Designed by Charles Rocheville, the sole 1928 American Albatross B-1 NX6772 was sold in 1929 to (Alva Roy) Ebrite Aero Corp of Long Beach CA, for charter work and is sometimes seen as Ebrite New Albatross, reportedly repowered with 400hp P&W Wasp. It was used for 1929 endurance record attempts by John Gugliemetti and Lee Schoenhair, but without success.
The sole 1927 Albatross Z-12, or Schofield Albatross, NX3622, succeeded, after four attempts, in taking off with 9898 lbs, 2.47 times its empty weight, in a 1928 demonstration flight.
Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading edge, swept for¬ward trailing edge and tapering chord; con¬ventional tail. Pitch control by fully flying tail; yaw control by fully flying rudder; roll control by half span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile double surface. Undercarriage has three wheels in tricycle formation; glass fibre sus¬pension. Push right go right nosewheel steer¬ing connected to yaw control. Aluminium tube and sheet framework, with optional total enclosure pod. Engine mounted at wing height driving tractor propeller. All aluminium and hardware is of aircraft quality. The Zipper is a conventional three axis machine with rudder pedals and centre stick, and it appears to be quite conventional in its choice of materials, being basically a tube and Dacron machine. There are some interesting features though, such as the tail boom, which is not tubular but is constructed of sheet aluminium alloy formed into a rectangular cross section. Most of the innovation, however, is centred on the wing design, which has an unusual shape plan, with ailerons attached to the trailing edges. The design allows the wing to be folded in two minutes, the maker claims, after which the aircraft can be towed on its own wheels, avoiding the expense of a trailer. Engine is the direct drive JPX PUL425, which is available in two states of tune 22 hp standard or 26hp with tuned exhaust. The aircraft is sold in kit form, but Zenair says the kit takes only an afternoon to complete, having already been test assembled in the factory before shipping. Other options include floats and wheel spats, while an enclosed cockpit, skis and propeller spinner are also offered.
Length overall 14.5 ft, 4.42 m Height overall 5.5ft, 1.68m Wing span 28.0ft, 8.53m Mean chord 5.0ft, 1.52m Sweepback 0 deg Total wing area 140 sq.ft, 13.0 sq.m Wing aspect ratio 5.6/1 Engine: JPX PUL425, 22hp at 4600rpm Propeller diameter 42 inch, 1.07 m No reduction Max static thrust 180 lb, 82 kg Power per unit area 0.16hp/sq.ft, 1.7hp/sq.m Fuel capacity 6.0 US gal, 5.0 Imp gal, 22.7 litre Empty weight 180lb, 82kg Max take off weight 420 lb, 191 kg Payload 240 lb, 109 kg Max wing loading 3.00 lb/sq.ft, 14.7 kg/sq.m Max power loading 19.1lb/hp, 8.7kg/hp Load factors +6.0, 3.0 design Max level speed 50 mph, 80 kph Never exceed speed 80 mph, 129 kph Cruising speed 40mph, 64 kph Stalling speed 20 mph, 32 kph Max climb rate at sea level 700 ft/min, 3.6 m/s Take off distance 120 ft, 35 m Landing distance 80 ft, 25 m Range at average cruising speed 100 mile, 161 km Seats: 1
The STOL CH 801 was developed to provide maximum short-field performance while being easy to build and maintain. The STOL CH 801 is a four-seat sport utility kit aircraft based on the two-seat STOL CH 701.
Zenith CH-801 C-GCUI
The larger STOL CH 801 has been developed to expand the utility of the STOL CH 701 model by increasing the useful load from 500 lbs. (225 kg) to 1,000 lbs. (450 kg.) while retaining the original design’s short and rough field capability. While the two designs share many similarities in appearance, they actually do not share any airframe parts due to the significantly larger size of the STOL CH 801.
Built of all-metal construction, the STOL CH 801 is designed to provide the durability and ruggedness required of an “off-airport” bushplane with high-lift wing with slats and flaps, the kit (basic airframe) was $18,490, and $20,950 in 2002.
Engine: Subaru, 180 hp Wing span: 9.4 m / 30 ft 10 in Wing area: 15 sq.m Length: 23 ft 2 in MAUW: 920 kg Empty weight: 460 kg Fuel capacity: 150 lt Max speed: 200 kph / 125 mph Cruise speed: 175 kph / 110 mph Minimum speed: 62 kph / 39 mph Climb rate: 5.3 m/s Take-off roll: 200 ft Landing roll: 150 ft Seats: 4 Fuel consumption: 30 lt/hr
Engine: Lycoming O-360-A, 180 hp Prop: Sensenich 76-EM8-0-54 fixed Engine range: 150 – 240 hp, 440lb Length: 24 ft.6 in./ 7.5 m. Height: 10 ft.0 in./ 3.0 m Ultimate load: + 5.7, – 2.8g Wing Span: 31 ft.4 in./ 9.55 m Wing Area: 167 sq.ft./ 15.5 m.sq. Wing Chord: 5 ft.3 in./ 1.6 m Empty Weight: 1,150 lb./ 522 kg Horizontal Tail Span: 10 ft.1 in./ 3.1 m Gross Weight: 2,200 lb./ 1,000 kg Horizontal Tail Area: 30 sq.ft./ 2.8 m.sq Useful Load: 1,050 lb./ 478 kg Fuel Cap (Std): 30 USG. (2 x 15)/ 112 lt (2 x 56) Design Payload: 800 lb./ 360 kg. Fuel Cap (Opt): 60 USG. (4 x 15)/ 224 lt (4 x 56) Wing Loading: 13.2 lb /sq.ft /64.4 kg/m sq.ft. Power Loading: 11.95 lb /hp / 5.44 kg/hp Cabin Width: 44 in/112 cm. Cabin Length: 78 in/198 cm Max. Flap Speed: 80 mph/129 km/h Max. Cruise: 120 mph/193 km/h Vne: 150 mph/240 km/h Take-Off Roll: 290-390 ft./ 88-119 m Max Level Speed: 110 -112 mph/178-181 km/h Cruise (75%, 7,000 ft.): 105 -106 mph/169-170 km/h Stall (Flaps Dn): 35-39 mph/56-64 km/h Stall (Flaps Up): 43-48 mph/69-77 km/h Rate Of Climb: 720 -1,200 fpm/3.7 -6.1 m/s Endurance (Std): 3.0 Hrs Endurance (Opt): 6.0 Hrs. Range (Std): 315 -320 sm/507 -515 km Range (Opt): 630-640 sm/1015-1030 km. Service Ceiling: 14,000 -16,000+ ft/4,267-4,875+ m. Cockpit width: 44 in Undercarriage: trigear
Based on the CH 701 the STOL CH 750 design incorporates the 701’s short-field capabilities, while maximizing cabin size and load carrying capability allowed under the FAA’s new Sport Pilot / Light Sport Aircraft category. The STOL CH 750 aircraft was developed as an “off-airport” short take-off and landing kit aircraft to fulfill the demanding requirements of both sport pilots and first-time builders. The aircraft features fixed leading-edge slats for high lift, full-span flaperons (both ailerons and flaps), an all-flying rudder, and durable all-metal construction. The aircraft features many engine choices: Continental, Jabiru, Rotax, Corvair, and more, and full length flaperons and all-flying rudder
Engine: Continental O-200-A, 100 hp Powerplant range: 80 – 125 hp, up to 300 lb. Wing Span: 29 ft. 9 in/9.1 m Height (Rudder Tip): 8 ft. 8 in/2.6 m. Wing Area: 144 sq.ft./13.4 m.sq Wing Chord: 4 ft. 10 in/1.5 m. Length: 21 ft. 10 in/ 6.7 m Horizontal Tail Span: 8 ft. 5 in/2.6 m Wing Loading: 9.15 lb/ft.sq/44.8 m.sq Horizontal Tail Area: 22.2 sq.ft/2.0 m.sq. Empty Weight: 775 lb/350 kg Gross Weight: 1,320 lb/600 kg. Useful Load: 545 lb/250 kg Power Loading: 13.2 lb/hp / 6.0 kg/hp Load Factor (Ult): +6 G / -3g Cabin Width (Shoulders): 42 in/100 cm. Cabin Width(Opt): 50 in/1.27 m Fuel Capacity (Std): 24 USG/90 lt Take-Off Roll: 100 ft/30m Landing Roll: 125 ft/38m Max Cruise SL: 100 mph/162 kph VNE : 125 mph/200 kph Stall, Flaps Dn: 35 mph/56 kph Rate of climb: 1,000 fpm/5.1 m/s Service Ceiling: 14,000+ ft/ 4,200+ m Std. Range: 400 sm/710 km. Endurance: 5 Hrs
The STOL CH 701 aircraft was developed as an “off-airport” short take-off and landing kit aircraft for both sport pilots and first-time builders. It is designed to be providing maximum short-field performance while being easy to build and maintain, making in a true sport utility kit aircraft. With the STOL CH 701, designer Chris Heintz combined the features and advantages of a “real” airplane with the short-field capabilities of an “ultralight” aircraft. The aircraft features fixed leading-edge slats for high lift, full-span flaperons (both ailerons and flaps), an all-flying rudder, and durable all-metal construction. Simple systems, modern materials, and design ingenuity minimize required maintenance, and make the STOL CH 701 easy to build and fly, affordable, and very durable. The STOL CH 701 uses a special airfoil design to achieve very high lift, low stall speeds, and high strength. A thick wing, full-length leading-edge slats and trailing edge ‘junker’ type flaperons develop a maximum wing lift while maintaining a short wing-span – for maximum strength and ground maneuverability. The aircraft designs also feature an all-flying vertical tail (rudder) section for excellent effectiveness and control, especially at low speeds. This provides responsive rudder control, while also minimizing weight and complexity (there’s only one vertical tail section). Two rudder bearings bolt to the rear fuselage to fix the rudder to the fuselage.
The Zenith Zodiac CH-701 STOL is a two-seat, single-engine, all metal shoulder-wing microlight airplane with a fixed tricycle undercarriage with steerable nosewheel or tail wheel. The “SkyJeep,” with the heavy gear and tundra tires and all aluminium wings is a Ultralight Bush Plane with excellent short-field performance. With its slow flight capability the plane is an excellent observation platform. In 1985, Chris Heintz, founder and chief designer of Zenair, started the development of the Zenair STOL CH701 in a response to the need for a small but rugged airplane that could be fitted with wheels, skis and floats. The first Zenair CH701 s/n 73001, registered N701ZA, was introduced in 1986. Production deliveries started in 1987. In 1992, Heintz licensed the kit manufacturing and marketing rights to Zenith Aircraft Company for the Zodiac CH 601 and the STOL CH 701 designs. The Zenair CH-701 is nowadays manufactured in kit form by Zenith Aircraft Company, Mexico, Missouri in the USA. The STOL CH 701 kit aircraft may be built from component or complete kits, or even built from just the drawing and manuals. Building a STOL CH 701 from just the drawing and manuals lasts more time, skills, and tools, to build. Recommended power for the CH-701 is the four cylinder four stroke 80 HP Bombardier Rotax 912 UL engine, other alternative power units with a recommended power of 65 to 100 HP and up to 185 lbs. installed weight can be installed. Already over 500 CH-701 airframes are flying all around the world. The STOL CH701 design meets the definition of a Light Sport Aircraft (LSA) for operation under the Light Sport Aircraft (LSA) category.
The STOL CH701 design meets the definition of a Light Sport Aircraft (LSA) for operation under the FAA’s Sport Pilot / Light Sport Aircraft (LSA) category. 2009 Price: 42000 US$ The two-seat, high wing aircraft has been fitted with the Spray Miser Ag System by Czech Aircraft Works which uses wind-driven rotary atomisers. This CH 701-AG is equipped with fixed leading-edge slats, full-length flaperons, which enable it to be manoeuvred at speeds below 35 mph and typically take-off in less than 30 metres.
Featuring CNC precut and predrilled aluminum skins, the CH 701 is easy to build quickly. On three occasions, Zenith demonstrated this with kit startup, completion and first flights in seven days using volunteers at the Florida Sun ’n Fun fly-ins.
As of October 1998 125 kits were sold, and 95 were built from plans, the basic airframe kit selling for $12,360. Plans also offered.
Amphibious floats cut the speed by 3 mph. The floats are built in about 80 hrs from plans and are installed without removing the tri gear. The nose wheel folds back.
The STOL CH.701 two-seat utility cabin monoplane is certificated in Israel and Mexico.
STOL CH 701 Engine: Rotax 582, 65 hp Engine Limit: 50-100 hp, up to 185 lbs. Wing Span: 27 ft/8.2 m Wing Area: 122 sq.ft./11.4 m.sq. Length: 20 ft. 11 in/6.38 m Height: 8 ft. 7 in/2.6 m. Empty weight: 580 lbs/263 kg Gross weight: 1,100 lbs/500 kg. Useful load: 520 lbs/236 kg Wing loading: 9.0 lb/sq.ft / 43.8 sq.m Power loading: 13.75 lb/hp / 6.25 kg/hp Design load: +6 G / -3G Cabin width Option: 44 in / 110 cm Cabin width: 40 in / 100 cm. Fuel cap Std: 20 USG (2 x 10 USG.) Fuel cap Opt: 2 x 38 lt Speed max: 85 mph. Cruise: 75 mph. Range: 270 sm Range Opt: 740 km Stall: 28 mph ROC: 1200 fpm. Take-off dist: 90 ft Landing dist: 125 ft. Service ceiling: 16,000 ft Seats: 2. Width (wings folded): 7 ft 4 in Landing gear: nose.
STOL CH 701 Engine: Rotax 912, 80 hp Top Speed: 85 mph Cruise, Sea Level: 80 mph VNE: 110 mph 75% Cruise @ 8,000 ft: 92 mph tas Stall: 28-30 mph Rate Of Climb: 1,000-1,100 fpm Take-Off Roll: 60-115 ft Landing Roll: 80-140 ft Service Ceiling: 12,000-13,000+ ft Std. Range: 372 sm Endurance: 4.6 Hrs.
Zenair SP701 STOL Wing area: 11.4 sq.m Length: 6.38 m Height: 2.6 m Gross weight (floats): 500 kg Empty weight (floats): 354 kg Useful load: 236 kg Wing loading: 43.8 kg/sq.m Design loading; +6 / -3 G Cabin width: 1.04 m Fuel capacity (wing tanks): 2 x 45 lt Top speed: 159 kph Cruise: 144 kph Stall: 65 kph ROC: 305 m/min Takeoff roll: 40 m Landing dist; 50 m Range no res: 700-830 km Endurance 5000 rpm: 82 kt / 16 lt/hr: 5.5 hr Endurance 5300 rpm: 20 lt/hr: 4.4 hr
CH701 STOL Engine: Rotax 912S, 100 hp HP range: 50-100 Length: 20.9 ft Wing span: 27 ft Wing area: 122 sq.ft Empty weight: 580 lb Gross weight: 1100 lb Fuel capacity: 20 USG Cruise: 85 mph Stall: 30 mph Range: 460 sm Rate of climb: 1200 fpm Takeoff dist: 90 ft Landing dist: 140 ft Seats: 2 Cockpit width: 44 in Landing gear: nosewheel LSA: yes
CH 701-AG
CH 701 STOL Amphib Top speed: 90 mph Cruise: 74 mph Stall: 32 mph Range: 240 sm Rate of climb: 950 fpm Takeoff dist: 155 ft land / 300 ft water Landing dist: 225 ft land / 250 ft water Service ceiling: 12,000 ft Engine: Rotax 912, 80 hp HP range: 65-100 Fuel capacity: 11 USG Empty weight: 575 lb Gross weight: 1075 lb Height: 9.5 ft Length: 20 ft Wing span: 27 ft Wing area: 122 sq.ft Seats: 2 Landing gear: retract trigear / floats
The CH 650 LS AND LSi, introduced at AirVenture 2008, combine the best of a European-built CH 601 XL sold as a ready-to-fly aircraft, the AMD CH 601 XL sold as an S-LSA, and the Zenith Aircraft Company’s amateur built CH 601 XL kit. Eventually, the 601 XL will be phased out. The 650 is available as plans (with CAD drawings and assembly manuals), a complete kit (or a series of sub kits) from Zenith Aircraft, Mexico, Missouri, or as a ready-to-fly S-LSA from Aircraft Design Manufacturing & Design (AMD) of Eastman Georgia. The CH 650 LS’s improvements include a more-convenient hinged clamshell bubble canopy, with dual tube 4130 roll-over protection. The new canopy adds headroom. (The new roll-over protection and redesigned canopy latching system are also available from Zenith Aircraft as an upgrade kit for existing Zodiac Owners.) The CH 650 LS, anticipated as a primary trainer, sports standard aviation 500-by-5 wheels and brakes. The gear system is bigger, making the aircraft taller, and the AMD main gear spring is gun-drilled, for cleaner, more protected brake line routing. The rudder was redesigned and looks sleeker. The “European” wing angle is now standard on the 650 LS, with the trailing edge of the wing tilted down about 2 inches. Extra aluminum braces have been added to the fuselage sides and wings. The interior sports carpeting, and parts familiar to other Heintz-designed airplanes include the rudder pedals, the cowl, the nose gear strut, and firewall, all similar to the larger CH 640, CH 801, and CH 2000. Much work was done to the controls, which are now more balanced for better feel. The IFR airframe of the 650 LSi is based on what was required to certify the Alarus CH 2000 to FAR 23 Certification. The 650 LS is powered by a TCM (Continental) O-200 with Sensenich fixed-pitch prop. Performance and safety options include a BRS all-aircraft parachute system, AmSafe airbag-seat belts, full electric gyro instruments, and wheelpants. In the experimental kit version, the CH 650’s firewall-forward will accommodate a Jabiru 3300, Lycoming O-235 or -233, or Rotax four-cylinder powerplants as alternatives to the S-LSA version’s TCM O-200. With the Continental O-200 engine, the AMD 650 LS carries 30 gallons of fuel and has a useful load of 550 pounds. (With the Jabiru 3300, the useful load is 625 pounds, leaving a generous 481 pounds with full 24 gallon tanks.) For European pilots who want to fly without getting involved in the assembly and/or finishing of their aircraft, the CH 650 E is now available as a Ready-to-Fly (RTF) ultralight from most of our regional distributors. Assembled locally from genuine Zenair airframe kits, these RTF planes can now be completed with custom features, options and colors to meet your unique needs.
Common equipment list for a typical Ready-to-Fly CH 650 E model: Instruments can include basic flight and engine instruments plus the Dynon EFIS-D100 with flight and engine monitoring capabilities, and avionics such as the Garmin 296 GPS and Garmin SL-30 Nav/com. This advanced panel offers considerable redundancy and makes for an ideal cross-country flyer as well as an excellent training platform (the built-in intercom is a nice feature of the Garmin SL-30). Expect your standard CH 650 E to be equipped with the rocket-powered BRS recovery system as well as a two tone exterior color finishing. 2009 Price: 35820 EURO
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