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
The original Zodiac CH 600 was designed by Chris Heintz as a low-cost primary trainer aircraft. The 1984 Zodiac CH 601 HD is the updated model. New improvements to this model include a wider 44-inch cabin and a larger rear baggage compartment. Standard equipment includes wing baggage lockers, hydraulic disk brakes, electric trim tab, and tinted canopy. Designed to meet the requirements of the sport pilot, the aircraft offers great performance and capabilities, and is easy-to-fly with pilot-friendly characteristics, including a low landing (stall) speed. The aircraft has excellent cross-country flying capability as well as short-field performance of well under a thousand feet. The HD (Heavy duty) version is stressed for + or -6G. The S-series speedwing option features a four foot shorter span and a thinner, tapered aerofoil in the outboard section, with a scarfed tip for enhanced dihedral effect. Other options included wing fuel tanks.
A lightened version of the Zodiac CH 601 HD, the basic CH 601 Zodiac model was developed in 1984 specifically for the Advanced Ultralight (AULA) category in Canada and other European countries, where the CH 601 can be used as a trainer and personal aircraft.
Zenith CH-601 NC41013
With a reduced gross weight, this model’s specifications are very similar to those of the CH 601 HD model. With a lighter gross weight (useful load), a lower empty weight is achieved using lighter materials in selected areas. Registered as an advanced ultralight, the basic CH 601 makes an ideal low-cost trainer and personal aircraft. Bubble canopy was standard, but was available with an open cockpit, taildragger, trigear, or twin-float options. As a certified design, factory pre-assembled aircraft were available direct from the manufacturer. As of Oct 1998, 275 kits were sold and 200 built from plans.
The basic airframe kit for the HD cost $12,620, the HDS Super Zodiac basic airframe kit $13,640, and XL Super Zodiac basic airframe kit $15,890, all in 1998.
CH 601 Super Zodiac
Based on the Zodiac CH 601 HD, the Super Zodiac 601HDS features tapered and shortened ‘speed wings’ to achieve a higher cruise speed. The wing span is reduced to 23 feet, and the wing area is lowered to 98 sq. feet, with the airfoil tapering to a 34 inch chord at the wing tips. The speed wings have full-length ailerons for very responsive controls. The Super Zodiac has the same fuselage and tail sections as the CH 601 HD model; the only difference being the outboard wing panels. The outboard wings of the Super Zodiac and the Zodiac CH 601 HD can be interchanged.
CH601XL
Grossing 100 lb heavier than the CH 601, the CH601XL was designed to accommodate larger engines such as the Continental O-200, Lycoming O-235 and Rotax 912s, all in the 100 hp range. The 601XLhas an entirely new wing, 27 ft span, and has the same dihedral from the root to tip because the aluminium spring maingear legs are attached to the fuselage structure. Construction is of 6061-T6 aluminium with pulled rivets. The new wing also has electrically operated flaps, which reduce the span of the ailerons. The XL canopy is forward tipping with gas spring assist, and behind the seats is a 40 lb baggage area. The cabin area is three inches longer than the 601. The flight controls are cable operated. 2009 Price: 64000 EURO With the new wing flaps, stall speed has been kept low for recreational pilots. The XL design is the product of extensive research and development, and the result of professional engineering by Chris Heintz, a leading designer of light aircraft. The modern design makes use of advanced technologies, while using proven design concepts and simple systems for easy assembly and maintenance. A professional design, the structure has undergone a complete and rigorous flight test and design stress analysis, as well as load testing of critical components. The XL has been configured to take full advantage of its increased useful load: New and larger wing tanks offer a larger fuel capacity resulting in superior range and endurance, and the baggage area behind the seat has also been increased. Also with optional wing storage lockers the baggage capacity of this aircraft is quite exceptional. The XL features a new spring main landing gear system. The standard tricycle gear provides effective ground handling and allows for excellent forward visibility while taxiing. This heavy-duty tricycle gear system was chosen as the standard gear configuration as it provides better stability and control on the ground. The Rotax 912ULS 100HP engine offers great performance and is highly recommended for this aircraft as it provides great reliability, and is very efficient and smooth-running. The Zodiac XL prototype model is powered by the six cylinder Jabiru 3300. Lycoming O-235 (116-hp) and Rotax 912S (100-hp) engines have also been installed and flown in the prototype. The XL has been developed with the FAA’s proposed Sport Pilot / Light-Sport Aircraft category in mind, and offers maximum performance and capability possible under the new FAA category.
CH 601 Engine: Lycoming O-235, 116 hp TBO: 2400 hr Prop: Sensenich Composite sheathed wood, 2 blade fixed pitch Wingspan; 27 ft Wing area: 132 sq.ft Length: 19 ft Height: 6.5 ft Undercarriage: fixed nosewheel Main tires: 5.00 x 5 Nose tire: 5.00 x 5 Seats: 2 Max speed: 148 mph Cruise 75%: 138 mph Range 75% no res; 600 sm Stall with flaps: 44 mph ROC: 930 fpm Takeoff roll: 500 ft Landing roll: 500 ft
CH 601 Engine: Jabiru 3300 Wingspan: 27 ft Wing area: 132 sq.ft Length: 19 ft Height: 6.5 ft Undercarriage: fixed nosewheel Main tires: 5.00 x 5 Nose tire: 5.00 x 5 Seats: 2 Empty weight: 660 lb Useful load: 640 lb Wing loading: 9.85 lb/sq.ft Power loading: 11.2 lb/hp Fuel capacity: 25 USG Baggage capacity: 40 lb Aspect ratio: 5.46-1
CH601UL Engine: Rotax 912, 80 hp Engine range: 65 -100 hp, up to 225 lbs. Wing Span: 27 Ft Wing Area: 130 sq.ft. Length: 19 Ft Empty Weight: 550 Lb. Useful Load: 508 Lb Gross Weight: 1,058 Lb. Wing Loading: 8.0 lb.sq.ft Power Loading: 13.2 Lb./Hp Design Load: +/- 6 “G” Cabin Width: 44 Inches Fuel Capacity (Std): 16 USGallons Fuel Cap Option: 30 USGallons Seats: 2 Landing gear: nose or tail. Performance @ 800 Lb Top Speed: 135 mph Cruise: 120 mph Vne: 150 mph Stall Speed: 39 mph Rate Of Climb: 1,400 fpm Take-Off Roll: 360 ft Landing Distance: 450 ft Service Ceiling: 12,000+ ft Range (Std): 480 sm Range (With option): 820 sm Load Factor: +/- 7.9 G Performance @ 1050 Lb Top Speed: 135 mph Cruise: 120 mph Vne: 150 mph Stall Speed: 44 mph Rate of Climb: 1,200 fpm Take-Off Roll: 430 ft Landing Distance: 550 ft Service Ceiling: 12,000+ ft Range (Std): 480 sm Range (With option): 820 sm Load Factor: +/- 6.0 G
CH 601 HD Engine: Rotax 912, 80 hp Engine Limitations: 65 – 115 hp, up to 265 lbs. Wing Span: 27 ft./8.2 m Wing Area: 130 sq.ft./12 m.sq. Wing Airfoil: NACA 65018 Mod Wing Chord: 4ft 1in/124.5 cm. Wing Aspect Ratio: 5.58 Horiz. Tail Span: 7ft 6in/228 cm. Rudder Tip Height (Tri): 6ft 10in/208 cm Cabin Top Height: 5ft 6in/168 cm. Length: 19 ft./580 cm Empty Weight: 590 lb./267 kg. Useful Load: 610 lb./277 kg Gross Weight: 1,200 lb./544 kg. Wing Loading: 9.2 psf/45 kg/m.sq Power Loading: 15 lb./hp / 6.8 kg./hp Design Load Factor: +/- 6 “G” Cabin Width: 44 Inches/112 cm. Fuel Cap (Std): 16 Gallons (US)/ 60.5 lt With Option Wing Tanks: 30 Gallons (US)/113 lt. Seats: 2 Landing gear: nose or tail. Performance @ 800 lb/362 kg Top Speed: 135 mph/217 km/h Cruise: 120 mph/193 km/h Vne: 150 mph/240 km/h Stall Speed: 40 mph/64 km/h Rate Of Climb: 1,400 fpm/7.1 m/s Take-Off Roll: 360 ft/110 m Landing Distance: 450 ft/137 m Service Ceiling: 12,000+ ft/3,600+ m Range (Std.): 480 s.m./772 km Range (optional tanks): 800 s.m./1285 km Design load (Ultimate): +/- 6.8 G Performance @1,050 lb/476 kg Top Speed: 135 mph/217 km/h Cruise: 120 mph/193 km/h Vne: 150 mph/240 km/h Stall Speed: 44 mph/70 km/h Rate Of Climb: 1,200 fpm/6 m/s Take-Off Roll: 430 ft/131 m. Landing Distance: 550 ft/168 m Service Ceiling: 12,000+ ft/3,600+ m Range (Std.): 480 s.m./772 km Range (With option tanks): 800 s.m./1285 km Load Factor (Ultimate): +/- 6.8 G
CH 601 HDS Engine: Rotax 912, 80 hp Engine Limitations: 65 – 115 hp, up to 265 lbs. Wing Span: 23 ft Wing Area: 98 sq.ft. Length: 19 ft Empty Weight: 590 lb. Useful Load: 610 lb Gross Weight: 1,200 lb. Wing Loading: 12.2 psf Power Loading: 15 lb./hp Design Load (Ultimate): +/- 6 “G” Cabin Width: 44 Inches Fuel Capacity (Std.): 16 Gallons (US) Fuel Capacity (Optional): 30 Gallons (US) Performance @ 800 lb. Top Speed: 150 mph Cruise: 135 mph Vne: 160 mph Stall Speed: 48 mph Rate Of Climb: 1,300 fpm Take-Off Roll: 450 ft Landing Distance: 550 ft Service Ceiling: 12,000+ ft Range (Std): 540 sm Performance @ 1,050 lb. Top Speed: 150 mph Cruise: 135 mph Vne: 160 mph Stall Speed: 54 mph Rate Of Climb: 1,100 fpm Take-Off Roll: 550 ft Landing Distance: 550 ft Service Ceiling: 12,000+ ft Range (Std.): 540 sm
CH 601 HDS Engine: Divers Wing span: 7 m Wing area: 9 sq.m MAUW: 544 kg Empty weight: 263 kg Fuel capacity: 60 lt Max speed: 241 kph Cruise speed: 217 kph Minimum speed: 100 kph Climb rate: 5 m/s Seats: 2 Kit price (1998): £10,600 Fast build kit price (1998): £14,300
CH 601 XL Wing span: 8.23m Length: 5.8 m Wing area: 12.3 sq.m Wing loading: 48 kg/sq.m Empty weight: 300 kg Gross weight: 544 kg Cabin width: 1.1 m Fuel capacity: 2 x 45 lt Useful load: 244 kg Takeoff roll: 152 m Landing dist: 152 m Rate of climb: 1000 fpm Stall with flap: 30 kt Stall no flap: 35 kt Cruise 75%: 110 kt Range: 484-550 nm Endurance 5000 rpm – 100 kt 16 lt/hr: 5.5 hr Endurance 5300 rpm – 110 kt 20 lt/hr: 4.4 hr
Zodiac XL Cruise: 134 mph Stall: 44 mph Range: 760 sm Rate of climb: 980 fpm Takeoff dist: 490 ft Landing dist: 500 ft Engine: Jabiru 3300, 105 hp HP range: 80-125 Fuel capacity: 24 USG Empty weight: 690 lb Gross weight: 1320 lb Length: 20 ft Wing span: 27 ft Wing area: 132 sq.ft Seats: 2 Cockpit width: 44 in Landing gear: nose or tail LSA: yes
Roland Aircraft Zodiac Z-602 XL Stall: 34 kt / 39 mph / 63 kmh Cruise: 127 kt / 146 mph / 235 kmh VNE: 131 kt / 151 mph / 243 kmh Empty Weight: 297 kg / 655 lbs MTOW Weight: 472 kg / 1041 lbs Climb Ratio: 1000 ft/min / 5 m/s Glide Ratio: 10 Take-off distance (50ft obstacle): 820 ft / 250 m Landing distance (50ft obstacle): 980 ft / 300 m
CH 601 Super Zodiac Engine: Rotax 912, 80 hp Wing span: 8.20 m Wing area: 12 sq.m MAUW: 450 kg Empty weight: 248 kg Fuel capacity: 60 lt Max speed: 240 kph Cruise speed: 195 kph Minimum speed: 65 kph Climb rate: 5 m/s Certification: VZ A-UL, PFA Seats: 2 Fuel consumption: 13 lt/hr Kit price (1998): £10,600
With 100 hp the CH-200 will cruise for four hours at 130 mph carrying two passengers and baggage, while 150 hp and an aerobatic option turns the Zenith into a powerful per¬former. (The Zenith is stressed for engines from 85 to 160 hp). First designed and built in 1974. Two ¬place seating is under a sliding canopy in a fuselage formed by four longerons with stiffened skins, blind riveted to longerons. Five bulkheads carry the top skin. The constant-chord wings have a single cantilevered spar with three sections and electronically-operated flaps. One-piece, all-moving, horizontal and vertical control surfaces constitute the tail.
Price 1982: $8,500 (excludes engine, instruments and paint). Units delivered to June 1981: 450.
Engine: 125-hp Gross Weight: 1500 lbs. Empty Weight: 930 lbs Fuel Capacity: 24 USG. Wingspan: 23 ft Length: 20ft 6in. Wing area: 105 sq.ft Top speed: 151 mph. Cruise speed: 141 mph Stall speed: 54 mph. Climb rate: 1100 fpm Takeoff run (to 50ft): 1400 ft. Landing run (from 50ft): 1400 ft Range: 450 sm. Seats: 2 Design load: +9g.
Engine: Lycoming, 150 hp Max speed: 167 mph. Cruise speed: 152 mph Range: 400 sm. Stall speed: 53 mph ROC: 1700 fpm. Take-off dist: 600 ft Landing dist: 600 ft. Service ceiling: 12,000 ft Fuel cap: 24 USG. Empty wt: 970 lbs Gross wt: 1500 lbs. Height: 6.75 ft Length: 20.5 ft. Wing span: 23 ft Wing area: 105 sq.ft. Seats: 2
The Mono-Z is a single-place, scaled-down version of the original Zenith first built in 1974. It offers maximum operating economy with VW power at a three gph cruise. Detachable wings leave an 8-foot-wide section for easy road towing, requiring only 20 minutes to install both wings. It is stressed for 9G’s and with 100-hp becomes a powerful aerobatic performer. Engine range from the VW 1600 to 100-hp Continental.
In his spare time, Heintz began to design and build his own aircraft, which he named the Zenith, anagram of Heintz. After a little more than a year’s work, the two-place low-wing Zenith was rolled out and successfully flown on 22 March 1970 as F-WPZY.
Soon after, detailed blueprints and construction manuals of the aircraft were drawn up and offered to the growing number of interested builders and flyers.
All Aero 