Californian brothers Walter Bissell Cannon and John Arthur Cannon built two machines in 1911. The second, a monoplane, was tested on Eaton Field in June 1911, powered by a Ford engine.
Cannon Brothers 1911 monoplane
Piston
Canard SC / SCM / Farner SC / SCM / Aviafiber SC / SCM
The Canard SC was the 1983 production version of the Farner Canard 2FL by Canard Aviation. designed by Ernst Ruppert with ETH Zurich.
During flight tests of the SC, from 23 July 1983, progress was accelerated by the use of an auxiliary 15 kW (20 hp) König SC 430 3-cyl. two-stroke radial engine mounted on a pylon between the v-struts and main-plane, driving a folding propeller, as the SCM.
Two were built (HB-2152 V-01 & HB-3004).
Two motorized versions (Canard SCM and Colibri) flew in 1983 and 1984. The development was suspended in 1993 following the accidental death of the designer, Hans Farner, during a test flight. The Company immediately bought the sold aircraft and ceased production.
They are stored in an attic, and two trailers are located at Ruppert Composites in Wald (Switzerland)
Canamerican S.G.VIE / Omega Aircraft Corp Sznycer-Gottlieb SG VI / Sznycer-Gottlieb SG VI
Designed by Bernard Sznycer and Selma Gottlieb as the S.V.IV in 1946, the 1947 Canamerican S.G.VIE was the first helicopter of all-Canadian construction. The prototype was certificated by civil authorities and developed through A, B, C and D versions by Engineering Products of Canada Ltd.
Omega Aircraft Corp was founded 1953 as a subsidiary of Allied Aero Industries for further development of the Sznycer-Gottlieb SG VI helicopter.
The Canamerican company was formed to produce it in the United States, the S.G.VI-E was essentially an improved model of the -D powered by a 200 hp Franklin 6A4-200-C6 engine.
S.G.VIE
Engine: 200 h.p. Franklin 6A4-200-C6
Rotor diameter: 35 ft.
Rotors: 4-blade main; 3-blade tail
Fuselage length: 32 ft.
Loaded weight: 2,550 lb
Cruise: 78 mph
ROC: 760 fpm
Typical range: 200 miles at 78 m.p.h.
Seats: 3
Canaero Dynamics Toucan
Designed by Peter Corley, the Toucan is a twin-engined, centreline thrust aircraft with twin tail booms.
Engine: 2 x Rotax 277
Empty wt.: 393 lbs
Max wt.: 900 lbs
Wing span: 38.5 ft
Wing area: 182 sq.ft
Wing loading: 5 lbs/sq.ft
Power loading: 16 lbs/hp
Max speed: 80 mph
Cruise: 65 mph
Stall: 25 mph
Vne: 90 mph
CLASS Cadi / BushCaddy
The prototype Cadi was designed by Jean Potbin of Lac St. Jean, Quebec, as a trainer and bushplane. It was intended to be powered by a Rotax 912 of 80 hp.
Potbin began selling kits in 1994 and delivered more than 50 before the program was taken over by Sean Gilmore. Gilmore had built a Cadi and had flown it for a year but was not satisfied with its construction and handling, so he tore it apart and started over. After the third version he turned to an engineer at Canadair to improve the design.
The Cadi was re-engineered to include a stiffened cabin and higher-stressed wings, as well as being convertible from wheels to floats or skies within 2 hours. The new design features a kickout windshield and was renamed BushCaddy.
The Bush Caddy was developed as a bush plane and performs equally well on wheels, skis or floats. The 44 to 47 inch cabin, doors that swing upwards under the wing and side by side deluxe adjustable seating afford even a 6 foot plus pilot easy access and a comfortable ride.
The full span windshield, door wide windows and low instrument panel provide excellent visibility. Pilot controlled heating and ventilation allow for all weather comfort anytime of year.
The Bush Caddy satisfies all the needs of the dedicated bush pilot. Low landing speeds combined with superior control and stability makes access to places that bush pilots dream of a reality. With more than a 4 hour fuel range the Bush Caddy is an excellent cross country aircraft. This is truly an aircraft capable of flying anywhere, anytime of year.
Flexibility is the principal characteristic of the versatile Bush Caddy kit. Models can be customized to suit all needs. The R80 ultra-light version can be entirely factory assembled, painted and custom equipped. The Voyageur model transforms from a taildragger to a trike in hours.
Designed as a rugged Canadian bush plane, the BUSH CADDY features:
Modern aerodynamics and superb engineering result in super STOL performance.
Solid rivet cabin construction pre-jigged and pre-punched.
All-metal airframe – easy to assemble, economical, tough and durable
Major components, pre-jigged and pre-drilled.
Wide comfortable cabin – from 44 “on the R-80 to 47” on the L-164
Many options to choose from – cargo doors, sky lights, interior finishes and more
Big payload – the BushCaddy will lift its own empty weight in payload
Wheels, skis and floats available
Engine options from 80 hp on the R-80 to 250 hp on the L-164
20 to 60 plus gallon fuel capacity
Super STOL performance – take off run as short as 75 feet.
Exceptional rate of climb to get you out of tight spots.
Customization for special needs available
Builder assistance available.
The wing is fitted with two spars, both with bent-up C sections made from 6061-T6 sheet aluminium. The forward spad is 5.9 inches high and located 5.5 inches aft of the leading edge; the rear spar is 37.5 inches farther aft, with a 4.7 inch height. Each wing half has 11 stamped 6061-T6 ribs. Ailerons each span 6 feet and have a 17 inch chord with a C-shape leading edge spar. They are aluminium skinned and are cable and pushrod activated.
Optional flaps are of similar construction. The wings are braced by 3 inch wide extruded aluminium struts. Twelve US gallon fuel tanks, with aluminium tops, are installed in each wing root.
The fuselage is made in three sections – nose, main, and tail – and is of box construction, with a four-corner, 4 inch radius structure. It has seven 0.016 gauge 6061-T6 stamped bulkheads with U-shape stringers on the sides, top and bottom. Two three-sided box frames, built of 0.050 gauge, 0.125 inch angles, are placed in the aft fuselage to support the tail. The cabin area employs a 6061-T6 L extrusion internal structure, with a 0.040 gauge belly pan and 0.032 gauge lower side skins.
Internal cabin width and height are both 44 inch. The side-by-side seats are adjustable and easily removed. Swing-up doors provide access to the cabin. The standard baggage area, aft of the seats, holds 15 cu.ft/75 lb.
Tailspan is 8 ft 7 in, and all surfaces contain tapered C-shape frames and ribs, also made from 6061 sheet metal. The stabiliser’s forward spar is positioned 7 inches aft of the leading edge. The rear spar is at the trailing edge. The rudder is 4 ft 2 in high, has a 15 in chord, and contains six ribs.
The rudder is controlled by cable and the elevator by pushrod. Skins are primarily 0.016 gauge. Solid rivets are used in the internal structure and to attach the skins in the cabin area, and Avex blind rivets are used elsewhere in the fuselage, the wings and the empennage. The main landing gear is a Cub type, with bungee-cord shocks. Cleveland wheels and brakes are fitted with Matco master cylinders. Tires are 6.00×6 McCreary.
The tailwheel is a castering/steerable design incorporating an O-ring sealed dust cap and a 4.5 in wheel. Maingear tread is 7 fee, and the wheelbase is 14 ft 7 in.
The R-80 model can be built as an experimental (amateur built) aircraft, or as a Canadian Advanced Ultralight Aeroplane, (AULA) built to the LAMAC Design Standards 10141. Powered by a Rotax or Jabiru engines, with a roomy cabin, CNC pre-jigged and constructed with aluminum angle and solid rivets. Side by side seating on fully adjustable removable seats are standard. A large baggage compartment, low stall speed and easy handling makes this model the perfect training aircraft.
The R-80 is either factory built (AULA Canada only) or in kit form. And to make it flexible, you can order the kit in sub-kits, starting with the fuselage first, then the cabin and lastly the wings.
The BushCaddy R80 kit has been evaluated and determined to meet the 51% rule.
The R-80 AULA Deluxe model taildragger with a Rotax engine sold for $89,500CAD in 2008.
The BushCaddy Sport AULA Taildragger/Trike convertible model with the Rotax 912S, 100 hp or Jabiru 3300, 120 hp sold for $92,900 CAD in 2008 completed. The R80 kit, less engine, engine mount, instruments, wheels, brake, and interior finish, but including cowling, fibreglass nose bowl and float mounts, sold for US$12,621 in 2001.
Rotax Model 100 hp or Jabiru 120 hp engine.
The L120 is the 1500 lbs. version of the R80, but beefed up to allow for a larger range of engine choices including the Continental 0-200 or Lycoming 0-235. It is a two place side by side with standard center stick. Available on wheels (trike or taildragger) skis and floats. It is shown here on Full Lotus 1650 floats, amphibious metal floats and wheels. The same rugged solid construction that is standard on all the BushCaddy models is designed into the R120. This is an excellent all-season, all-terrain hard working little bush plane. It side slips so well, and is off the ground in such a short distance that flaps are not necessary. They are however available as options if you wish them . NOTE: The R120 has now been approved by engineering for a gross weight of 1700 lbs.
The L120 choice of engines includes:
Rotax 912 – 912S – 914
Continental 65 – 85 – 90 – 100 hp
PZL Franklin 120 hp
Subaru conversion (weight max. 220 lb.)
Jabiru 120 hp
The L120 kit, less engine, engine mount, instruments, wheels, brake, and interior finish, but including cowling, fibreglass nose bowl and float mounts, sold for US$13,027 in 2001.
The L160 is a two seater with room for a child’s seat in the back. This model evolved from the R120 and was designed for pilots requiring a float plane with optimum fuel economy and payload. At 2200 gross you have a generous 1100 lbs of payload. Center stick, great visibility and a large roomy cabin are additional features. The two front seats are adjustable and removable. This is the perfect mid-size bush plane for hunting and fishing trips.
The L160 kit, less engine, engine mount, instruments, wheels, brake, and interior finish, but including cowling, fibreglass nose bowl and float mounts, sold for US$15,526 in 2001.
The four place L164 is powered by a Lycoming IO-350 of 180 hp. All BushCaddy kits and components, including fuel tanks, are made of aircraft grade aluminium.
The BushCady L164 four seater, at 2500 gross, this model will accommodate 1200 lbs plus of payload. Featuring two large main doors with optional hinged windows, four fully adjustable and removable seats with hinged backs to allow for easy entry into the back, and featuring our unique “caddy storage” compartments under the cushions. A generous cabin and cargo bay with standard cargo door. Your kit comes complete with wheels, brakes, engine cowling, nose bowl – all you add is paint, engine and instruments. Flight testing the L164 has resulted in better than expected STOL and climb performance. A cargo version “C” model of this aircraft is also available for those who want a total utility aircraft.
The fast build kit includes Cabin, doors and seats pre-jigged, pre-drilled and pre- assembled; fuselage fully built and riveted closed; vertical, horizontal stabilizers, rudder and elevators all pre-built, skins pre-punched and ready to rivet; wings fully built, and jigged for washout, pre-punched with top of wing riveted closed, bottom of wings tacked riveted for inspection.
The convertible-gear Voyager, with its taildragger-to-trike option, was available in two models and allows owners to switch gear in a few hours. Float fittings are also included in the Voyager option.
Club Aeronautique Delisle Cadi
Engine: Rotax 912, 80 hp
Wing span: 9.75 m
Wing area: 16 sq.m
MAUW: 544 kg
Empty weight: 274 kg
Fuel capacity: 90 lt
Max speed: 160 kph
Cruise speed: 142 kph
Minimum speed: 50 kph
Climb rate: 4.5 m/s
Seats: 2
Fuel consumption: 12 lt/hr
Price (1998): Can$50,000
Kit price (1998): Can$15,000
R80
Engine: Rotax 912 – 80 h.p.
Undercarriage: wheels
Length: 22 ft. 1in.
Height: 6 ft
Wing span: 32 feet
Wing area: 168 sq. ft.
Ceiling: 10,000 ft.
Max weight: 1232 lbs
Empty weight: 680 lbs.
Useful load: 552 lbs.
Cruise 75%: 95 mph
Vne: 130 mph
Va: 68 mph
Stall power off: 32 mph
Take off: 266 ft. asphalt, 282 ft grass, 305 ft. softfield
Rate of climb: 850 f.p.m.
R80
Engine: Rotax 912 – 80 h.p.
Undercarriage: floats
Length: 22 ft. 1in.
Height: 6 ft 10 in
Wing span: 32 feet
Wing area: 168 sq. ft.
Ceiling: 10,000 ft.
Max weight: 1232 lbs
Empty weight: 835 lbs
Useful load: 397 lbs
Cruise 75%: 87 mph
Vne: 130 mph
Va: 76 mph
Stall power off: 38 mph
Take off: 15 secs
Rate of climb: 600 f.p.m.
R80
Engine: Rotax 912S 100 h.p.
Undercarriage: wheels
Length: 22 ft. 1in.
Height: 6 ft
Wing span: 32 feet
Wing area: 168 sq. ft.
Ceiling: 12,000 ft.
Max weight: 1232 lbs
Empty weight: 680 lbs
Useful load: 552 lbs
Cruise 75%: 100 mph
Vne: 130 mph
Va: 68 mph
Stall power off: 32 mph
Take off: 200 ft asph.
Rate of climb: 930 f.p.m
R80
Engine: Rotax 912S 100 h.p.
Undercarriage: floats
Length: 22 ft. 1in.
Height: 6 ft. 10 in
Wing span: 32 feet
Wing area: 168 sq. ft.
Ceiling: 12,000 ft.
Max weight: 1232 lbs
Empty weight: 835 lbs
Useful load: 397 lbs
Cruise 75%: 91 mph
Vne: 130 mph
Va: 76 mph
Stall power off: 38 mph
Take off: 15 secs
Rate of climb: 750 f.p.m.
R80
Engine: Rotax 914, 115 h.p.
Undercarriage: wheels
Length: 22ft.1in.
Height: 6 ft
Wing span: 32 feet
Wing area: 168. sq. ft
Ceiling: 12,000 ft.
Max weight: 1232 lbs`
Empty weight: 680 lbs.
Useful load: 552 lbs.
Cruise 75%: 105 mph
Vne: 130 mph
Va: 68 mph
Stall power off: 34 mph
Take off: 200 ft. asph.
Rate of climb: 1000 fpm
R80
Engine: Rotax 914, 115 h.p.
Undercarrige: floats
Length: 22ft.1in.
Height: 6 ft. 10 in.
Wing span: 32 feet
Wing area: 168. sq. ft
Ceiling: 12,000 ft.
Max weight: 1232 lbs`
Empty weight: 835 lbs
Useful load: 397 lbs
Cruise 75%: 100 mph
Vne: 130 mph
Va: 80 mph
Stall power off: 40 mph
Take off: 15 secs
Rate of climb: 800 f.p.m.
R80
Engine: Jabiru 3300
Undercarriage: wheels
Length: 22 ft. 1in.
Height: 6 ft
Wing span: 32 feet
Wing area: 168 sq. ft.
Ceiling: 10,000 ft.
Max weight: 1232 lbs
Empty weight: 694 lbs
Useful load: 538 lbs
Cruise 75%: 115 mph
Vne: 130 mph
Va: 68 mph
Stall power off: 34 mph
Take off: 200 ft asph.
Rate of climb: 1000 f.p.m.
R80
Engine: Jabiru 3300
Undercarriage: floats
Length: 22 ft. 1in.
Height: 6 ft 10 in.
Wing span: 32 feet
Wing area: 168 sq. ft.
Ceiling: 10,000 ft.
Max weight: 1232 lbs
Empty weight: 848 lbs
Useful load: 384 lbs
Cruise 75%: 100 mph
Vne: 130 mph
Va: 84 mph
Stall power off: 34 mph
Take off: 15 secs.
Rate of climb: 850 f.p.m.
L120
Engine: Rotax 912S, 100 hp
Hp range: 65-130
Wing span: 34 feet
Wing chord: 63 inches
Wing area: 168 sq. ft
Wing loading: 8.9 lb. per sq. ft
Length: 22 ft. 1 in.
Cabin width: 44 in.
Cabin height: 46 in.
Fuel capacity: 20 or 34 imp. gallons
Empty weight: 823 lb.
Maximum gross take off weight: 1500 lb. – (1700 lbs on approval from CLASS)
Useful load: 677 lb.
Fuel consumption: 4 imp. gal per hour
G loading: +5.7 / -3.8
Maximum speed (v.n.e.): 130 m.p.h.
Cruising speed at 75% power: 110 m.p.h.
Cruising speed 60% power: 90 m.p.h.
Power off stall: 34 m.p.h.
Flap extended stall speed: 32 m.p.h.
Rate of climb 1500 lbs: 800 f.p.m.
Service ceiling: 16,000 feet
Take off 1500 lbs: 200 feet
Take off (floats): 15 to 30 sec. (1500 lb.)
L160
Engine: Lycoming 0-320, 160 hp
Wing span: 36 feet
Wing chord: 63 inches
Wing loading: 11.6 lb. per sq. ft
Length: 23 ft. 10 in.
Cabin width: 44 in.
Cabin height: 46 in.
Fuel capacity: 38 imp. Gallons
Empty weight: 1098 lb.
Maximum gross take off weight: 2200 lb.
Useful load: 1102 lb.
Fuel consumption: 7 imp. gal per hour
‘G’ loading: +5.3 / -3.2
Maximum speed (vne): 150 m.p.h.
Cruising speed at 75% power: 115 m.p.h.
Cruising speed 60% power: 105 m.p.h.
Power off stall: 42 m.p.h.
Flap extended stall speed: 37 m.p.h.
Rate of climb (full load): 850 f.p.m.
Rate of climb (1200lb): 1300 f.p.m.
Service ceiling: 13,000 feet
Take off (2200 lb): 360 feet
Take off (1600 lb): 250 feet
Take off (floats): 15 to 30 sec. (1500 lb)
L164
Engine: Lycoming I0-360 L2A, 180 hp
Propeller: Sensenich 76EM8
Hp range: 160 to 250
Length: 25.5 feet
Wing Span: 36 feet
Cabin Width: 47 inches
Cabin Height: 52.5 inches
Wing Chord: 63 inch
Gross weight: 2500 lbs.
Empty weight: 1350 to 1450 lbs
Useful load: 1050 to 1150 lbs
Fuel Capacity: 60 US gallons
Rate of climb: 1200 fpm
Take off run: 200 ft. at gross
Stall: 38 mph
Max.Cont Airspeed Vh: 135 mph IAS/128.5 mph CAS
Cruise Speed: 115 mph IAS
G Loading: +5.3 / -3.2 limit, +3.8 / -1.9 normal category
Seats: 4
L164
Engine: Franklin 220 hp
Undercarriage: floats
Propeller: Constant speed
Average Take off run: 15 to 20 seconds
Voyager
Canadian Home Rotors Baby Belle Safari
Canadian Home Rotors Inc. (CHR) are the manufacturers of the Safari helicopter. A scaled Bell 47G look alike, that has consist¬ently placed at the top of the custom built helicopter pile. Originally called the Baby Belle, but after objection from Bell Helicopters the name was changed to Safari.
A two seat side by side enclosed helicopter, the 4130 steel tube frame cabin monocoque and boom can be made up in the home workshop while awaiting delivery of the factory built main rotor and tail rotor gearboxes along with the main rotor head and blades. Main rotor is gear driven, tail rotor is shaft driven. Tail boom is steel tube. The main rotor blades are skinned all-aluminium with extruded aluminium leading and trailing edges. Blades are shaped by one solid rib each 6 inches from the root to three feet outboard, then one rib per 12 inches to the tip. Each blade contains 16 ribs. The main rotor flies at 500 rpm, and tail-rotor at a 5.4:1 rpm ratio.
The four foot diameter, 4 inch chord tail rotor blades are stainless steel, with a solid steed spar running out 6 inches from each blade root and wrapped with stainless sheeting to form the airfoil.
The main rotor gearbox includes clutches and engine fan. The cabin bubble is sourced from Nordam Plastics, manufacturers of the original Bell 47 item. The bubble is an actual Bell 47 series enclosure.
A Delta teetering system provides the control. Aluminium castings are used in the swashplate-controlled main rotor system.
The instrument panel carries operational instruments and a main transmission temp indicator and chip detectors for the main and tail rotor gearboxes. Engine, seats and cockpit fittings were generally the items sourced from written off Robinson R22.
Fuel capacity of 28 US gallons is carried in two 14 USG aluminium tanks aft of the cabin.
Skid landing gear is built with 2 inch diameter tubing, the bottom horizontals black anodised.
In 1996 the kit price was US$38,000.
CHR are constantly improving the Safari with experience, including increased service intervals on the main rotor gearbox. Build weight is always slightly different between machines but generally just under 1,000 lbs., which allows a useful load of better than 500 lb. The 12 foot span blades feature an eight inch chord and weigh 40 lb. each.
The Safari is powered by a Lycoming 160 hp aircraft engine, maintaining the highly trustworthy flying abilities of this classic design. Cruising speed is 80 mph with climb rate of 1,000 fpm & an operating ceiling of 10,000ft. Max. speed is 100mph.
A US corporation, CHR International Inc acquired Safari Helicopter. The owners of CHR International Inc., Bobby and Delane Baker, have been involved with Safari for several years. Murray Sweet, one of the original developers of the Safari, was to remain involved with the new company as a technical consultant, as will other long time members of the Safari team.
Much of the production was to remain in Canada, with assembly and flight training continuing in Marianna, Florida. They reduced the dealership requirements in most parts of the world, with positive results.
Engine: Lycoming O-320, 150 hp.
HP range: 150-180.
Disk span: 25 ft 11 in
Rotor Blades chord: 8 in
Disk area: 490.6 sq.ft.
Width 6 ft
Height 8 ft
Length 29 ft 8 in
Weight empty: 920-945 lbs.
Gross: 1450 lbs.
Speed max: 100 mph.
Cruise: 80 mph.
Range: 200 sm.
ROC: 1000 fpm at 45 mph.
Service ceiling: 10,000 ft.
HIGE: 7000 ft
HOGE: 2000 ft
Fuel cap: 28 USG.
Seats: 2.
Landing gear: skids.
Engine: Lycoming O-320, 150 hp
Rotor span: 7.30 m
MAUW: 750 kg
Empty weight: 372 kg
Fuel capacity: 108 lt
Max speed: 160 kph
Cruise speed: 145 kph
Minimum speed: 0 kph
Climb rate: 5 m/s
Seats: 2
Price (1998): $88,500
Plan price (1998): $150
Kit price (1998): $38,430
Canadian Car & Foundry FDB-1 Gregor Fighter
Can Car’s final attempt to produce its own design was the FDB 1, the so called ‘Gregor Fighter’, named after Michael Gregor, the chief aeronautical engineer who preceded Miss MacGill. The FDB 1 was designed as a highly manoeuvrable, biplane fighter/dive bomber with retractable undercarriage and powered by a Pratt & Whitney R 1535 SI34 G Twin Wasp Junior. The fuselage was of stressed skin construction while the wings were fabric covered metal structures with trailing edge flaps on upper and lower planes and automatic leading edge slots on the former. Port and starboard sections of the upper wing were separate, joining the fuselage in a modified gull wing form, which helped to improve forward visibility.
Despite the excellent manoeuvrability of the prototype, which first flew on 17 December 1938 at Fort William, Ontario, its speed was considerably less than had been predicted and there were problems with controls and flaps. Aircraft of this type were rapidly becoming outdated and, since by this time CCF had become involved in what was to be its most successful contract, the Gregor Fighter was placed in storage at Cartierville, Quebec, where it was burned in 1945.
Canadian Car & Foundry Maple Leaf II
The Maple Leaf I was followed by the Maple Leaf II, which, despite the name, had little more than the empennage in common with its predecessor. The design and engineering team, led by Miss E G MacGill, at that time the only female chief aeronautical engineer in Canada, had the prototype ready for its first flight in the fall of 1939. Although it gave creditable performances in tests by the Department of Transport and the RCAF, the Maple Leaf II never reached the production line, mainly because at that time the company had already committed its Fort William plant to the production of the much needed Hurricane. The prototype, along with various components and parts of at least two partly finished aircraft, was eventually exported to Mexico.
Canadian Airmotive CAM 100 / Firewall Forward CAM 100
The Firewall Forward CAM 100 is a 100 hp (75 kW) four-cylinder, four-stroke liquid-cooled piston aircraft engine built by Firewall Forward Aero Engines. Originally designed and built by Canadian Airmotive as the CAM 100 and later marketed by The Cam-Fire Engine Group, it is based on a Honda Civic automotive piston engine. Unit cost was US$8,450 in 2005.
Applications:
Blue Yonder Merlin
Denney Kitfox V
Murphy Rebel
Zenith Zodiac CH 601
CAM 100
Type: Four-cylinder, four-stroke piston engine
Bore: 74 mm (3.07 in)
Stroke: 86.5 mm (3.41 in)
Displacement: 1488 cm3 (90.7 cu in)
Length: 32 inches (810 mm)
Width: 19.5 inches (500 mm)
Height: 25 inches (640 mm)
Dry weight: 226.2 pounds (102.6 kg)
Valvetrain: overhead camshaft
Fuel type: 90 Octane petrol or 100LL aviation petrol
Cooling system: Uses a water-glycol mixture with a camshaft belt driven water pump.
Reduction gear: 2.4:1 reduction ratio (6,000 rpm engine, 2,500 rpm propeller).
Starting system Electric gear reduction starter.
Power output: 100hp (74.6 kW) at propeller flange.
Specific power: 130 kW/L (1.10 hp/cu in)
Compression ratio: 9.6:1
Specific fuel consumption: 0.43 lb/bhp/hr at 80% power
Firewall Forward CAM 100
Cycle: 4 stroke
No cylinders: 4 inline
Bore: 74 mm
Stroke: 86.5 mm
Compression: 9.6
Displacement: 1488 cc
Cooling: liquid
Ignition: Electronic
Reduction: Crantee Belt 2.4/1
Dimension: 570 x 641 x 813 mm
Weight: 101.9 kg
Max pwr: 105 hp
Price 1998: $7950
Canadian Aerodrome Company Hubbard Monoplane “Mike”
The Canadian Aerodrome Company Hubbard Monoplane “Mike” (Hubbard II) designed and built in Canada in 1910.
J. A. D. McCurdy set up the Canadian Aerodrome Company after the AEA was dissolved. Gardiner Hubbard was a cousin of Bell’s wife, Mabel Gardiner Hubbard.
The Hubbard Monoplane, also nicknamed “Mike”, was designed by John McCurdy and built by the Canadian Aerodrome Company. It was commissioned by Gardiner Greene Hubbard II of Boston. The monoplane was constructed at the Beinn Bhreagh estate of Alexander Graham Bell in Baddeck, Nova Scotia, by John McCurdy and F. W. “Casey” Baldwin. The aircraft was the third to be built by the Canadian Aerodrome Company, and the first to represent an indigenous design, although loosely based on the Blériot XI. The aircraft made two brief flights on 3 March 1910, flown by McCurdy.
After it was shipped to Montreal for the 1910 Montreal Air Meet, Hubbard was unsuccessful in flying the aircraft, it possibly being too low-powered to do more than taxiing. Shortly after, Hubbard had the aircraft dismantled and shipped to Boston, making it the first Canadian aircraft sold and built for export. The intent was to enter the aircraft at the Harvard-Boston Aero Meet in Boston. The aircraft was displayed at the aero meet, and was included in the photographs of the flight line, but it did not leave the ground.
Baddeck No. 2
Engine: 1 × Kirkham air-cooled piston engine, 40 hp (30 kW)
