A single-seat very-light multipurpose pusher monoplane (first flown in 1990 as MAI-89 prototype), also available in autogyro and training glider forms.
1980->
Moscow Aviation Institute / MAI
The Moscow Aviation Institute (MAI) was founded in 1930 on the basis of the aeromechanical faculty of the Moscow National Technical University “Bauman” (MGTU), becoming independent from it due to the wide importance that, since then, the aviation in the Soviet Union. It began with two faculties, aircraft construction and engine construction, since then it has been the most important aeronautical academic institution in the entire region, becoming a leader both in the scientific field, being the first to offer science chairs. aeronautics and training its own teachers and doctors who would make up the university boom, as well as technical-industrial, this is confirmed by the fact that it is the only university in the world that has launched its own aircraft on the market, built by its professors and students since 1932, when the MAI set up its own aircraft construction office.
After the Second World War the MAI expanded its academic and scientific interests, a new teaching system was developed, faculties were added in all aeronautical fields, as well as in physical-mathematical sciences, electronics and robotics. The student campus was built with more than 35 buildings, aeronautical infrastructure, workshops and laboratories were acquired, as well as the aerospace faculty, and in this way the MAI obtained the category of technical university. In 1979, artificial satellites ” Radio ” and ” Cosmos ” were launched into space, built with the participation of a large delegation from the MAI.
Although it is true in Soviet times the MAI as a national university maintained a margin of military defense, together with the state and the armed forces, always collaborating with the country, the university has also specialized its engineering in the commercial and experimental field.
The Moscow Aviation Institute (Russian: Московский авиационный институт (МАИ)) is a Russian university located in Moscow dedicated to the study of everything related to the aeronautical and aerospace industry. However, education is currently multidisciplinary and teaching and research programs are offered in multiple scientific and technological fields.
Over the years, the university grew to become the largest aerospace engineering teaching center in Russia, and one of the most prestigious universities in the world. More than 130,000 students, including 1,000 international students from 40 countries, have graduated from MAI after its founding in 1930.
In 1982 by the order of Ministry of Aircraft Industry the Design Bureau was transformed into a branch-wise experimental students aircraft construction design bureau of the MAI. The work was carried out by professional engineers. If necessary the co-workers from among the MAI students and teachers and also from among the workers of the industry were invited. The production facility of the MAI aircraft development plant (EOZ) in the experimental development shop (shop № 3) are manned by qualified technicians. The OSKBES work on the experimental aircraft engineering constantly received high estimations of the industry. Their technical novelty and utility are confirmed by nine Introduction Certificates and more than twenty Invention Certificates. By the end of 1980s six experimental aircraft of different types were designed and built: Kvant, Elf-D UAV, PS-01 small-sized UAV, Elf, Photon and Yunior aircraft.
The basic structure, address and the industrial areas occupied by it in the OSKBES MAI have remained the same. The EOZ MAI (shop № 3) and the MAPO (Moscow aircraft building plant) were used as an industrial base. On July 27, 1992 the application on realization the inspection work in the OKB MA for reception the certificate for the right to develop the civil aircraft engineering was sent to the Aviaregister of the MAK and the Air Industry Department of the Ministry of Industry of Russian Federation. It was made on behalf of the “Aviatika” joint-stock company. According to the inspection results the Aviaregister of the MAK issued Certificate № R-9 to the “Aviatika” joint-stock company with the right to develop light civil aircraft. It was on February 17, 1993.
Aircraft designed and developed at OSKBES include:
A single-seater Aviatika-MAI-890 aircraft — passed certification, had a temporary Certificate of a type of 31 March 1994 № 52В-890, valid till 1 April 1995, is series produced by the RAC “MiG”; A two-seater Aviatika-MAI-890U aircraft is serially produced by the RAC “MiG”; An agricultural Aviatika-MAI-890SKh aircraft is serially produced by the RAC “MiG”; A single-seater Aviatika-MAI-900 aerobatics (“Akrobat”)’ A two-seater Aviatika-MAI-910 with wings, folding on the ground; An Aviatika-MAI-920 glider; A single-seater Aviatika-MAI-890A autogyro, a pre-production model at the stage of flying test. The basis for the “Aviatika” aircraft manufacture at the MAPO plant is the License Agreement concluded by this plant with the “Aviatika” joint-stock company on 10 April 1995 (contract № 4276).
In 1997 Aviatika withdrew from the Design Bureau of Moscow Aviation Institute (Aviatikas) program, after which the manufacturer of Aviatika lightplanes became known as KB MAI.
The personnel of the OSKBES have continued to work in the field of light civil aircraft together with the MAPO MIG.
In April 27, 1998 the Aviaregister of Interstate Aviation Committee issued a Design Organization Certificate R-52 of the developer of light civil aircraft.
29 September 1999 eight members of our design bureau, Moscow Aviation Institute and RAC “MIG” were rewarded by “State Prize of the Russian Federation in science and technology” for designing and development of light multipurpose airplanes in a serial production. They are:
OSKBES MAI Chief Designer K. Zhidovetskiy (posthumously); OSKBES MAI Deputy Chief Designer (after the death of K. Zhidovetskiy — Chief Designer) N. Goryunov; OSKBES MAI Deputy Chief Designer V. Demin; OSKBES MAI Deputy Chief Designer V. Feigenbaum; Rector of MAI A. Matveyenko; Manager of MAI Experimental Plant P. Ogadzhanov; General Manager of RAC “MIG” plant G. Nemov; Deputy Manager of RAC “MIG” O. Chukantsev.
Autogyro MAI-205 made the first flight in 2001, chief designer Andrey Zorin.
In 2002 OSKBES MAI has started designing a new plane MAI-223. This plane made the first flight in 2004.
In 2003 OSKBES MAI started to work on different aircraft, airships and autogyros. It designed and produced gondolas, nacelles, fly-by-wire power plant controls and empennages of NPO “RosAeroSystems” airships Au-30 and Au-12M.
The design and development of Autogyro MAI-208 was started in 2006. The first MAI-208 is undergoing testing. OSKBES MAI presented MAI-208 at the 2nd International exhibition of the helicopter industry “HeliRussia-2009” (21…23 May 2009, Moscow). The new autogyro has caused the big interest of visitors and the press.
July 1, 2008 Vadim Demin was appointed Chief Designer of OSKBES MAI. The same year the design office has started working on a new multi-purpose four-seat twin engine aircraft MAI-407.
In 2009 OSKBES MAI started designing a new training glider MAI-227.
Volokolamskoe Shassé,
Building 4,
Moscow,
Russia,
125993
Faculties and Departments of MAI:
High school.
Faculty № 1. Aeronautical Engineering.
Faculty №2. Aircraft Engines
Faculty №3. Computer Science and Navigation System
Faculty №4. Radio and Electronics
Institute of Economic Engineering
Faculty №6. Aerospace
Faculty №7. Robotics and Intellectual Systems
Faculty №8. Applied Physical-Mathematical Sciences
Faculty №9. Applied Mechanics
Faculty №10. Humanities (Social Engineering)
Military Institute
Moshier Aurora 400-C
A four-seat VTOL aircraft of unusual configuration.
Moshier Technologies Corporation
USA
Founded 1986 to develop Aurora 400-C four-seat VTOL aircraft of unusual configuration.
Morrisey OM-1 / OM-1-2 Bravo II
Designed by Bill Morrissey, the Bravo originated as the single-place Model OM-1, which became the two-place Bravo II in 1982. Modification was simple – no alterations to the basic structure. Instrument panel and windscreen were moved forward and the canopy extended.
Gross wt: 1700lbs
Empty wt: 965 lbs
Fuel cap: 35 US Gal
Wing span: 26.5’
Length: 21.5’
Top speed: 155mph
Cruise 75%: 145mph
Stall: 57mph
Climb rate: 1500fpm
T/O run: 400ft
Ldg roll; 700ft
Range: 550mls + res
Morrisey Aircraft
Morrisey Aircraft was founded in 1949 by former Douglas test pilot William J. Morrisey at Long Beach, California, to market the Model 1000 Nifty tandem two-seater first flown 1948. Initially flown with Continental A65 and later with Continental C90. Reorganized as Morrisey Aviation Inc. at Santa Ana, California, and in 1958 began delivery of series production aircraft as Morrisey 2150 with 150 hp Lycoming engine. Rights in the 2150 acquired by Shinn Engineering and later Varga Aircraft, which produced its Kachina version. Morrisey Aircraft Company reestablished in Las Vegas, producing single-seat Bravo in 1981 for construction from plans, and more recently has offered Morrisey 2000 two-seater in certificated and kit forms as modern development of Nifty.
1996: PO Box 27889, Las Vegas, NV 89126, USA.
Morava Zlin Aero Savage
Designed in Italy by Pasquale Russo with some help from Bonaldo, Franchini and Vizzini in 1997, and manufactured in the Czech Republic by the Morava Zlin Aero, at their Otrokovice factory, is a J3 Cub lookalike. The Savage is a single-engine, high-wing, two-seater tandem microlight aircraft.
With a Rotax 912S 100 hp performance is lively. There is ample baggage space behind the front seat, the one piece door hinges up and fastens on and the aircraft can be flown with the door open. There are features such as sight glasses in the wing root to view the tank contents, an effective flap to 35 degrees, disk brakes and electric start. With a comfortable 95 kts cruise, the large balloon tyre undercarriage and fully castoring tailwheel allows for some off runway outlandings.
Available as a basic kitset through to a fully assembled option, the type is powered by the 100 hp Rotax 912S and turns a 183 cm propeller. An interesting feature of the Zlin tube framed aircraft is the option to pressurise the frame with an inert gas. Should the frame crack and the gas leak out, a drop in pressure will be detected through a gauge on the instrument panel. The two spar (foldable) wing, with flaps, is fabric covered and contains two 34 litre fuel tanks.
The Zlin Savage Cub fleet includes the iCub (with docked Apple iPad) and its Bobber open-frame, totally customizable variant.
Savage
Engine: Rotax 912S 100 hp
Stall: 31 kt / 36 mph / 58 kmh
Cruise: 92 kt / 106 mph / 170 kmh
VNE: 111 kt / 127 mph / 205 kmh
Empty Weight: 288 kg / 635 lbs
MTOW Weight: 560 kg / 1235 lbs
Climb Ratio: 800 ft/min / 4,8 m/s
Take-off distance (50ft obstacle): 660 ft / 200 m
Landing distance (50ft obstacle): 520 ft / 160 m
Mooney M20 / M21
After the Mite and a corporate shuffle, the company moved from the original Kansas facility to Kerrville, Texas, and re-emerged one year later with a four seater called the Mark 20. Pug Piper offered to buy it and Mooney regrets not taking Piper’s marketing know how. The first M20 was built in 1955 and kept the Mite’s most distinctive features: the high aspect ratio wing; squared off wingtips; manually activated, stubby, trailing beam landing gear; and the all moving tail assembly with its forward ¬swept trailing edges.
First flown on August 10, 1953 with a Lycoming O-320 engine, the 150 hp engine was upgraded to O-360-A 180 hp as the M-20A, improving the Mark 20’s takeoff, climb and cruise performance with an acceptably small sacrifice in economy. Mooney owners could count on a cruise speed of 150 knots at 75 percent power, making the Mark 21 the fastest airplane for the horsepower in its class. It wasn’t long before Mooneys were outselling all other single engine retractables, an honor they would hold until the ascendancy of the Piper Arrow in the late 1960s. This all-wooden wing aircraft was in production until 1961 when the all-metal M20B was introduced. This was superseded by the M20C Mk2l in 1962.
From the M20C the basic structure has been all-metal but with the unusual feature of a welded steel tube frame for the cabin area, covered in sheet light alloy, and the more conventional semi-monocoque construction aft of the rear seats. The wing is made as a single full-span unit of considerable strength to support the fuselage, and the entire empennage, tailplane, fin, rudder and all, pivots to provide a low-drag elevator trim.
In 1963, Mooney introduced two variations on the theme: the Master (M 20D), a fixed gear fixed pitch prop less sophisticated (read cheap) airplane that could be used for training; and the Super 21 (M 20E), a Mark 21. The Master was actually an attempt to generate brand loyalty in the flight training stratum. The M20E Super 21 with a 200-hp injected Lycoming giving a maximum cruise of 187 mph. In 1965, Mooney offered an optional electrically actuated retractable landing gear system. By 1965 Mooney was selling almost 700 aircraft that year, with the M20F Executive with stretched fuselage offered a year later in 1966. It was essentially a Super 21 with a longer fuselage and a third side window.
Square windows were introduced in 1967 for O-360-AID-powered Ranger and Executive, and M20J or Model 201, both of which had Lycoming IO-360-A1B6D engines.
The Executive has an extra 10 inches of length and extra window in the aft cabin. The Executive has a gross weight of 2,740 pounds, 165 pounds almost one passenger’s worth more than the Chaparral and the Ranger. The empty aircraft weighs 40 pounds more than its 200 hp cousin, the Chaparral, however, so the useful load difference is whittled to 125 pounds. Engine: Lycoming IO 360 AlA. The advertised service ceiling of an Executive is 18,800 feet.
The Executive’s larger, airier cabin, higher gross weight and increased fuel capacity proved to be a popular combination, and it wasn’t very long before Mooney came up with yet another stretch job, this time on the ubiquitous Mark 21, resulting in the Statesman.
Only 196 of the M20G Statesman model were built in 1968 and 1969, as basically an M20F powered by only a 180 hp Lycoming instead of the normal 200 hp, with a consequent lower gross weight. But the longer fuselage (with its built in invitation to greater load factors) didn’t fare as well with the smaller, 180 hp engine, and most people opted for the higher powered version.
Beginning in 1968 there was some name changing: the Mark 21 became the Ranger, the Super 21 became the Chaparral. The standard body airplanes now had a one piece windshield, even nicer instrument panels, and paint designs that actually complemented their lines. Electric gear retraction was standard equipment, the hand pump arrangement that lowered the flaps had given way to a simpler electric system.
The Ranger is recognizable by looking first at the chin beneath the propeller spinner. Executives and Chaparrals, both with Lycoming IO 360 A1A engines, have a filter housing that is flush with the cowling, but the air filter on the Ranger, powered by the Lyc O 360 A1D, is set up with its lower edge jutting out just a bit. Otherwise, a Ranger is exactly like a Chaparral, which is, with the exception of 10 inches of fuselage length, exactly like an Executive. All three air¬planes have the same wingspan: 35 feet.
After the take-over by Republic, the M20 underwent a major efficiency and drag reduction programme to produce the M20J. The last of the M20Cs was built in 1978, a year after the popu¬lar 200-hp M20J was introduced – known as the 201 because the cruise speed was 201 mph. Late in 1976, Mooney presented the Model 201 as a new design that boasts a significant speed increase over the Mooney Executive. The same size as the Executive and, like it, powered by a 200 hp Lycoming engine, the 201 is capable of a 174 knot (201 mph, hence the name) top speed, the increase a result of a very effective aerodynamic cleanup.
The early 201s had the Vne upped from 173 kt to 195 and the Vno from 151 to 173 kt by removing the propeller high pitch (full coarse) stops. Roy Lopresti, who did the aerodynamic clean-up on the Grumman range to get the excellent figures for the Tiger and Cheetah, joined Mooney in 1975 work on the Mooney M20F Executive to turn it into the Mooney M20J Model 201. It’s careful attention to detail plus striking a balance between cost and benefit. Flush riveting is used extensively both above and below the wing back to the rear spar. And also on the fuselage from the nose cowl back to the widest part just abeam of the front seats. Careful fitting of all doors and windows and the increased rake of the windshield over that on earlier Mooneys all add up. The Mooney fuselage is a welded steel tube and underneath the starboard wing a little bump protrudes that is the new OAT sensor replaces the old temperature probe usually seen sticking out from the windshield on other aircraft. The trim system is unique on light aircraft in that the whole tail assembly pivots for trimming – rudder and all. This was a design feature of all Mooneys designed by Al Mooney. On this area Mr Lopresti limited his efforts to ensuring good sealing around all gaps and joins. The 201 was a new airplane, an addition to the Mooney line. The 200 hp Executive re-mains a part of it, although many observers thought the 201 would replace the Executive, which has the same engine, wing and fuse¬lage.
1978 updates for the 201 incorporate a revised power console with vernier push pull controls in place of the power levers of yore. There’s also a re¬vised gear extension system with a cable and pull handle, replacing the crank that was always in semi eclipse, half covered by the pilot’s seat. They’ve also relocated the fuel selector to a position just forward of the front seats and left of the centerline, which should now make it easier to see and to reach.
The M20K 231/252 first appeared in 1979 and differed from the 201 in that it had a Conti¬nental 210-hp. There’s a prop extension on the front of the 231 longer engine, and the 231 has a longer and very distinc-tive nose. Two landing lights are located in the chin of the new cowling, and the cowl flaps are larger. There’s a new wing root fillet, and non ic¬ing fuel vents. The fuel filler caps have been placed farther out on the wingand the tanks are bigger, with a usable capacity of 75 USG.
A dorsal fin has been added at the rear, including a scoop for cabin air. This new ventilation system eliminates the scoop right atop the cabin.
In 1988 Mooney teamed up with Porsche and produced forty-one 217-hp Porsche engined aircraft, the M20L. The incredibly quick, big-block Mooneys began rolling off the line in 1988 with the 220-knot, 270-hp M20M Bravo, followed by the 280-hp M20R Ovation in 1994. The M20M model was available in two versions. The MSE has the four-cylinder Lycoming O-360 and the TLS (Turbo Lycoming Sabre in marketing parlance) has more power.
Four-seat Allegro (former M20J) production ended 1998, and Encore (M20K) became built in batch orders. Bravo (M20M) four-seater has turbocharged TI0-540-AF1A and was previously known as TLS (first appeared 1989), while Ovation (M20R) first flew May 1994 and has Teledyne Continental IO-550-G5B engine.
Mooney’s next model was the 244-hp M20S Eagle, awarded type certification by June 1997. The Eagle was marketed as a high performance model combining the longer fuselage design with a 244 hp / 182 kW Continental IO-550 and two blade prop.
Certification to Federal Aviation Administration USA 2A3:
M20C
1852, 1940 to 3466 (1962-66)
20-1186 and up (1977-1978)
M20E
1964-65
M20F
22-013 and up (1974)
M20G
680001 to 680164 (1968)
M20J
24-0084, 24-0764 to 24-1037 (1979-1980)
24-3079 and up (1989-1990)
M20M
1991-2003
M20R
All
Specifications:
M20
Engine: Lycoming O-320
M20A
Engine: Lycoming O-360A1A, 180 hp
Cruise: 165 mph
Seats: 4
M20C Mk.21 / Aerostar Ranger
Engine: Lycoming O-360-A1D, 180 hp
Wingspan: 35 ft 0 in / 10.67 m
Length: 24 ft 1 in / 7.34 m
Cabin length: 8 ft 8 in / 2.64 m
Cabin max width: 3 ft 4.5 in / 1.04 m
Cabin max height: 3 ft 8.5 in / 1.13 m
Baggage compartment: 13.5 cu.ft / 0.38 cu.m
Empty weight: 1525 lb / 691 kg
MTOW: 2575 lb / 1168 kg
Max speed SL: 153 kt / 176 mph / 283 kph
ROC SL: 1000 fpm / 305 m/min
Service ceiling: 19,500 ft / 5743 m
Range 45min res: 1001 mi / 1610 km
Seats: 4
Ranger M20C
Engine: 1 x Lycoming O-360-A1D, 180 hp
Seats: 4
Wing loading: 15.4 lb/sq.ft
Pwr loading: 14.3 lb/hp
Gross wt: 2575 lb
Empty wt: 1525 lb
Equipped useful load: 961 lb
Payload max fuel: 649 lb
Range max fuel/75% pwr: 694nm/4.8hr
Range max fuel / 55% pwr: 799 nm/ 6.6 hr
Service ceiling: 16,500 ft
75% cruise: 143 kt
55% cruise: 122 kt
Stall: 49-58 kt
1.3 Vso: 64 kt
ROC: 800 fpm
Min field length: 1550 ft
Fuel cap: 312 lb
Undercarriage: retractable.
M20 Ranger
Engine: Lycoming 0 360 AlD, 180 hp
TBO: 2,000 hrs
Prop: constant speed, two blade, 74 inch dia
Length: 23 ft. 2 in
Height: 8 ft. 4 in
Wingspan: 35 ft
Wing area: 174 sq. ft
Wing loading: 15.11 lb./sq.ft
Seats: 4
Empty weight, IFR equipped: 1,606 lbs
Useful load, IFR equipped: 969 lbs
Equipped payload (750 miles fuel, 75 % power): 715 lb
Gross weight: 2,575 lbs
Power loading: 14.2 lb/hp
Fuel capacity: 52 gals./312 lbs
Minimum runway requirement: 1,550 ft
Rate of climb: 800 fpm
Service ceiling: 16,300 ft
Maximum speed: 147 knots
Cruise (75 % @ 10,000 ft): 143 knots
Economy cruise (57 % @ 10,000 ft.): 123 knots
Maximum range (75% power): 948mi
Stall speed, clean: 58 knots
Stall speed, landing config: 49 kts
Cabin width (elbow to elbow): 43.5in.
Ranger
Engine: Lycoming O 360 A1D, 180 hp
TBO: 2,000 hrs
Propeller: Hartzell two blade, constant speed, 74 in
Length: 23 ft. 2 in
Height: 8 ft. 4 in
Wingspan: 35 ft
Airfoil: NACA 632 215 at root, NACA 641 412 at tip
Aspect ratio: 7.338
Wing area: 167 sq. ft
Wing loading: 15.4 lb/sq.ft
Seats: 4
Empty weight: 1,525 lbs
Useful load: 1,050 lbs
Payload with full fuel: 738 lbs
Gross weight: 2,575 lbs
Power loading: 14.3 lb/hp
Fuel capacity: 52 USG/312 lbs
Baggage capacity: 120 lbs
Baggage area: 15 cu.ft
Minimum runway requirement: 1,550 ft
Rate of climb: 860 fpm
Service ceiling: 19,500 ft
Maximum speed: 153 knots
Cruise (75% @ 10,000 ft.): 143 knots
Economy cruise (65% @ 10,000 ft.): 135 knots
Range @ max cruise (45 min res): 684 nm
Range @ economy cruise (45 min res): 745 nm
Duration @ max cruise (no res): 5.5 hrs
Stall speed (clean): 58 knots
Stall speed (gear and flaps down): 49 knots
M 20D Master
Simplified M20C
Undercarriage: fixed
M20 Chaparral / M20E Super 21
Engine: Lycoming IO 360 A1A, 200 hp
TBO: 1,600 hrs
Propeller: Hartzell two blade, constant speed, 74 in
Length: 23 ft. 2 in
Height: 8 ft. 4 in
Wingspan: 35 ft
Airfoil: NACA 632 215 at root, NACA 641 412 at tip
Aspect ratio: 7.338
Wing area: 167 sq. ft
Wing loading: 15.4 lb/sq.ft
Seats: 4
Empty weight: 1,600 lbs
Useful load: 975 lbs
Payload with full fuel: 663 lbs
Gross weight: 2,575 lbs
Power loading: 12.8 lb/hp
Fuel capacity: 52 USG/312 lbs
Baggage capacity: 120 lbs
Baggage area: 15 cu.ft
Minimum runway requirement: 1,550 ft
Rate of climb: 1,125 fpm
Service ceiling: 21,200 ft
Maximum speed: 165 knots
Cruise (75% @ 10,000 ft.): 158 knots
Economy cruise (65% @ 10,000 ft.): 150 knots
Range @ max cruise (45 min res): 534 nm
Range @ economy cruise (45 min res): 700 nm
Duration @ max cruise (no res): 4.1 hrs
Stall speed (clean): 58 knots
Stall speed (gear and flaps down): 49 knots
Cabin width (elbow to elbow): 43.5in
Seats: 4
M20F / Aerostar Executive
Engine: Lycoming IO-360-AlA, 200 hp at 2700 rpm
TBO: 1600 hours
Prop: Hartzell 74” Constant speed
Power Loading: 13.7 lbs/hp
Wingspan: 35 ft
Wing Area: 167 sq.ft
Airfoil: NACA 632 215 at root, NACA 641 412 at tip
Wing Loading: 16.4 lbs./sq.ft
Length: 24 ft
Height: 8’4”
Seats: 4
Baggage Capacity: 120 lbs
Gross Weight, Normal Category: 2,740 lbs
Empty Weight: 1,640 lbs
Equipped payload (750 miles fuel, 75 % power): 752 lb
Fuel Capacity, Standard Tanks: 64 USG / 384lb
Payload max fuel: 627 lb
Max speed; 185 mph
Cruise Speed (75% pwr): 177 mph
Cruise 67% pwr: 171 mph
55% cruise: 130 kt
1.3 Vso: 70 kt
Maneuvering Speed: 135 mph
Stall Speed, Clean: 68 mph
Stall Speed, (gear and) full flaps: 62 mph
Takeoff Distance: 834 ft
Landing Distance: 785 ft
Takeoff, over 50ft. obstacle: 1,384 ft
Landing, over 50 ft. obstacle: 1,786 ft
Best Rate of Climb, S.L.: 960 fpm
Service Ceiling: 18,800 ft
Max. Endurance Range, Standard Tanks, No Reserve: 8:41 hours; 1,060 st.mi.
Maximum speed: 161 knots
Cruise (75% @ 10,000 ft.): 150 knots
Economy cruise (65% @ 10,000 ft.): 141 knots
Range @ max cruise (45 min res): 649 nm
Range @ economy cruise (45 min res): 834 nm
Duration @ max cruise (no res): 5.1 hrs
Range 75% pwr, 45 min res: 977 sm
Average Fuel Consumption, Normal Cruise: 10.2 gph
Cabin width (elbow to elbow): 43.5in
M20G Statesman
Similar to Ranger, longer fuselage, extra window
M20J 201
Engine: 1 x Lycoming IO-360-AB6D, 200 hp
TBO: 1800 hrs
Prop: McCauley 2 blade, constant speed 74 in
Seats: 4
Length: 24.7 ft
Height: 8.3 ft
Wingspan: 35 ft
Wing area: 170 sq.ft
Wing aspect ratio: 7.4
Max ramp wt: 2740 lbs
Max take off wt: 2740 lbs
Standard empty wt: 1640 lbs
Max useful load: 1069 lbs
Max landing wt: 2740 lbs
Baggage cap: 130 lbs
Wing loading: 16.1 lbs/sq.ft
Power loading: 13.7 lbs/hp
Max useable fuel (std): 64 USG, 384 lbs
Climb rate: 1030 fpm @ 89 kts
Climb gradient: 694 ft/nm
Rate of climb @ 8000 ft: 630 fpm
Service ceiling; 18,800 ft
Max speed: 185kts
Cruise @ 65% power @ 8,000ft: 157kts
Fuel flow @ 65% power @ 8,000ft: 56 pph
Endurance @ 65% power @ 8,000ft: 6.6 hr
Stalling speed clean: 63 kts
Stall speed flaps/gear down: 55 kts
T/O 50 ft: 1302 ft
Ldg 50 ft: 1700 ft
Turbulent air penetration speed: 120 kts
Retractable undercarriage.
M20J Allegro
1978 201
Engine: Lycoming IO-360-A3B6D, 200 hp
TBO: 2000 hr
Propeller: Const. spd.
Landing gear type: Tri/Retr
Gross weight: 2740 lb
Empty weight: 1640 lb
Useful load: 1100 lb
Fuel: 64 USG
Wingspan: 35 ft
Overall length: 24 ft. 8 in
Height: 8 ft. 4 in
Wing area: 167 sq. ft
Seating capacity: 4
Cabin width: 43.5 in
Cabin height (in.): 44.5
Baggage capacity (lbs.):120
Cruise speed 75% power: 169 kt
Cruise speed 65% power: 156 kt
Max range (w/ reserve) 75% power: 835 nm
Max range (w/ reserve) 65% power: 881 nm
Fuel consumption 75% power: 10.8 USgph
Fuel consumption 65% power: 9.7 USgph
Stall speed (gear, flaps down): 55 knots
Best rate of climb: 1030 fpm
Service ceiling: 18,800 ft
Takeoff ground roll: 913 ft
Landing ground roll: 770 ft
Mooney 205
Engine: Lycoming IO-360-A3B6D, 200 hp@2700 rpm @SL
TBO: 2000 hr
Fuel type: 100LL
Propeller: McCauley CS
Landing gear type: Tri/Retr.
Max ramp weight: 2740 lb
Gross weight: 2740 lb
Max landing weight: 2740 lb
Empty weight, std: 1695 lb
Useful load, std: 1045 lb
Payload, full std. fuel: 661 lb
Usable fuel, std: 64 USG
Oil capacity: 8 qts
Wingspan: 36 ft. 1in
Overall length: 24 ft. 9 in
Height: 8 ft. 4 in
Wing area: 174.8 sq. ft
Wing loading: 15.7 lbs./sq. ft
Power loading: 13.7 lbs./hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 1
Cabin width: 43.5 in
Cabin height: 45 in
Baggage capacity:120 lbs /13.5 cu. ft
Cruise speed 75% power: 171 kt
Cruise speed 65% power: 162 kt
Max range (w/ reserve) 75% power: 740 nm
Vs: 61 kt
Vso: 54 kt
Best rate of climb: 1050 SL fpm
Best rate of climb, 8,000 ft: 700 fpm
Service ceiling: 18,600 ft
Takeoff ground roll: 900 ft
Takeoff over 50-ft. obstacle: 1700 ft
Landing ground roll: 677 ft
Landing over 50-ft. obstacle: 1600 ft
M20K Turbo 231
First built: 1978
Engine: 1 x Continental TSIO-360-GB-1, 210 hp
TBO: 1800 hrs
Fuel; 100/100LL
Prop: McCauley 2 blade, constant speed 74 in
Seats: 4
Length: 25.4 ft
Height: 8.3 ft
Wingspan: 36.1 ft
Wing area: 174.8 sq.ft
Wing aspect ratio: 7.4
Max ramp wt: 2900 lbs
Max take off wt: 2900 lbs
Standard empty wt: 1800 lbs
Max useful load: 1100 lbs
Payload full std fuel; 462 lbs
Max landing wt: 2900 lbs
Wing loading: 16.6 lbs/sq.ft
Power loading: 13.8 lbs/hp
Max useable fuel: 453 lbs
Fuel Capacity (std); 78.6 US Gal
Usable Fuel (std); 75.6 US Gal
Climb rate: 1080 fpm @ 96 kts
Climb gradient: 675 ft/nm
Rate of climb @ 8000 ft: 1020 fpm
Certificated (& service) ceiling; 24,000 ft
Turbulent air penetration speed: 119 kts
Retractable undercarriage
Wheel base; 5 ft 11 9/16 in
Wheel Track; 9 ft 3/4 in
Wheel Size; Nose; 5.00×5 Mains; 6.00×6
Cabin Length; 114 in
Cabin Width; 43.5 in
Cabin Height; 44.5 in
Baggage Capacity; 130 lbs
Trim; Stabilizer.
Max Level Speed; 201 kts
Never Exceed Speed; 196 kts.
Cruise 75%, 24,000 ft: 192 kt
Cruise 65%, 24,000 ft: 178 kt
Cruise 55%, 24,000 ft: 163 kt
Range 75%, 21,000 ft: 1000 nm
Range 65%, 9,000 ft: 1080 nm
Range 55%, 12,000 ft: 1170 nm
Stall Speed Flaps up/gear up; 61 kts
Stall Speed Flaps down/ gear down; 57 kts
Best Angle of Climb; 71 kts
Take-off Ground Run; 1250 ft
Take-off 50 ft; 2250 ft
Landing Ground Roll; 1150 ft
Landing over 50 ft; 2300 ft
M20K Encore 1998
Engine: Lycoming IO-360-A1B6, 200 hp
TBO: 2000 hr
Propeller: Const. spd.
Landing gear type: Tri/Fixed
Gross weight: 2535 lb
Empty weight: 1576 lb
Useful load: 959 lb
Fuel capcity: 54 USG
Wingspan: 32 ft
Overall length: 25 ft. 2 in
Height: 9 ft. 10 in
Wing area: 128 sq. ft
Seating capacity: 4-5
Cabin width: 50 in
Cabin height: 46 in
Baggage capacity: 143 lb
Cruise speed 75% power: 130 kt
Cruise speed 65% power: 123 kt
Max range (w/ reserve) 65% power: 800 nm
Fuel consumption 75% power: 12.4 USgph
Fuel consumption 65% power: 11.0 USgph
Stall speed (gear, flaps down): 53 kt
Best rate of climb: 937 fpm
Service ceiling: 16,000 ft
Takeoff ground roll: 1067 ft
Landing ground roll: 623 ft
M20L
M20M Bravo
Engine: Lycoming TIO-540-A1FB, 270 hp
TBO: 2000 hr
Propeller: Const. spd.
Landing gear type: Tri/Retr.
Gross weight: 3368 lb
Empty weight: 2268 lb
Useful load: 1100 lb
Fuel: 89 USG
Wingspan: 36 ft. 1 in
Overall length: 26 ft. 9 in
Height: 8 ft. 4 in
Wing area: 174.8 sq. ft
Seating capacity: 4
Cabin width: 43.5 in
Cabin height: 44.5 in
Baggage capacity: 120 lb
Cruise speed 75% power: 220 kt
Cruise speed 65% power: 215 kt
Max range (w/ reserve) 75% power: 750 nm
Max range (w/ reserve) 65% power: 840 nm
Fuel consumption 75% power: 17.6 USgph
Fuel consumption 65% power: 16.6 USgph
Stall speed (gear, flaps down): 59 kt
Best rate of climb: 1230 fpm
Service ceiling: 25,000 ft
Takeoff ground roll: 1080 ft
Landing ground roll: 1200 ft
M20M MSE
Engine: Lycoming IO-360-A3B6D, 200 hp@2700 rpm@SL
TBO: 2000 hr
Fuel type: 100/100LL
Propeller type/diameter: McCauley CS
Landing gear type: Tri/Retr.
Max ramp weight: 2900 lb
Gross weight: 2900 lb
Landing weight: 2900 lb
Empty weight, std: 1726 lb
Useful load, std: 1174 lb
Payload, full std. fuel: 790 lb
Usable fuel: 64 USG
Oil capacity: 8 qts
Wingspan: 36 ft. 1 in
Overall length: 24 ft. 8 in
Height: 8 ft. 4 in
Wing area: 175 sq. ft
Wing loading: 16.6 lbs./sq. ft
Power loading: 14.6 lbs./hp
Wheel base: 6 ft
Wheel track: 9 ft. 2 in
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 1
Cabin width: 43.5 in
Cabin height: 44.5 in
Baggage capacity: 120 lb
Cruise speed 75% power @ 8,000 ft.: 168 kt
Cruise speed 65% power @ 8,000 ft.: 160 kt
Max range (w/ reserve) 75% power: 850 nm
Fuel consumption 75% power: 10.8 USgph
Fuel consumption 65% power: 9.1 USgph
Fuel consumption 55% power: 7.7 USgph
Vs: 62 kt
Vso: 58 kt
Best rate of climb: 1030 fpm
Best rate of climb, 8000 ft: 750 fpm
Service ceiling: 18,600 ft
Takeoff over 50-ft. obstacle: 1520 ft
Landing ground roll: 770 ft
Landing over 50-ft. obstacle: 1610 ft
M20M TLS
Engine: Lycoming TIO-540-AF1A, 270 hp
Vne: 195 kt
MAUW: 3368 lb
Max ldg wt: 3200 lb
Cruise: 220 kt @ 25,000 ft
Cruise: 200kt @ 12,000ft
Range IFR res: 1070nm.
M20R Ovation
Engine: 280-hp.
Length: 26.739 ft / 8.15 m
Height: 8.333 ft / 2.54 m
Wingspan: 36.089 ft / 11.0 m
Aspect ratio: 7.4
Wing area: 175.023 sq.ft / 16.26 sq.m
Max take off weight: 3367.0 lb / 1527.0 kg
Weight empty: 2268.9 lb / 1029.0 kg
Max. payload weight: 1144.4 lb / 519.0 kg
Landing speed: 59 kts / 110 km/h
Cruising speed: 190 kts / 352 km/h @ 9000 ft.
Initial climb rate: 1150 ft/min
Service ceiling: 20013 ft / 6100 m
Cruising altitude: 9006 ft / 2745 m
Wing load: 19.27 lb/sq.ft / 94.0 kg/sq.m
Range: 1129 nm / 2090 km
Endurance: 7 h
Crew: 1+3
1997 Ovation
Engine: Cont. IO-550G, 280 hp
TBO: 2000 hr
Propeller: Const. spd.
Landing gear type: Tri/Retr.
Gross weight: 3368 lb
Empty weight: 2225 lb
Useful load: 1134 lb
Fuel: 89 USG
Wingspan: 36 ft. 1 in
Overall length: 26 ft. 9 in
Height: 8 ft. 4 in
Wing area: 175 sq.ft
Seating capacity: 4
Cabin width: 42.5 in
Cabin height: 44.5 in
Baggage capacity: 120 lb
Cruise speed 75% power: 190 kt
Cruise speed 65% power: 182 kt
Max range (w/ reserve) 75% power: 935 nm
Max range (w/ reserve) 65% power: 1015 nm
Fuel consumption 75% power: 17 USgph
Fuel consumption 65% power:14 Usgph
Stall speed (gear, flaps down): 59 kt
Best rate of climb: 1200 fpm
Service ceiling: 20,000 ft
Takeoff ground roll: 900 ft
Landing ground roll: 1000 ft
2005 Mooney Ovation2 GX
Base Price: USD$418,150
Engine: Continental IO-550G, 280 hp@2500@SL
TBO hr: 2000
Fuel type: 100LL
Propeller diameter: 73 in
Landing gear type: Tri./Retr.
Max ramp weight: 3368 lb
Gross weight: 3368 lb
Landing weight: 3368 lb
Empty weight, std: 2205 lb
Useful load: 1163 lb
Payload, full std. fuel: 567 lb
Usable fuel, std: 89 USG
Oil capacity: 12 qts
Wingspan: 36 ft. 1 in.
Overall length: 26 ft. 9 in.
Height: 8 ft. 4 in.
Wing area: 174.5 sq. ft
Wing loading: 19.3 lbs./sq. ft
Power loading: 12.0 lbs./hp
Seating capacity: 4
Cabin doors: 1
Cabin interior length: 12.1 in
Cabin interior height: 3.7 in
Cabin interior width: 3.6 ft
Baggage capacity: 120 lb
Range (w/ res) 75% power @ 9,000 ft.: 970 nm
Range (w/ res) 55% power @ 9,000 ft.: 1240 nm
Cruise Speed (8000 ft.): 192 kts
Endurance (75%) (970nm@9000 ft.): 5.0 hr
Endurance (55%) (1240nm@9000 ft.): 7.9 hr
Best rate of climb (SL): 1250 fpm
Service ceiling: 20,000 ft
Vso: 60 kt
Takeoff ground roll: 900 ft
Takeoff over 50-ft. obstacle: 1700 ft
Landing ground roll: 1000 ft
Landing over 50-ft. obstacle: 1600 ft
2007 Mooney Ovation3
Base price: $469,000
Engine: Continental IO-550G, 310hp @SL
TBO: 2000 hr
Fuel type: 100/100LL
Propeller type: Hartzell CS/3-blade
Landing gear type: Tri./Retr
Max ramp weight: 3374 lb
Gross weight: 3374 lb
Landing weight: 3374 lb
Empty weight, std: 2267 lb
Useful load, std: 1107 lb
Useful fuel, std: 102 USG
Optional fuel: 130 USG
Payload, full std. fuel: 495 lb
Wingspan: 36 ft. 1 in
Overall length: 25 ft. 9 in
Height: 8 ft. 4 in
Wing area: 174.8 sq. ft
Wing loading: 19.3 lbs./sq.ft
Power loading: 10.9 lbs./hp
Seating capacity: 4
Cabin doors: 1
Cabin width: 43.5 in
Cabin height: 44.5 in
Cruise speed 75% power: 197 kt @8000 ft
Fuel consumption 75% power: 17.1 Usgph
Fuel consumption 45% power: 10.1 Usgph
Vso (kts.): 59
Best rate of climb, SL: 1300 fpm
Service ceiling: 20,000 ft
Takeoff distance: 900 ft
Takeoff over 50 ft. obstacle: 1620 ft
Landing distance: 1000 ft
Landing over 50 ft. obstacle: 1600 ft
2009 M20R Ovation 3
New price: $517,522
Engine: Continental IO-550G-A/P, 300 hp@SL
TBO: 2000 hr
Fuel type: 100LL
Propeller type: 3-blade, CS Hartzell
Landing gear type: Tri./Retr.
Gross weight: 3368 lb
Empty weight, std: 2261 lb
Useful load, std: 1107 lb
Usable fuel, std./opt: 100/300 USG
Payload, full std. fuel: 495 lb
Wingspan: 36 ft. 1 in
Overall length: 26 ft. 9 in
Overall height: 8 ft.3 in
Wing area: 175 sq. ft
Wing loading: 19.3 lbs./sq. ft
Power loading 10.86 lbs./hp
Seating capacity: 4
Cabin doors: 1
Cabin width: 43.5 in
Cabin height: 44.5 in
Vso: 59 kt
Best rate of climb, SL: 1300 fpm
Service ceiling: 20,000 ft
Cruise speed, 75% power: 197 kt
Fuel consumption, 75% power: 19 Usgph
Max range, 102 USgals: 1860 nm
Takeoff ground roll: 1620 ft
M20S Eagle
Engine: 244 hp / 182 kW Continental IO-550
Prop: two blade
Max cruise: 175 kt
Initial ROC: 1150 fpm / 350m/min
Max range: 1210 nm / 2240 km
2001 Mooney Eagle2
Base price: US$360,000
Engine: Continental IO-550G, 244 hp @ 2400 rpm@SL
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: McCauley CS/73 in
Landing gear type: Tri/Retr.
Max ramp weight: 3300 lb
Gross weight: 3300 lb
Landing weight: 3300 lb
Empty weight, std: 2200 lb
Useful load, std: 1100 lb
Payload, full std. fuel: 650 lb
Usable fuel: 75 USG
Oil capacity: 12 qts
Wingspan: 36 ft. 1 in
Overall length: 26 ft. 9 in
Height: 8 ft. 4 in
Wing area: 175 sq. ft
Wing loading: 18.3 lbs./sq. ft
Power loading: 13.1 lbs./hp
Wheel base: 6 ft. 7 in
Wheel track: 9 ft. 2 in
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 1
Cabin width: 43.5 in
Cabin height: 44.5 in
Baggage capacity: 120 lb
Cruise speed 75% power @ 8,300 ft.: 180 kt
Fuel consumption 75% power: 12.7 Usgph
Fuel consumption 65% power: 11.0 USGph
Fuel consumption 55% power: 9.2 USGph
Stall speed (flaps up): 66 kt
Stall speed (flaps down): 59 kt
Best rate of climb: 1150 fpm
Best rate of climb, 8000 ft: 760 fpm
Service ceiling: 18,500 ft
Landing ground roll: 1100 ft
M20 TN Acclaim
Price: US$495,000
Engine: Continental IO-550-G, 262 bhp@25,000 ft
Fuel type: 100LL
Propeller diameter: 76 in.
Landing gear type: Tricycle/Retractable/Trailing Link
Max ramp weight: 3374 lb
Gross weight: 3368 lb
Landing weight: 3200 lb
Empty weight, std: 2353 lb
Useful load, std: 1015 lb
Useful fuel, std: 102USG
Payload, full std. fuel: 418 lb
Oil capacity: 8 qts
Wingspan: 36 ft. 5 in
Overall length: 26 ft. 6 in
Height: 8 ft. 6 in
Wing area: 175 sq. ft
Wing loading: 19.25 lbs./sq. ft
Power loading: 12.03 lbs./hp
Wheel base: 79 in
Wheel track: 110 in
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cruise speed, 25,000 ft 100% power: 237 kt
Cruise speed 94% power: 231 kt
Cruise speed 75% power: 206 kt
Cruise speed 65% power: 198 kt
Cruise speed 55% power: 180 kt
Max range 100% power: 932 nm
Max range 94% power: 1097 nm
Max range 75% power: 1373 nm
Max range 65% power: 1455 nm
Max range 55% power: 1594 nm
Fuel flow 100% power: 22.1 USgph
Fuel flow 94% power: 20.7 USgph
Fuel flow 75% power: 14.5 USgph
Fuel flow 65% power: 12.0 USgph
Fuel flow 55% power: 10.2 USgph
Service ceiling: 25,000 ft
M20TN Acclaim Type S
Base price: $599,900
Engine: Continental TSIO-550-G, 280 hp @SL
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: 3-blade, CS Hartzell
Landing gear type: Tri./Retr.
Gross weight: 3374 lb
Empty weight, std: 2370 lb
Useful load, std: 1004 lb
Usable fuel: 100 USG
Payload, full std. fuel: 404 lb
Wingspan: 36 ft. 5 in.
Overall length: 26 ft. 9 in.
Height: 8 ft. 4 in.
Wing area: 175.7 sq. ft
Wing loading: 19.2 lbs./sq. ft
Power loading: 12.1 lbs./hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 1
Cabin width: 43.5 in
Cabin height: 45 in
Cruise speed, 75% power: 237 kt @ FL250
Vso: 59 kt
Climb rate, SL: 1240 fpm
Max operating altitude: 25,000 ft
1988 Mooney 252 TSE
Base price: $330,000
Engine: Continental TSIO-360-MB1, 210
TBO: 1800 hr
Fuel type: 100LL
Propeller: 3-blade McCauley/74 in
Landing gear type: Tri./Retr.
Max ramp weight: 2900 lb
Gross weight: 2900 lb
Landing weight: 2900 lb
Empty weight, std: 1800 lb
Useful load, std: 1100 lb
Payload, full std. fuel: 647 lb
Useful fuel, std: 75 USG
Oil capacity: 8 qts
Wingspan: 36 ft. 1 in.
Overall length: 25 ft. 5 in.
Height: 8 ft. 4 in
Wing area: 175 sq. ft
Wing loading: 16.6 lbs./sq. ft
Power loading: 13.8 lbs./hp
Wheel base: 71.6 in
Wheel track: 108.75 in
Wheel size, nose: 5.00 x 5 in
Wheel size, main) :6.00 x 6 in
Seating capacity: 4
Cabin doors: 1
Cabin width: 43.5 in
Cabin height: 44.5 in
Baggage capacity: 120 lb
Cruise speed 75% power @ 20,000 ft.: 201 kt
Cruise speed 65% power @ 10,000 ft.: 180 kt
Range (w/ reserve) 75% power @ 10,000ft.: 541nm
Range (w/ reserve) 75% power @ 20,000 ft.: 541nm
Max range (w/ reserve) 75% power: 980 nm
Fuel consumption 75% power: 12.7 Usgph
Vs: 61 kt
Vso: 59 kt
Best rate of climb: 1080 fpm
Best rate of climb, 8,000 ft: 1100 fpm
Service ceiling: 28,000 ft
Takeoff ground roll: 1250 ft
Takeoff over 50-ft. obstacle: 2200 ft
Landing ground roll: 1140 ft
Landing over 50-ft. obstacle: 2300 ft
Mooney
Mooney Aircraft formed July 1946 at Wichita, Kansas, USA.
Moved to Texas in 1953. M-20 four-seat version first flown August 10,1953.
Merged with Alon Inc. in October 1967. A variety of problems had run the company mil¬lions of dollars into debt, and in 1969, it was taken over by American Electronic Laboratories.
Became Aerostar Aircraft Corporation on July 1,1970, renamed Mooney Aircraft Corporation October 1973.
Then Butler Aviation International bought the operation, thinking to combine the three most popular Mooneys the Ranger, Chaparral and Executive with the twin engine Aerostar line, the product of still another company that had been taken over by Butler. Mooney might finally have come to an end in 1971 when Mooney quietly closed the doors and shut down production.
The company and its airplane lay dormant for a full three years before Republic Steel, in an unexpected diversification, acquired all rights to the Mooney line in October 1973 and resumed production at the old facility in Kerrville, Texas. In 1976, Republic continued to produce the Ranger, Chaparral and Executive.
1979: Mooney Aircraft Corporation, Subsidiary of Republic Steel, Kerrville, Texas 78028, USA.
Mooney’s 10,000th aircraft built 1994.
In 2001 the Mooney Aircraft Corp filed for bankruptcy, but in 2002 Advanced Aerodynamics & Structures took over the Mooney Aircraft Corporation.
Mooney Mite Aircraft Corp., Box 3999, Charlottesville, VA 22903, USA
Montgomerie Merlin / Layzell Merlin
Bensen’s Gyrocopter is the design-ancestor to the Merlin’s bolted 2×2 aluminum tube frame and streamlining is the modern Merlin’s anthem. Two fuel tanks are foamed in place behind the pilot and together hold 11 US gal. Partially enclosed, it has capacity for one. Sprung main wheel suspension struts w/intergral gas shock absorbers.
2001 Kit price without engine, rotors, propeller or instruments: approximately $5338.98 (U.S. dollars). Kits were supplied to the US market less rotors, gimbal head, engine, propeller and instruments.
Jim Montgomery’s design was produced by Layzell Gyroplanes of Quedgeley, Gloucester. The aircraft was supplied as a kit for amateur construction. After taking over Montgomery’s design, company owner Gary Layzell expressed an interest in further developing the Merlin, but initially produced it unchanged.
The aircraft fuselage is made from bolted-together square aluminum tubing. Its 7.01 m (23.0 ft) diameter Rotor Flight Dynamics rotor has a chord of 18 cm (7.1 in).
The type remained in production by Layzell through 2011, although by July 2012 the company website had been removed from the internet. The unit cost in 2011 was £12,761.
By January 2013, 28 examples had been registered in the United Kingdom with the CAA as Montgomerie-Bensen B8MR.
Engine: 65 hp Rotax 582
Prop: 60” GSC 3 blade ground adjustable / 60″ Ivoprop 3-blade ground adjustable
Rotor blades: 23’ Rotordyne bonded aluminium
Width: 6’7”
Height: 7’3”
Length: 12’6”
Width 6′ 7″
Empty Weight 298 lbs
Useful Load 352 lbs
Gross Weight 650 lbs
Min Speed 20 mph
Cruise 80 mph
Top Speed 100 mph
Engine: Rotax 582, 64 hp
Rotor span: 7.05 m
Blade area: 0.203 sq.m
MAUW: 300 kg
Empty weight: 174 kg
Fuel capacity: 30 lt
Max speed: 140 kph
Cruise speed: 90 kph
Seats: 1
Fuel consumption: 15 lt/hr
Kit price (1998): £11,721
Layzell Merlin GTS
Engine: 1 × Rotax 582, 48 kW (64 hp)
Propeller: 3-bladed composite
Main rotor diameter: 7.01 m (23 ft 0 in)
Empty weight: 145 kg (320 lb)
Gross weight: 295 kg (650 lb)
Fuel capacity: 50 litres (11 imp gal; 13 US gal)
Useful load: 150 kg (331 lb)
Cruise speed: 120 km/h (75 mph; 65 kn)
Rate of climb: 4.5 m/s (890 ft/min)
Crew: one
All Aero 