1982: P M & T, Whites Close, Alfreton, Derby, Derbyshire, Great Britain.
Built the Honeybird UL
1980->
Pletnyov Zhuravlic
A single seat single engine, high wing mono¬plane with hybrid control circa 1983. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by weight shift; yaw control by fully flying rudder; no separate roll control; control inputs through weight shift for pitch/yaw/roll. Wing braced from above by kingpost and cables, from below by cables; wing profile single ¬surface. Undercarriage has three wheels in tail dragger formation. Metal tube framework, without pod. Engine mounted below wing driving pusher propeller.
It appears to have a rudder to assist the weight-shift in yaw, a combination which is sufficient to class the Zhuravlic as a hybrid, but it is not clear whether a similar arrangement is used for pitch control or whether the pilot relies solely on weight shift for up/down control.
No details are given of the power unit, except that it is of 350 cc and is coupled to a two blade propeller.
Wing span 31.5 ft, 9.60 m
Engine: 350 cc
Empty weight 121 lb, 55 kg
Max level speed 37.5 mph, 60 kph
Best glide ratio with power off: 30/1
Take off distance 66ft, 20m
Landing distance 33ft, 10m
Service ceding 6600ft, 2000m
Platzer Lilienthal Doppeldecker
Michael Platzer built a Lilienthal Doppeldecker Replica, and it was flown in front of hundreds of spectators on the Wasserkuppe “Kleiner Westhang”.
Photographed at the 1978 first “Otto Lilienthal Memorial” at the Wasserkuppe.
Wing area: 10 m²
Wing span: 7.6 m
Hang glider weight: 18 kg
Platzer P.5 Kiebitz
Based on the 1927 Focke-Wulf S-24 “Kiebitz”, the modern Kiebitz was designed by Michael Platzer and has been available as an UL-biplane kit since 1984. Almost 300 Kiebitz biplanes had been built by homebuilders throughout the world.
Various engine options have flown, including Rotax 2 and 4 stroke, Limbach 2000, Sauer 2100, Nissan MA12, and English built 100 hp Mid-West rotary.
Engine: Nissan 12 P, 50 hp
Wing span: 7.6 m
Wing area: 18.3 sq.m
MAUW: 400 kg
Empty weight: 200 kg
Fuel capacity: 50 lt
Max speed: 140 kph
Cruise speed: 125 kph
Minimum speed: 50 kph
Climb rate: 3 m/s
Certification: Vz
Seats: 2
Fuel consumption: 9.5 lt/hr
Plan price (1998): 1500 DM
Engine: Nissan MA12
Seats: 2 Tandem
Wing Span: 7,6 m
Wing Area: 18,3 sq.m
Length: 6,9 m
VNE: 77 kts
Cruise: 60 kts
Stall speed: 38 kts
Empty Weight: 220 kg / 485 lbs
Max. take-off weight: 472 kg
Platzer P.4 Motte
In 1981 Michael Platzer designed and built Germany’s first legal ultralight with three axis control, the P.4 Motte. It has a spaceframe fuselage and dural tube wings.
A parasol UL, the Motte was rebuilt and fitted with a converted Nissan Micra automobile engine.
P4 Motte BR
Engine: Rotax 462, 52 hp
Wing span: 8.2 m
Wing area: 11.4 sq.m
MAUW: 285 kg
Empty weight: 170 kg
Fuel capacity: 40 lt
Max speed: 145 kph
Cruise speed: 125 kph
Minimum speed: 50 kph
Climb rate: 4 m/s
Certification: Vz
Seats: 1
Fuel consumption: 13 lt/hr
Plan price (1998): 1000 DM
Platzer
1998-2010: Michael Platzer, Am Rohleiber 20, D-34302 Ellenberg, Germany.
In 1981 Michael Platzer designed and built Germany’s first legal ultralight with three axis control, the P.4 Motte.
Pitts Model 12
Designed by Curtis Pitts, the Pitts Model 12 is a 2 place fully aerobatic biplane designed specifically around the 360 HP (400hp) Russian built Vedeneyev M-14P (PF) radial.
In March 1996 the completed Pitts Model 12 was test flown and earned the nickname “Macho Stinker” as part of the long line of Pitts prototypes. The name “Bolshoi” is no longer used. Professional pilot, airshow performer, Ben Morphew performed all acro test flights in the model 12 and decided he wanted one and contacted the Kimballs at Jim Kimball Enterprises for them to provide some of the components.
Marketed by Jim Kimball Enterprises in Zellwood FL in kit and component form. The Kimballs made their own modifications to Model 12, which was known as the HP performance version. The type was available as plans built, HP kit, or factory built Model 12S by Jim Kimball Enterprises.
All are two seat except the 12S, which is a single seater. All are tube and fabric, fully aerobatic, and powered by the M14P or M14PF engine.
Plans Version Model 12
Engine: Vendenyev M14P/PF, 360 hp
Span: 23ft
Length: 20ft 6in
Empty weight: 1550lb
Gross weight: 2250lb
Wing loading: 14.9lb/sq.ft
Fuel: 54 USgallons
Baggage: 40lb
Cruise speed: 170mph
Rate of climb: 2900ft/min
Stall speed: 64mph
Roll rate: 240deg/sec
Range: 500 mile
G Limit: +6, -4.5 (+9, -7.5 ult)
Seats: 2
Useful load: 750lb
Vne: 239 mph
Cruise @70% Power: 175 mph
Cockpit width: 26 in
HP Kit Version Model 12
Engine: Vendenyev M14P/PF, 360 hp
Span: 22ft
Length: 19ft 8in
Empty weight: 1525lb
Gross weight: 2250lb
Wing loading: 15.3lb/sq.ft
Fuel: 54 USgallons
Baggage: 40lb
Smoke: 7 USgallons
Cruise speed: 175mph
Rate of climb: 3200ft/min
Stall speed: 64mph
Roll rate: 300deg/sec
Range: 525 mile
G Limit: +6, -4.5 (+9, -7.5 ult)
Seats: 2
Useful load: 750lb
Vne: 239 mph
Cruise @70% Power: 175 mph
Cockpit width: 26 in
Model 12 S
Engine: Vendenyev M14PF, 360 hp
Span: 21ft
Length: 19ft 8in
Empty weight: 1400lb
Gross weight: 1900lb
Wing loading: 13.8lb/sq.ft
Fuel: 36 USgallons
Baggage: 40lb
Smoke: 12 USgallons
Cruise speed: 75mph
Rate of climb: 3800ft/min
Stall speed: 62mph
Roll rate: 370deg/sec
Range: 350 mile
G Limit: +8, -6 (+11, -9 ult)
Seats: 1
Useful load: 750lb
Vne: 239 mph
Cruise @70% Power: 175 mph
Cockpit width: 26 in
Model 12
Engine: Vendeneyev M-14P, 360hp or 400hp
Wingspan (upper): 23’0″
Wingspan (lower): 22’0″
Length: 20’6″
Useful load: 700 lb
Max speed: 235 mph
Cruise speed: 175 mph
Stall: 64 mph
Range: 520 mi
Model 12 HP
Wingspan (upper): 22’0″
Wingspan (lower): 21’0″
Length: 19’8″
Useful load: 775 lb
Pitts Model 11 Super Stinker
In 1991 Curtis and a group of friends formed a new company, Aero Design Eleven, and he designed the Model 11-260. A single seat Lycoming powered aerobatic biplane incorporating all that has been learned including his “Aerodynamically Boosted Ailerons.” Construction of the model 11 then began.
In 1993 the prototype model 11 was completed by Curtis Pitts, Pat Ledford, Don Lovern, Bill Lancaster and Will Teft. The new airplane was dubbed “Super Stinker” in the tradition of many of the prototype designs Curtis created through the years.
S-1-11B Super Stinker
Engine: IO-540, 250 hp
Speed max: 205 mph
Cruise: 187 mph
Range: 350 sm
Stall: 64 mph
ROC: 3300 fpm
Take-off dist: 300 ft
Landing dist: 1200 ft
HP range: 250-328
Fuel cap: 29 USG
Weight empty: 1025 lb
Gross: 1500 lb
Height: 6 ft
Length: 17.5 ft
Wing span: 18 ft
Wing area: 110 sq.ft
Seats: 1
Roll sate: 360 deg/sec
Landing gear: tail wheel
Pitts S-2
It was not until 1967 that Pitts introduced the two seat S 2A. Although similar to the S 1 in configuration and construction, the S 2A is slightly larger in overall dimensions and shares little commonality in components. In 1973, five 200 hp S 2As were supplied to a British aerobatic team sponsored by Rothmans Tobacco. Five more S 2As were later supplied to the Carling Black Label team in Toronto, Canada. And in mid 1976, the Peruvian Air Force announced an order for six S 2As, for “an unspecified training role.” The single seater’s popularity has been partially eclipsed by that of the two seat version, the S 2A, which went into production early in 1971, and of which nearly 140 have been sold by 1977.
The S 2A is slightly larger in all dimensions than the S 1; no attempt was made at commonality of structure. A tandem two holer with a 200 hp Lycoming engine and a constant speed prop, it is not a tiny airplane. Both wings use symmetrical airfoil sections, the upper considerably thicker than the lower; they are set at an incidence that compromises between the requirements of upright and inverted flight, so that the airplane feels slightly nose high in cruise but comfortably level when inverted. The cockpits are fairly roomy, but the instrument panel is inches from your face, and the optical distortions caused by the edges of the compound curved windshields add to an already (and inevitably) cluttered view. Canopy hoods of plexiglass may be fitted, at the expense of intimacy with the air. The hoods reduce the unpleasant forward pressure of the wind on the rear seat pilot. The cockpit sides are high, blocking visibility, which in the landing disappears altogether. Any object carelessly dropped finds its way into the far end of the tail cone, there to interfere with the elevator controls.
Besides its legendary ability to snap roll several times in succession with little loss of rate, the Pitts is notable for its willingness to be held in any attitude and yet to recover on command. As well as being a highly qualified aerobatic competitor, the S-2A is also ideally suited for advanced aerobatic instruction. It is a two-place aerobatic biplane that offers the student the opportunity to learn aerobatics under the supervision of an instructor.
The S-2B is a two-place 260hp aircraft. Wings and landing gear moved forward 6 in to balance the larger engine.
The S-2E price in 1982 was $50,800 as a complete kit. Units delivered to June 1982: 75.
The S-2S is identical to the S-2A except for the forward fuselage which has been shortened 14 inches to accommodate the larger 285hp Lycoming IO 540 engine, with the wings nine inches further forward and a number of other differences such as symmetrical ailerons which increase roll rate over other Pitts by 60″/sec (Up to 240″/sec). In addition, the front cockpit has been eliminated, making it a single-place plane. The S-2S’s larger size makes it ideal for air show flying as well as aerobatic competition. Its cruising speed of 175 mph combined with its fuel capacity of 35 gallons also gives it excellent cross country capability. With a 5 lb/hp and thrust/weight ratio of almost 1:1, it can, for example, do three vertical rolls in full competition, climb 300ft/min in knifedge and hover for “three or four seconds” at the end of a vertical climb. Climb rate is around 3,000ft/min and its snap roll rate is something like 480o/sec, and other party tricks include the ability to pinwheel, which is a stall turn through 540 degrees.
The first S 2S received its certification in mid 1981. The S-2S price in 1982 was $56,550 as a complete kit. Units delivered to June 1982: 10.
The S-2, S-2A, S-2B, and S-2S are certified under FAA A8SO.
The S2-S was not a Pitts product, but a single place experimental home-built.
S-2A
First built: 1971
Engine: Lycoming AEIO-360-A1E, 200 hp
TBO: 1600 hr
Prop: Hartzell 2-blade, 76-in
Seats: 2
Length: 17.8 ft
Height: 6.4 ft
Wingspan: 20 ft
Wing area: 125 sq.ft
Maximum ramp weight: 1575 lb
Maximum takeoff weight: 1575 lb
Standard empty weight: 1000 lb
Maximum useful load: 575 lb
Maximum landing weight: 1575 lbs
Wing loading: 12.6 lbs/sq.ft
Power loading: 7.9 lbs/hp
Maximum usable fuel: 144 lb
Best rate of climb: 1900 fpm
Service ceiling: 17,000 ft
Maximum speed: 139 kt
Stalling speed: 52 kt
1.3 Vso: 71 kt
75% cruise: 121 kt
55% cruise: 113 kt
Range max fuel /75% pwr: 169nm/1.4hr
Range max fuel / 55% pwr: 209 nm/ 1.9 hr
Turbulent-air penetration speed: 134 kt
Fixed tail wheel under carriage
Min field length: 1150 ft
S-2B
Engine: Lycoming AEIO-540-D4A5, 260-hp
MAUW: 1700 lb
Empty Wt. 1175 lb
Pwr loading: 6.54 lb/hp
Wing loading: 13 lb/sq.ft
Length: 18 ft 9 in
Wing span: 20 ft
Height: 6 ft 7.5 in
Wing area: 125 sq.ft
Stall: 53 kt
Vne: 184 kt
Cruise 65%: 140 kt
Max X-wind: 17 kt
Range (wth res): 300sm
ROC: 2700 fpm
S-2C Pitts Special
Base Price 2009: $165,500
Engine: Lycoming AEIO-540, 260 Hp
TBO: 1200 hr
Fuel type: 100LL
Propeller: Hartzell, constant speed, composite three-blade
Landing gear: Fixed/Conv.
Max ramp weight: 1700 lb
Gross weight: 1700 lb
Max landing weight: 1700 lb
Empty weight: 1155 lb
Useful load: Normal 545 lb (aerobatic 470 lb)
Payload, full fuel: 371lb
Usable fuel: 28 USgal (23 USgal aerobatic)
Oil capacity: 12 qt
Wingspan: 20 ft
Overall length: 17 ft. 9 in
Height: 6 ft. 5 in
Wing area: 127.5 sq. ft
Wing loading: 13.3 lbs./sq. ft (12.7 lbs./sq. ft aerobatic)
Power loading: 6.59 lbs./hp (6.25 lbs./hp aerobatic)
Wheel base: 163 in.
Wheel track: 60.75 in.
Wheel size: 5.00 x 5
Cabin width: 2 ft. 4 in
Cabin height: 6 ft. 11 in
Baggage capacity: 20 lb
Stall: 56 kt
Max cruise: 169 kt
Cruise speed 75% power: 157 kt
Cruise speed 65% power: 150 kt
Cruise speed 55% power: 147 kt
Max range (w/ res) 75% power: 246 nm
Max range (w/ res) 65% power: 274 nm
Max range (w/ res) 55% power: 300 nm
Fuel consumption 75% power: 13.5 USgph
Fuel consumption 65% power: 12 USgph
Fuel consumption 55% power: 11 USgph
Estimated endurance (65% power w/1 hr reserve): 5.6 hr
Best rate of climb (SL): 2900 fpm
Takeoff ground roll: 554 ft
Takeoff over 50-ft. obstacle: 860 ft
Landing ground roll: 750 ft
Landing over 50-ft. obstacle: 1200 ft
Pitts S-2C
Engine: Lycoming AEIO-540, 260 HP
Propeller: The Claw by Hartzell 76: Composite Constant Speed
Length: 17 feet 9 inches
Height: 6 feet 5 inches
Wing Span : 20 feet
Wing Area : 127.5 square feet
Wing Loading : 13.3 lb/sqft (normal)/12.7 lb/sqft (aerobatic)
Power Loading : 6.59 lb/hp (normal)/6.25 lb/hp (aerobatic)
Seats : 2 tandem
Cabin Length : 6 feet 11 inches
Cabin Width : 28 inches
Cabin Height : 47 inches
Empty Weight : 1,155 pounds
Maximum Gross Weight : 1700 pounds
Useful Load : 545 lb (normal)/470 lb (aerobatic)
Payload w/Full Fuel : 371 pounds
Fuel Capacity w/5 Gallon Wing Tank: 29 U.S. gallons (28 gallons usable)
Aerobatic Flight Load Limits: +6 G/-5 G
Takeoff Distance Ground Roll: 554 feet
Takeoff Distance Over 50 ft Obstacle: 860 feet
Max Demonstrated Crosswind Component: 17 kt
Rate of Climb, Sea Level, Minimum Weight: 2,900 fpm
Maximum Level Speed, Sea Level: 169 kt
Cruise Speed w/30 min rsv. at 75% Power: 150 KTAS/1.6 hours
Range w/30 min rsv. at 75% Power: 284 st. miles
Fuel Consumption at 75% Power: 84 pph/14 gph
Best Economy: 6,000 feet
Landing Distance over 50 ft Obstacle: 1,200 feet
Landing Distance, Ground Roll: 750 Feet
VY (Best Rate of Climb): KIAS 82
VA (Design Maneuvering): KIAS 134
VNO (Max Structural Cruising): KIAS 134
VNE (Never Exceed): KIAS 185
VSI (Stall, Clean): 56 KIAS
Aviat Pitts S2C
Engine: Lycoming AEIO-540-D4A, 260 hp
TBO: 1200 hr
Fuel type: 100LL
Propeller: Hartzell Constant Speed
Landing gear: Fixed Bungee
Max ramp weight: 1700 lb
Gross weight: 1700 lb
Landing weight: 1700 lb
Empty weight, std: 1155 lb
Useful load, std: 545 lb
Payload, full std. fuel: 377 lb
Useful fuel, std: 28 USG
Oil capacity: 12 qt
Wingspan: 20 ft
Overall length: 17 ft. 5 in
Height: 6 ft. 5 in
Wing area: 127.5 sq. ft
Wing loading: 13.3 lbs./sq. ft
Power loading: 6.25 lbs./hp
Wheel size: 5.00 x 6
Seating capacity: 2
Cabin width: 24 in
Cabin height: 41 in
Baggage capacity: 20 lb
Cruise speed 75% power: 160 kt
Cruise speed 65% power: 156 kt
Cruise speed 55% power: 152 kt
Max range (w/ reserve) 75% power: 270 nm
Max range (w/ reserve) 65% power: 290 nm
Max range (w/ reserve) 55% power: 310 nm
Fuel consumption 75% power: 14.0 USgph
Fuel consumption 65% power: 12.9 USgph
Fuel consumption 55% power: 11.5 USgph
Vso: 56 kt
Best rate of climb (SL): 2900 fpm
Service ceiling: 29,500 ft
Takeoff ground roll: 554 ft
Takeoff over 50-ft. obstacle: 860 ft
Landing ground roll: 750 ft
Landing over 50-ft. obstacle: 1200 ft
S-2E
Designed in 1966
Gross weight: 1,500 lb
Empty weight: 980 lb
Useful load: 520 lb
S-2S
First built: 1977
Engine: Lycoming AEIO-540-D4A5, 260 hp
TBO: 1600 hr
Prop: Hartzell 2-blade
Seats: 1
Length: 17.4 ft
Height: 6.4 ft
Wingspan: 20 ft
Wing area: 125 sq.ft
Maximum ramp weight: 1575 lb
Maximum takeoff weight: 1575 lb
Standard empty weight: 1100 lb
Maximum useful load: 475 lb
Maximum landing weight: 1575 lb
Wing loading: 12.6 lbs/sq.ft
Power loading: 5.7 lbs/hp
Maximum usable fuel: 210 lb
Service ceiling: 20,000 ft
Maximum speed: 185 kt
Stalling speed: 58 kt
Turbulent-air penetration speed: 134 kt
Fixed tail wheel under carriage
Pitts S-1
Curtis Pitts began designing the single-seat S 1 in 1942. The 55 hp prototype flew in September 1944, but was repowered with 90hp Franklin and sold to a cropduster, who reportedly was so hard of hearing that one time he didn’t hear the motor quit and crashed—no injury, but the plane was written-off.
A second Special, with 85hp Continental C-85, went to aerobat Betty Skelton in 1947 as Li’l Stinker (NX86401/N22E) (still active in 1975, displayed at NASM 2001).
Black Beauty (built by Pitts for Caro Bailey) started the trend toward more power by packing a 125 hp Lycoming O 290.
The Pitts Special is a single seat, open cockpit, fully aerobatic biplane. The fuselage is made up of a welded steel tube structure to which plywood formers and wooden stringers are fitted, the whole being fabric covered except for the aluminium front panels. Roth wings have solid spruce spars to which are fitted wooden ribs, each wing panel being internally and externally wire braced and fabric covered. The wings are set at 6 degrees sweep back at the quarter chord line, Frise type ailerons are fitted only to the lower wings, which have 3 degrees dihedral. Single faired interplane struts and N type cabane struts are fitted. The wing airfoil section is an M6.The main undercarriage is made up of welded steel tube and utilises rubber cord shock absorption. The tail wheel is steerable. A 16 Imperial gallon fuel tank is located immediately aft of the firewall. Engines of from 100-200 h.p. may be fitted.
The 1960 S1-C or Flatwing incorporated a semi-symmetrical airfoil and lower-wing ailerons with a Continental O-200 engine. The first S1-C was Pat Ledford’s (N8L) and the plans were drawn up as it was constructed. They were redrawn in the ’90s by Steen Aero Lab, incorporating many minor changes, one of which was the inclusion of the slightly-longer S1-S fuselage.
The S-1D is a four aileron version with a modified M-6 airfoil, completely certified. Kits and plans were marketed to home-builders.
The S1-E is an experimental, home-built version of the S1-S, with some crossover in names and parts provided by the factory between the -S and –E. An unknown number of S1-E became certified S1-S.
The S-1S model was first year built in 1974. The price in 1982 was $41,690 as a complete kit, or certified under FAA A8SO.
S1-S / Roundwing of 1973 was an S1-D with two different symmetrical airfoils on the upper and lower wings with four ailerons.
S1-S production continued until 1981, when its plans were released for home-builders. Any home-built S1-S predating 1981 was not a true S1-Ss.
S1-SS or Super Stinker Pitts Special used an airfoil and aileron setup derived from the S-1-11/-11B “Super Stinker” aircraft, which was not a Pitts Special nor was it an S1, but a new design meant for world championship aerobatic competition. S1-SS was offered by Steen Aero Lab since the ’90s as supplemental wing plans to fit onto any S1 fuselage.
The 1981 S-1T is a single-seater model which claims roll rates of up to 240 degrees/second. A certified version that superseded the S1-S, with a 200hp engine, constant-speed prop, and new aileron design. Pitts has sold more than 2500 sets of plans for the popular S-1T.
By 1998 the Pitts S-1 was marketed by Aviat Aircraft.
S1 Special
1945
Engine: 55hp Lycoming
Wingspan: 20’0″
Length: 18’3″
Seats: 1
S-1C
Engine: Lycoming IO-360-B4A, 180 hp
Speed max: 147 mph
Cruise: 143 mph
Range: 250 sm
Stall: 64 mph
ROC: 2600 fpm
Take-off dist: 300 ft
Landing dist: 600 ft
HP range: 125-200
Fuel cap: 20 USG
Weight empty: 720 lb
Gross: 1150 lb
Height: 6.25 ft
Length: 15.5 ft
Wing span: 17.33 ft
Wing area: 98 sq.ft
Seats: 1
Landing gear: tail wheel
Engine: Lycoming O-320, 150 hp
Cruise: 150 mph
ROC: 2650 fpm
Range: 300 sm
Span: 17 ft 5 in
Length: 15 ft 6 in
Empty wt: 720 lb
Max wt: 1050 lb
S-1C
Engine: 1 × Textron Lycoming AEIO-540-D4A5, 260 hp (194 kW)
Wingspan: 17 ft 4 in (5.28 m)
Length: 18 ft 9 in (5.71 m)
Maximum speed: 210 mph (338 kph)
Maximum range: 319 miles (513 km)
Service Ceiling: 21,000 ft (6,400 m)
S1-D
Enine: 180hp Lycoming IO-360B
Wingspan: 17’5″
Length: 15’6″
Useful load: 425 lb
Max speed: 145 mph
Cruise speed: 135 mph
Stall: 64 mph
Range: 230 mi
Ceiling: 22,000′
S-1S
First built: 1973
Engine: Lycoming AEIO-360-B4A, 180 hp
TBO: 2000 hr
Prop: Sensenich 2-blade, 72-in
Seats: 1
Length: 15.5 ft
Height: 6.3 ft
Wingspan: 17.3 ft
Wing area: 98.5 sq.ft
Maximum ramp weight: 1150 lb
Maximum takeoff weight: 1150 lb
Standard empty weight: 740 lb
Maximum useful load: 410 lb
Maximum landing weight: 1150 lb
Wing loading: 11.7 lbs/sq.ft
Power loading: 6.4 lbs/hp
Maximum usable fuel: 120 lb
Best rate of climb: 2500 fpm
Service ceiling: 18,000 ft
Maximum speed: 139 kt
75% cruise: 123 kt
55% cruise: 115 kt
Stalling speed: 56 kt
Turbulent-air penetration speed: 134 kt
Fixed tail wheel under carriage
Payload max fuel: 257 lb
Range max fuel/75% pwr: 148 nm/1.2 hr
Range max fuel / 55% pwr: 190 nm/ 1.7 hr
Min field length: 800 ft
Fuel cap: 114 lb
S-IT
Gross Wt. 1150 lb
Empty Wt. 830 lb
Fuel capacity 20 USG
Wing span 17’4”
Length 15’6”
Engine 200-hp AEIO-360-AE1
Top speed 185 mph
Cruise 175 mph
Stall 64 mph
Climb rate 2800 fpm
Aviat Aircraft Pitts S-1
Engine: Lycoming
Wing span: 5.27 m
Wing area: 9.06 sq.m
MAUW: 522 kg
Empty weight: 345 kg
Fuel capacity: 72 lt
Max speed: 222 kph
Cruise speed: 195 kph
Minimum speed: 100 kph
Climb rate: 12.5 m/s
Seats: 1
Fuel consumption: 35 lt/hr
Plan price (1998): US$250
All Aero 