Produced: 1974-75 Engine: Franklin O-350, 220 hp TBO: 1500 hr Prop: C/S Wingspan: 30’10” Wingtip: Droop
M5-235 Engine: Lycoming O 540 J1A5D, 235 hp TBO: 2,000 hrs Prop: two blade, constant speed, 84 inch diameter Length: 27 ft. 7 in Height: 6 ft. 4 in Wingspan: 30 ft. 10 in Wing area: 157 sq. ft Max ramp weight: 2,300 lb Max takeoff weight: 2,300 lb Standard empty weight: 1,400 lb Max useful load: 900 lb Max landing weight: 2,300 lb Wing loading: 14.6 lb/sq.ft Power loading: 9.8 lb/hp Max usable fuel: 63 USG/378 lb Max rate of climb, sea level: 1,300 fpm Max rate of climb 8,000ft: 800fpm Max operating altitude: 20,000 ft Max speed (8,500 ft): 148 kt Cruise, 65% power at 8,000 ft: 134 kt Fuel flow at 65% power: 12 USG/hr Endurance at 65% power, no res: 5 hr Stalling speed, clean: 54 kt Stalling speed, flaps down: 49 kt Turbulent air penetration speed: 109 kt Seats: 4
M-5-235C Lunar Rocket Engine: 1 x Lycoming O-540-J1A5D, 235 hp TBO: 2000 hr Prop: McCauley 3 blade, CSU Wingspan: 30’10” Wingtip: Droop Seats: 4 Wing loading: 14.57 lb/sq.ft Pwr loading: 9.79 lb/hp Gross wt: 2300 lb Empty wt: 1400 lb Equipped useful load: 837 lb Payload max fuel: 459 lb Range max fuel/75% pwr: 641 nm/4.3 hr Range max fuel / 55% pwr: 688 nm/ 5 hr Service ceiling: 20,000 ft 75% cruise: 149 kt 55% cruise: 139 kt Stall: 49-54 kt 1.3 Vso: 64 kt ROC: 1350 fpm Min field length: 600 ft Fuel cap: 240/378 lb Undercarriage: Fixed tail / oleo Produced: 1976-88
M-5-250C Undercarriage: conv. oleo Produced: 1975 Engine: Franklin TO-350, 235 hp TBO: 1500 hr Prop: C/S Wingspan: 30’10” Wingtip: Droop
The first Maule production model, known as the Jetasen M-4 was delivered in April 1962, constructed in Moutrie, Georgia. Originally designed as a homebuilt in the USA in the late 1950’s, it was developed until it has become a commercially-built aeroplane.
The Maule is a four seat, high wing, tail wheel monoplane, designed to operate in and out of confined airstrips. The excellent short field performance is obtained by the unusually high-lift capability flaps and the thick high-lift aerofoil of the wing. The welded steel-tube fuselage is covered with fiberglass, and the shortspan wing is all-metal with a thick, high-lift airfoil. The airplane accomplishes its short-field performance with two-position flaps of an unusually high-lift capability and without the elaborate spoilers, slots, and other items normally associated with STOL design.
The fuselage is fairly wide giving a cabin dimension of 3 ft 6 ins which comfortably accommodates two adults in side-by-side seating. There is a door either side for the two front seats, as well as one on the starboard side for the rear seats. The baggage locker has its own door but this cannot be opened without the rear door being opened as well. The all-metal wings have down swept tips, strengthened centre-section so that floats can be fitted; other optional extras also fitted in¬clude a top and bottom strobe light and a glider tow hook. The tailplane is covered in a form of fibre-glassed linen that is virtually rot-proof. The fuel is contained in two, 18 Imp.G tanks in the inboard section of each wing.
First flying in 1960, the original M-4 was powered by a 145-hp O-300 Continental engine, and in 1965, the Rocket entered production with a 210-hp Continental powerplant and a constant-speed propeller. The Astro-Rocket was a deluxe version of the Jetasen, housing a 180-hp Franklin. In 1967, the Strata-Rocket was introduced into the line. Basically similar to the Rocket, it was powered by a 220-hp Franklin. All aircraft mentioned shared the same M-4 designation.
In the 1960s Servicios Aereas De America Sa serviced and repaired aircraft and engines, but undertook license-manufacture of a higher-powered Maule M-4, developed specially for Mexican conditions and called Cuauhtemoc M-1. In 1964 Servicios de America began production in Mexico City as the Cuauhtemoc M-1. Mexican materials were used and a 180 hp Lycoming engine. Delivery was taking 30 days and priced at US$12,600.
M-4 Jetasen Engine 145-hp O-300 Continental Gross wt. 2,100 lb Empty wt. 1,100 lb Fuel capacity 42 USG Top speed 157 mph Stall 40 mph Initial climb rate 700 fpm Ceiling 12,000 ft Range 750 miles Takeoff distance (50′) 585 ft Landing distance (50′) 600 ft Seats 4
M-4 Rocket Engine 210-hp IO-360 Continental Gross wt. 2,100 lb Empty wt. 1,190 lb Fuel capacity 42 USG Top speed 170 mph Cruise mph 165 Stall 40 mph Initial climb rate 1,250 fpm Range 680 miles Ceiling 18,000 ft Takeoff distance (50′) 585 ft Landing distance (50′) 600 ft Seats 4
M-4 Astro-Rocket Engine: Franklin 6A-335-B1A, 180 hp Double cargo door
M-4 Strata-Rocket Engine: Franklin 6A-350-C1, 220 hp
M-4-180C Gear: conv. oleo Produced: 1970-71 Engine: Franklin O-335, 180 hp TBO: 2000 hr Prop: C/S Wingspan: 30’10” Wingtip: Droop
M-4-210 Rocket Engine: Cont IO-360-A, 210 hp TBO: 1500 hr Prop: C/S Wingspan: 30’10” / 9.40 m Length: 22 ft 0 in / 6.71 m Empty weight: 1220 lb / 553 kg MTOW: 2300 lb / 1043 kg Max cruise 75%: 143 kt / 165 mph / 265 kph ROC SL: 250 fpm / 380 m/min Service ceiling: 18,000 ft / 5500 m Range std fuel: 590 nm / 680 mi / 1090 km Seats: 4 Bagage capacity: 100 lb / 45 kg Cabin length: 8 ft 4 in / 2.54 m Cabin width: 3 ft 6.5 in / 1.08 m Cabin height: 3 ft 10.5 in / 1.18 m Gear: conv. oleo Wingtip: Droop Produced: 1965
M4-210C Engine: Continental IO-360, 210 hp TBO: 1500 hr Prop: CS Wing span: 30 ft 10 in Length: 22 ft 9 in Empty wt: 1300 lb Max wt: 2300 lb Prop: McCauley CS Fuel cap: 36 Imp.G Cruise 75% pwr: 125 kt Undercarriage: Oleo / tail wheel Wingtips: Drooped Produced: 1965-73
M-4-220C Gear: conv. oleo Produced: 1967-73 Engine: Franklin O-350, 220 hp TBO: 1500 hr Prop: C/S Wingspan: 30’10” Wingtip: Droop
SADASA Cauchtemoc M-1 Engine: Lycoming O-360-A, 180 hp
All Aero 