In 1950 five manufacturers entered a competition to replace the fleet of L-4 and L-5 observation planes. The specifications included takeoff and land within 600 feet, cruise at 89 mph, have an observation speed of 49 mph, climb at 800 fpm, three hour endurance, service ceiling of 16,000 ft, and weigh 1000 lb empty.
The Cessna engineers put together the wings from the 170, a tail from the 195 and a new fuselage with transparent panels in the roof and a wider access door and new landing gear, to make the Cessna 305. Cessna’s design was a light-weight strut-braced high-wing monoplane, which provided accommodation for a pilot and three passengers.
Power was from a Continental O-470 of 213hp / 108kW and fixed pitch prop. The fixed pitch prop limited the cruise to 30% power so as not to overspeed the engine. The Birddog moved from design sketches to first flight in just 90 days. The landing requirement required 60 degrees of flap and a full stall, three-point landing technique with a high rate of sink. The O-1 is not cleared for aerobatics.
Cessna was awarded the contract with an initial order of 418 aircraft on 29 May 1950. The first military designated L-19s were delivered in December 1951 and sent to Korea, arriving there on 16 February 1951.
L-19A
The Model 305A differed from the 170 by having the aft fuselage redesigned to give a clear view to the rear and by the provision of transparent panels in the wing centre-section, which formed the cabin roof. A wider access door gave room to load a standard stretcher, for which support brackets were installed. Spring steel landing gear and slotted high lift flaps were fitted along the trailing edge of each wing.
By June 1951 there were 166 L-16s in Korea, and they had amassed about 20,000 hours.
Deliveries of production aircraft began in December 1950, under the designation L-19A and with the name Bird Dog, and by October 1954, 2,486 had been delivered, of which 60 were diverted to the US Marine Corps which designated them OE-1.
An L-19A-IT instrument trainer version was developed in 1953. By 1954 a total of 2486 had been delivered, of which 60 were diverted to the US Marine Corp where they were e-designated OE-1.
In 1956, the Army ordered 100 TL-19D instrument trainers. This was a growth version of the original instrument trainer with a constant-speed prop and a higher gross weight — 2,400 pounds. The next year, the order was expanded by another 207 TL-l9Ds and an uprated version of the basic L-19 was ordered —the “E” model which boosted the higher gross weight and “some minor improvements.”
Sixty Bird Dogs were delivered to the USMC as the O-1B, and the TO-1D is a dual control training version of the O-1A.
The L-19E was the final version to bring total production of Bird Dogs to 3,431. With redesignation in 1962, the US Army’s L-19A, TL-19D and L-19E aircraft became O-1A, TO-1D and O-1E respectively. The US Marines’ OE-1 became O-1B and this service also acquired 25 of the higher-powered O-1C. US Army trainers, derived from standard production aircraft, had the designations TO-1A and TO-1E.
Some O-1 were manufactured by Fuji Heavy Industries for the Japanese Ground Self-Defence Force.
The model 321, or O-1C was an extensively redesigned version of the O-1B Bird Dog for the USMC. The prototype of the O-1C was first flown in 1955 and twenty-five were built. Pilot and observer were protected by flak curtains and seat armour, and all fuel tanks are self-sealing. A 250 lb bomb or three air to surface rockets may be carried beneath each wing. The structure of the O-1C is similar to the O-1B apart from some strengthening for the more powerful engine.
The US Air Force acquired many of the US Army’s O-1s for use by forward air controllers in Vietnam; former TO-1Ds and O-1As were redesignated O-1F and O-1G respectively when equipped for this role.
The O-1Fs were TO-1Ds modified to O-1D standard by deleting the dual controls and rear seat instrument panel and the modified to -F standard by fitting under-wing hard points and army communication gear.
The US Navy ordered 25 of a progressive development designated OE-2. These differ principally in having a longer nose to house a 260 hp Continental SO-370 engine, and taller, more angular tail surfaces.
Cessna had delivered 3,431 examples by the time production ceased including 126 for the French – the bulk of these had been built as O-1s (L-19As), with later variants introducing uprated equipment and the ability to carry wing stores like target marking rockets
Of these, one was a civil prototype and four were evaluation models for civilian use. These were put into service in aerial application and although they got high marks with the dusters, Cessna could not see enough of a market for the aircraft and never put it into production. As far as FAA is concerned, the Birddog is the Cessna 305A and all those converted to civilian use are so designated in FAA records.
O-1s were also built under licence by Fuji in Japan.
Ector Aircraft Co., of Odessa, Texas produced (until stocks of new parts are exhausted) the Ector L-19 Mountaineer and the standard Ector (Cessna) 305. The basic aircraft is delivered with a majored Continental 0-470-11 and the McCauley fixed-pitch prop or with a Continental 0-470-13 or Lycoming 0-540-A4B5, a constant-speed prop and manifold pressure gauge.
Although long since retired from USAF service, a modest number of O-1’s continue to thrive with a handful of air arms across the globe, whilst surplus Bird Dogs have recently enjoyed a renaissance across North America and Australia.
O-1C Engine: 265 hp Continental O-470-2 Wingspan: 36 ft 0 in Length: 26 ft 3 in Height: 7 ft 10 in Wing area: 174 sq.ft Empty weight: 1853 lb Max loaded weight: 2650 lb Max speed: 185 mph Econ cruise: 122 mph ROC: 1300 fpm Time to 20,000ft: 22.6 min Range: 575 mi at 10,000 ft
CE-305A Engine: Continental O-470-11, 213 hp. Empty wt: 1700 lbs. MTOW: 2100 lbs (optional): 2300 lbs. Height: 7 ft 6 in. Length: 25 ft 9.5 in. Wing span: 36 ft. Cruise: (@ 2300 rpm): 78 kts. Stall: 42 kts.
Cessna L-19E / O-1E Bird Dog Engine: 1 x Continental O-470-11, 213 hp, 159kW Wingspan: 10.97 m / 35 ft 12 in Length: 7.85 m / 25 ft 9 in Height: 2.22 m / 7 ft 3 in Wing area: 16.16 sq.m / 173.94 sq ft Maximum Speed: 130mph (209kmh; 113kts) Maximum Range: 530miles (853km) Rate-of-Climb: 1,040ft/min (317m/min) Service Ceiling: 20,341ft (6,200m; 3.9miles) Accommodation: 2 Hardpoints: 2 Empty Weight: 1,614lbs (732kg) Maximum Take-Off Weight: 2,401lbs (1,089kg)
L-19 Engine: Continental O-470-11B, 213 hp Prop: McCauley 2 blade 90 in fixed pitch Wingspan: 36 ft Wing area: 174 sq.ft. Length: 25 ft 9 in Height: 7 ft 6 in Seats: 2 Max gross wt: 2400 lb Empty wt: 1480 lb Useful load: 920 lb Wing loading: 13.79 lb/sq.ft. Power loading: 11.26 lb/hp Toatl fuel cap: 42 USG Useable fuel cap: 36 USG Baggage cap: 100 lb Max speed: 179 mph Cruise 2300 rpm: 104 mph Stall clean: 44 mph Stall with flap: 40 mph ROC SL: 1350 fpm Service ceiling: 21,300 ft Takeoff ground roll: 355 ft Landing ground roll: 320 ft
Cessna L-19A Bird-Dog Engine: 213 h.p. Continental O-470-11 Span: 36 ft Length: 25 ft Height: 7 ft 6 in Wing area: 174 sq.ft Empty weight: 1400 lb Loaded weight: 2200 lb Max speed: 146 mph at 5000 ft Cruise: 115 mph ROC: 1290 fpm Service ceiling: 21,200 ft Range: 620 mi Seats: 2
Cessna O-1G Birddog Engine: 213hp / 158 kW Continental O-470-11 Fuel: 100 Octane Wingspan: 36 ft / 10.97 m Length: 25 ft 9 in / 7.85 m Height: 7 ft 6 in / 2.29 m Empty weight: 1,400lbs / 635 kg Maximum Take-off weight: 2,200lbs / 998 kg Max speed: 115 mph / 185 kph Service ceiling: 18,500 ft / 5638.8 m Max range: 530 mi / 742.08 km Armament: Eight 2.75 inch (70mm) smoke rockets Maximum Speed: 131 knots / 151 mph / 243 km/h
Cessna’s light twin, the Model 303 (N303PD), flew for the first time in February 1978. A top speed of 140 knots was reached on the Valentine’s Day flight, which lasted 54 minutes. It then designated Cessna Model 303 Clipper
In this prototype form it was a four-seat aircraft of low-wing monoplane configuration with the wing incorporating a super-critical aerofoil section. Other features included retractable tricycle landing gear, swept vertical tail surfaces with a long dorsal fin, extensive use of bonded construction and power-plant comprising two 119kW engines. Before the certification programme began it was superseded by a new Model T303 which reverted to conventional construction, had six-seat accommodation, was powered by two turbocharged engines of increased output, and had acquired the new name Crusader because the earlier title of Clipper infringed a US trademark.
Cessna’s Crusader had its keel laid in 1977, the airplane first flew in 1978 and was quickly laid to rest. The highly touted GAW 1 airfoil apparently was not talented enough in this application, and Cessna felt it would not be able to compete in a market that turned out to be small and overpopulated. That proved to be a good decision. So did the next one: to reinvent the light twin in a new form. The cabin class design was popular, so the target airplane became a basic size cabin class twin with good performance, excellent handling qualities and a big look. The result was an all new design called the Crusader (or T303, turbochargers having been added).
Cessna claimed the Crusader was the first lightweight twin of its class to have full IFR avionics and equipment as standard, and that handling of the aircraft benefited from the high set tailplane, coupled with unusually, counter rotating engines, which minimise engine torque effect. Production model Crusaders were certificated in August 1981, and first deliveries followed in October. When production ceased in 1986 297 had been delivered. Although it replaced the model 337, sales didn’t improve much and only a relatively small number were made.
T303 Crusader Engines: Continental TSIO-520-AE, 250 hp, 186kW and 1 x Continental LTSIO-520-AE. TBO: 2,000 hrs. Props: McCauley 3-blade, 74-in. Length: 30ft 5in. / 9.27 m Height: 13ft 2in. / 4.06 m Wingspan: 11.9 m / 39 ft 1 in Wing area: 189.2 sq.ft. / 17.58 sq.m Maximum ramp weight: 5,175 lbs. Maximum takeoff weight: 5,150 lbs / 2336 kg Standard empty weight: 3,305 lb / 1499 kg. Maximum useful load: 1,870 lbs. Zero-fuel weight: 4,850 lbs. Maximum landing weight: 5,000 lbs (5,150 lbs. with optional heavy-duty wheels and brakes). Wing loading: 27.2 lbs/sq.ft. Power loading: 10.3 lbs/hp. Maximum usable fuel 153 gals/918 lbs. Best rate of climb: 1,480 fpm @ 103 kts. Climb gradient: 871 ft/nm. Rate of climb @ 8,000 ft: 1375 fpm. Certificated ceiling: 25,000 ft / 7620 m. Maximum single-engine rate of climb: 220 fpm @ 97 kts. Single-engine climb gradient: 135 ft/nm. Single-engine service ceiling: 13,000 ft. Maximum speed: 2l6 kts. Cruise @ 65% pwr @ 8,000ft: 167 kts. Cruise @ 72% power @ 10,000ft 180 kts. Cruise @ 65% pwr @ 18,000 ft: 181 kts. Cruise @ 72% power @ 20,000 ft: 197 kts. Fuel flow @ 65% pwr @ 18,000 ft: 147 pph. Fuel flow @ 72% power @ 20,000 ft: 31.3 gph. Endurance at 72 % power, no reserve: 4.9 hrs: Stalling speed clean: 68 kts. Stalling speed gear/flaps down: 62 kts. Turbulent-air penetration speed: 148 kts. Range: 1889 km / 1174 miles
Cessna engineers fitted a retractable undercarriage to a model 182B resulting in the 210. The first 210s were flown in January 1957, and the airplane has always been a 160 knot cruiser that can go 175 knots. When its hydraulically activated landing gear is retracted, the gear doors seal it completely within the fuselage. (The 1979 model no longer has the all covering doors; the main gear nestles up into open wheel wells. As a result, the gear extension speeds have been raised 25 knots, and a more simple design has been obtained without any loss in performance.) The first in the Cessna range to introduce the swept vertical tail surfaces and a fully-retractable undercarriage.
The first production aircraft flew in December 1959 powered by a 194kW Continental IO-470-E engine. The initial 210s carried four people; then in 1964, two seats were added. The four seat 210s were made from 1960 to 1963, with wing struts, two windows per side and no rear window. The early models are powered by the 260 horsepower, fuel-injected Continental with a 1,200 hour TBO. Those 210s carried 65 USG of fuel, but in 1962, when the option was first offered, most buyers chose the 84 gallon long range tanks. The early 210s gross at 2,900 pounds, with a standard useful load of about 1,165 pounds.
An example of the Model 210 was first demonstrated in Britain early in 1960.
The 1961 210A model introduced two more cabin windows, additional headroom and an improved heating and ventilating system, and by 1963 an autopilot was offered as an option. The 1962 210B introduced a re-designed fuselage with all-round cabin vision and a simplified hydraulic system. The 1963 210C differed only in its restyled cabin, but the 1964 210D Centurion has a 285 hp engine in place of the 260 hp Continental IO-470-S. In January 1965 the Model 210E Centurion had supplanted earlier versions and was powered by a 213kW Continental IO-520-A. The Model 210F followed in 1966.
The Centurion, a heavier, bigger, more powerful 210, was introduced in 1964. The first Centurion had a 285 hp Continental, still fuel injected, still with a 1,200 hour TBO. The gross weight was increased to 3,100 pounds, which raised the useful load by 105 pounds. The cabin was expanded to seat six with the addition of two tiny rear seats that can be folded flush with the baggage compartment floor.
In 1966 the first turbocharged model became available in the form of the T210F Turbo-System Centurion with a 213kW Continental TSIO-520C; the extra power conferred a useful increase in performance, particularly in altitude. A new wing, first flown on a T210 in June 1965, was later introduced on production aircraft, and eliminated the need for external bracing struts. The turbocharged version eventually outsold the basic model two to one. In 1967, the Centurion lost its wing struts, took on two standard 45 gallon fuel tanks and gained 100 pounds, for a gross of 3,400. With a 1,960 pound empty weight, the full fuel payload went to about 905 pounds. In 1969, the TBO on the engine went up to 1,500 hours. The following year, the cabin was enlarged and the rear seats expanded to make the airplane an honest six seater. The gross weight went up again, this time to 3,800 pounds, and the useful load rose to 1,720, for a full fuel payload of about 1,186 pounds. At the same time, the old, square passenger windows were replaced by a three foot long window on each side, aft of the doors. The engine, still rated at 285 hp, was allowed to develop 300 hp for takeoff and five minutes of climb out. By 1970 Cessna had dropped its suffix letter system from model numbers and in that year introduced two new versions, the Centurion II and Turbo Centurion II which incorporated a factory-installed package of avionics and equipment as standard, these being produced alongside the Centurion and Turbo Centurion. By then the Centurions were of six-seat capacity and offered powerplant options of a 224kW Continental IO-520-L for the Centurion and a 213kW TSIO-520H for the Turbo Centurion. In 1975, the three blade prop became standard. The 210L models featured larger picture windows which greatly im¬proved the visibility for the rear seat passengers. The Turbo Centurion was first built with strutted wings. That was remedied in 1967 with a center section to make the Turbo Centurion’s wing full cantilever, eliminating the struts. A new airfoil was incorporated at the same time. Gone was the classic Cessna wing, swapped for a new laminar flow section. The strutless wing arrangement added 95 pounds to the empty weight, increased the stalling speed six knots, resulted in a 154 fpm decrease in rate of climb (largely from a 100 pound gross weight increase to preserve useful load) and improved the cruising speed but two knots. The first strutless Turbo Centurion almost had too much dihedral in the wings but that was quickly remedied. The Centurion’s performance has been greatly improved, too, through a series of small but important aerodynamic refinements. The 1975 Centurion is basically the same airframe as that used since 1970, when six full size seats were first offered. It uses the same engine, also, but incorporates such features as a retractable cabin step which gives it 10 knots additional cruise at maximum power settings. In November 1977 a new pressurised version of the Model 210, the Pressurized Centurion, was announced. Generally similar to the standard Centurion, it differed by having a pressure cabin and a 231kW Continental TSIO-520-P which incorporated a high-capacity turbocharger to support the pressurisation system, and like the earlier models was available in standard and Pressurized Centurion II versions.
Cessna P210N Pressurized Centurion II
The 210R model, with a longer span stabiliser and cambered wingtips, was produced for the 1986 sales year and only 112 were produced in the final year of production. All six versions remained available until 1986 when sales slowed down and at the end of 1987 when production ceased, a total of 8,453 Model 210s and Centurions had rolled off the line together with 851 Pressurized Centurions. Turbocharged Centurions established several world records in their class: including time-to-height records, a round the world speed record of 204km/h, and an altitude record of 12905m established on 13 May 1967.
210D 1964 Engine: Continental IO-520-A, 285 hp Wingspan: 36 ft 7 in Length: 27 ft 9 in Height: 9 ft 9 in Wing area: 173.5 sq.ft Empty weight: 1830 lb Loaded weight: 3100 lb Max speed: 199 mph Cruise 75%: 191 mph at 6500 ft ROC: 1210 fpm Max range: 1305 mph
1973 Cessna Centurion T210L Base price: US$544,295 Engine: Continental TSIO-520H, 285 hp to 17,000 ft TBO (hrs.): 1400 Fuel type: 100/100LL Propeller type: McCauley CS/3-blade Landing gear type: Tri./Retr. Max ramp weight (lbs): 3800 Gross weight (lbs.): 3800 Landing weight (lbs.) 3800 Empty weight, std. (lbs.): 2195 Useful load, std. (lbs.): 1605 Useful fuel, std (gals.): 89 Payload, full std. fuel (lbs.): 1071 Wingspan: 36 ft. 9 in. Overall length: 28 ft. 3 in. Height: 9 ft. 7 in. Wing area (sq. ft.): 175.1 Wing loading (lbs./sq.ft.): 21.7 Wheel size (in.): 6.00 x 6 Power loading (lbs./hp):12.3 Seating capacity: 6 Cabin doors: 2 Cabin width (in.): 45.5 Cabin height (in.): 48 Cruise speed (kts.) 80% power: 198@20,000 ft. Cruise speed (kts.) 70% power: 190@20,000 ft. Fuel consumption (USgph.) 80% power: 17.2 Fuel consumption (USgph.) 70% power: 15.5 Range (plus reserve, nm) 80% power: 830 Range (plus reserve, nm) 70% power: 880 Vso (kts.): 57 Best rate of climb, SL (fpm): 1115 Service ceiling (ft.): 28,500 Takeoff distance (ft.): 1170 Takeoff over 50 ft. obstacle (ft.): 2030 Landing distance (ft.): 765 Landing over 50 ft. obstacle (ft.): 1500
1977 Cessna T210M Engine: Continental TSIO-520H, 310 hp TBO hr: 1400 Propeller type: Const. spd. Landing gear type: Tri/Retr. Gross weight (lbs.): 3800 Empty weight, std. (lbs.): 2324 Useful load, std. (lbs.): 1476 Fuel (USgals.): 89 Wingspan: 36 ft. 9 in. Overall length: 28 ft. 2 in. Height: 9 ft. 5 in. Wing area (sq. ft.):175 Seating capacity: 6 Cabin width (in.): 42.5 Cabin height (in.): 48 Baggage capacity (lbs.): 240 Cruise speed (kt) 75% power @ 24,000 ft: 198 Cruise speed (kt) 65% power @ 6,500 ft.: 168 Max range (w/ reserve) (nm) 75% power: 870 Max range (w/ reserve) (nm) 65% power: 880 Fuel consumption (USgph) 70% power: 17.8 Fuel consumption (USgph) 65% power: 14.0 Estimated endurance (65% power with 1-hr. reserve): 5 hrs. 30 mins. Stall speed (gear, flaps down) (knots): 56 Best rate of climb (fpm): 1030 Service ceiling (ft.): 28,500 Takeoff ground roll (ft.): 1150 Landing ground roll (ft.): 765
CE-210N Engine: 1 x Continental IO-520-L, 300 hp. TBO: 1700 hrs. Prop: McCauley 3 blade, constant speed 80 in. Seats: 6. Length: 28.2 ft. Height: 9.7 ft. Wingspan: 36.8 ft. Wing area: 175 sq.ft. Wing aspect ratio: 7.7. Max ramp wt: 3812 lbs. Max take off wt: 3800 lbs. Standard empty wt: 2153 lbs. Max useful load: 1659 lbs. Max landing wt: 3800 lbs. Wing loading: 21.7 lbs/sq.ft. Power loading: 12.7 lbs/hp. Max useable fuel: 522 lbs. Climb rate: 950 fpm @ 96 kts. Climb gradient: 597 ft/nm. Rate of climb @ 8000 ft: 560 fpm. Service ceiling: 17,300 ft. Max speed: 175 kts. Cruise @ 65% power @ 8,000ft: 160 kts. Fuel flow @ 65% power @ 8,000ft: 82 pph. Endurance @ 65% power @ 8,000ft: 6.2 hr. Stalling speed clean: 65 kts. Stall speed gear/flaps down: 56 kts. Turbulent air penetration speed: 125 kts. Retractable nose wheel undercarriage.
1983 Cessna Turbo 210N Centurion II Engine: Continental TSIO-520-R Takeoff power: 310 hp @2700 rpm / 36.5-in manifold pressure Max continuous power: 285 hp @2600 rpm / 35-in. manifold pressure TBO hrs.: 1600 Fuel Type:100/100LL Propeller type/diameter: McCauley CS/80 in Landing Gear type: Tri./Retr. Max ramp weight (lbs.): 4016 Gross weight (lbs.): 4000 Landing weight (lbs.): 3800 Empty weight, std. (lbs.): 2303 Useful load, std. (lbs.): 1697 Payload (lbs.): 896 with 120-USgallon auxillary tanks Usable fuel, std. (USgals.): 90 Oil capacity (qts.): 11 Wingspan: 39 ft. 9 in With Flint Tip Tanks Overall length: 28 ft. 2 in. Height: 9 ft. 8 in. Wing area (sq. ft.):181 Wing loading (lbs./sq. ft.): 22.9 Power loading (lbs./hp.): 12.9 Wheel base (in.): 72 Seating capacity: 6 Cabin doors: 2 Cabin width (in.): 41.8 Cabin height (in.): 48 Baggage capacity (lbs.): 370 Cruise speed (kt) 75% power @ 2000/24,000 ft.: 157/192 Cruise speed (kt) 65% power @ 2000/24,000 ft.: 150/175 Cruise speed (kt) 45% power @ 2000/24,000 ft.: 135/154 Range (w/45-min. reserve) (nm) 75% power @ 2000/24,000 ft.: 1000/1075 Range (w/45-min. reserve) (nm) 65% power @ 2000/24,000 ft.: 1200/1125 Range (w/45-min. reserve) (nm) 45% power @ 2000/24,000 ft.: 1350/1200 Fuel consumption (est. @ .44 lbs./hp/hr. sfc gph) 75% power: 17 Fuel consumption (est. @ .44 lbs./hp/hr. sfc gph) 65% power: 15 Fuel consumption (est. @ .44 lbs./hp/hr. sfc gph) 45% power: 12 Estimated endurance (65%) (hrs): 8.0 Vso (kts.): 58 Best rate of climb (fpm): 930 Best rate of climb, 8,000 ft. (fpm): 850 Service ceiling (ft.): 27,000 Takeoff ground roll (ft.): 1300 Takeoff over 50-ft. obstacle (ft.): 2160 Landing ground roll (ft.): 765 Landing over 50-ft. obstacle (ft.): 1500
CE-P210N Engine: 1 x Continental TSIO-520-AF, 310 hp. TBO: 1600 hrs. Prop: McCauley 3 blade, constant speed 80 in. Seats: 6. Length: 28.2 ft. Height: 9.6 ft. Wingspan: 36.8 ft. Wing area: 175 sq.ft. Wing aspect ratio: 7.7. Max ramp wt: 4016 lbs. Max take off wt: 4000 lbs. Standard empty wt: 2426lbs. Max useful load: 1590 lbs. Max landing wt: 3800 lbs. Wing loading: 22.9 lbs/sq.ft. Power loading: 12.9 lbs/hp. Max useable fuel: 522 lbs. Climb rate: 945 fpm @ 100 kts. Climb gradient: 567 ft/nm. Rate of climb @ 8000 ft: 860 fpm. Certificated ceiling: 23,000 ft. 8000ft cabin altitude at 17,350 ft. Max speed: 201 kts. Cruise @ 65% power @ 8,000ft: 154 kts. Cruise @ 65% pwr @ 18,000 ft: 166 kts. Fuel flow @ 65% power @ 18,000ft: 88 pph. Endurance @ 65% power @ 18,000ft: 5.7 hr. Stalling speed clean: 67 kts. Stall speed gear/flaps down: 58 kts. Turbulent air penetration speed: 130 kts. Retractable nose wheel undercarriage and pressurised.
1985 Cessna P210R Engine: Continental TSIO-520CF, 325 TBO hr: 1600 Propeller type: CS Landing Gear type: Tri./Retr. Gross weight (lbs.): 4100 Empty weight, std. (lbs.): 2471 Useful load, std. (lbs.): 1629 Fuel (lbs.): 115 Wingspan: 33 ft. 5 in. Overall length: 28 ft. 4 in. Height: 9 ft. 8 in. Seating capacity: 6 Cabin width (in.): 42 Cabin height (in.): 48 Baggage capacity (lbs.):200 Cruise speed (kt) 75% power: 210 Cruise speed (kt) 65% power: 196 Max range (w/ reserve) (nm) 75% power: 1045 Max range (w/ reserve) (nm) 65% power: 1137 Fuel consumption (USgph) 75% power: 18.2 Fuel consumption (USgph) 65% power: 15.8 Estimated endurance (65% power with 1-hr. reserve) (hrs): 6 hrs. Stall speed (gear, flaps down) (knots): 55 Best rate of climb (fpm): 1150 Service ceiling (ft.): 23,000 Takeoff ground roll (ft.): 1325 Landing ground roll (ft.): 840
CE-T210N Engine: 1 x Continental TSIO-520-R, 310 hp. turbo charged TBO: 1400-1500 hrs. Fuel Type:100LL Prop: McCauley 3 blade Q-Tip , constant speed 80 in. Seats: 6. Length: 28.2 ft. Height: 9.8 ft. Wingspan: 36.8 ft. Wing area: 175 sq.ft. Wingspan (ft.): 39.7, Flint wingtip tanks Wing aspect ratio: 7.7. Max ramp wt: 4016 lbs. Max take off wt: 4000 lbs. Standard empty wt: 2237 lbs. Max useful load: 1779 lbs. Payload, full std. fuel: 718lb Max landing wt: 3800 lbs. Wing loading: 22.9 lbs/sq.ft. Power loading: 12.9 lbs/hp. Usable fuel, std. (gals.): 88 main, 123 w/aux. tanks Max useable fuel: 522 lbs. Best rate of climb (SL fpm): 1035 Best rate of climb, 8,000 ft. (fpm): 840 Best climb speed: 100 kt Climb gradient: 558 ft/nm. Rate of climb @ 8000 ft: 845 fpm. Service ceiling: 27,000 ft. Max speed: 204 kts. Cruise @ 65% power @ 8,000ft: 156 kts. Cruise @ 65% pwr @ 18,000 ft: 167 kts. Cruise speed (kts.) @ 10,000 ft 75% power: 174 Cruise speed (kts.) @ 10,000 ft 65% power: 164 Cruise speed (kts.) @ 10,000 ft 55% power: 157 Fuel consumption (lb) 75% power: 94 pph Fuel flow @ 65% power @ 18,000ft: 86 pph. Fuel consumption (lb) 55% power: 73 pph Endurance @ 65% power @ 18,000ft: 5.9 hr. Max range (w/reserve, 75% power) (nm): 1235 Stalling speed clean: 67 kts. Stall speed gear/flaps down: 58 kts. Turbulent air penetration speed: 130 kts. Undercarriage: Retractable / nose wheel Wheel track (ft.): 8.8 Cabin width (in.): 43 Cabin height (in.): 48 Baggage capacity (lbs.): 200 Takeoff ground roll (ft.): 1300 Takeoff over 50-ft. obstacle (ft.): 2160 Landing ground roll (ft.): 765 Landing over 50-ft. obstacle (ft.): 1500
1978 Pressurized Centurion Engine: Continental TSIO 520 P, 310hp for takeoff, 285 maximum continuous. TBO: 1,500 hrs. Prop: three blade, constant speed, 80 in. diameter. Length: 28 ft. 2 in. Height: 9 ft. 5 in. Wingspan: 36 ft. 9 in. Wing area: 174.6 sq.ft. Wing loading: 22.9 lb/sq.ft. Power loading: 12.9 lb/hp. Seats: 6. Empty weight: 2588 lb. Useful load: 1412 lb. Payload with full fuel: 878 lb. Gross wt: 4000 lb. Useable fuel: 89 USG/534 lb. Maximum landing weight 3,800 lbs. Max ramp wt: 4,016 lbs. Maximum rate of climb 930 fpm. Certificated ceiling 23,000 ft. Maximum speed 206 kts. Max cruise, 79% power at 20,000 ft: 195kts. Econ cruise, 55% power at 20,000 ft: 158 kts. Duration at max cruise 4.7 hrs. Duration at econ cruise (leaned to peak EGT) 7.3 hrs. Stalling speed, clean, forward CG 73 kts. Stalling speed, full flaps, forward CG 58 kts. Pressurization differential 3.35 psi. 10,000 ft. cabin at 20,000 ft. Max range: 926 nm. ROC: 930 fpm. Takeoff dist 50 ft obstacle: 2,160 ft. Landing dist 50 ft obstacle: 1,500 ft.
O&N Aircraft Modifications Cessna 210 Silver Eagle Engine: Allison 250-B17F/2, 450 shp TBO hrs.: 3500 Fuel Type: Jet A, Jet A1, JP 8, limited avgas Propeller make/type: 90-inch CS three-blade full-feather reversing Landing Gear type: Tri./Retr. Max ramp weight (lbs.): 4016 Gross weight (lbs.): 4000 Max landing weight (lbs.): 3800 Empty weight (lbs.): 2470 Useful load (lbs.): 1530 Payload, full fuel (lbs.): 1545 Usable fuel (USgals.): 114 Oil capacity (qts.): 12 Wingspan: 36 ft. 11 in. Overall length: 29 ft. 6 in. Height: 9 ft. 6 in. Wing area (sq. ft.): 175 Wing loading (lbs./sq. ft.): 22.9 Power loading (lbs./hp.): 8.89 Wheel track (in.): 8 ft. 7 in. Wheel size (in.): 6.00 x 6 main; 5.00 x 5 nose Seating capacity: 6 Cabin doors: 1 Cabin width (in.): 41.75 Cabin height (in.): 57 Baggage capacity (lbs.): 181.5 Cruise speed (kts.): 215 Cruise speed (kt) @ 12,000 ft.: 200 Cruise speed (kt) @ 17,500 ft.: 215 Cruise speed (kt) @ 23,000 ft.: 208 Max range (w/ reserve) @ 12,000 ft: 570 nm Max range (w/ reserve) @ 17,500 ft.: 860 nm Max range (w/ reserve) @ 23,000 ft.: 910 nm Fuel consumption (USgph): @ 12,000 ft.: 24.0 Fuel consumption (USgph): @ 17,500 ft.: 22.7 Fuel consumption (USgph): @ 23,000 ft.: 19.5 Estimated endurance (standard fuel)(hrs): 5.0 Stall speed (flaps up) (knots): 76 Stall speed (flaps down) (knots): 61 Best rate of climb (SL fpm): 2200 Service ceiling (ft.): 23,000 Takeoff ground roll (ft.): 600 Takeoff over 50 ft. obstacle (ft.): 900 Landing ground roll (ft.): 500 Landing over 50 ft obstacle (ft.): 1000
On 3 January 1969 Cessna flew the first production example of the lengthened seven-seat Model 207, which reverted to the name Skywagon. This introduced a second access door on the starboard side; a 54kg capacity baggage compartment, forward of the cabin; and the more powerful IO-520-J engine. The 206 and 207 use the same airframe, except that the 207 Skywagon is 3 feet 6.75 inches longer. This extra length is inserted just ahead of the double cargo doors, which adds cubic feet to the cabin, and an extra window on each side, making this a seven-place airplane.
Later the type became known as the Stationair 7 and then the Stationair 8.
CE-207
Both the Models 206 and 207 can be flown with cargo doors removed for the air-dropping of supplies, parachuting and photography. Both can carry a 136kg glassfibre cargo pack beneath the fuselage, and ambulance kits comprising a stretcher, oxygen supply, and attendant seat are available. The Model 207 also serves with several armed services.
Replaced by the Model 208 Caravan, volume production of the 206 and 207 ended in 1985, although around 100 more airframes were produced and sold. By 31 December 1987, no less than 7,652 Model 206 Skywagon and Stationairs had been delivered, including 643 Super Skylane luxury versions.
The Model 206 Super Skylane was, in effect, a fixed-gear version of the 210D Centurion, and this craft was built through 1971. The original six-seat Cessna Model 206, introduced in 1964, was designated the Super Skywagon as it was an improved version of the Cessna 185. The Stationair replaced the U206 Skywagon in 1971 (as Cessna considered the 206 a utility aircraft, the prefix U was added), combining the U206 airframe with a 300-hp Continental I0-520-F engine. The U206 had a double door on the right side of the fuselage and a single on the left by the pilots seat. It also had a Continental IO-520 of 285 hp and a redesigned wing with wide span flaps and wide chord ailerons. The 205A was also built in 1964 but changed to a P206 in 1965, also getting the 520 engine at that time. The U206 accounted for 90% of sale. The P206 was called a Super Skylane and the U206 a Super Skywagon. The Super Skywagon changed to Stationair when, after 1970, only the U206 version was built. Cessna released a number of models of the 206, which differed only slightly and included the Turbo Stationairs. Both U206 and P206 became available with turbochargers in 1966, the U206 becoming the TU206, and in that year the U206 MTOW increased to 3600 lb and the horsepower to 300 for take-off. Optional fuel was 80 USG. In 1968 came an enlarged horizontal tail and cantilever wing. The U206 got a camber lift wing (drooped leading edge) in 1973. The TU206 remained 285 hp until 1977, with a new IO-520 rated at 310 hp for take-off and 285 continuous, and a wet wing replaced the bladder fuel system in 1979. The replacement of the 260 hp Continental by a 285 hp engine resulted in the model 205 changing to the model 206. Sales remained steady so that 1700 had been built by 1971. Cessna offered operators the choice of the tricycle undercarriage Super Skywagon with omnivision or the taildragger model 185 Skywagon. These early model 206s can be identified by the third door on one side for the rear seat passengers. A new name was allocated to the Stationair from 1978, the Stationair 6. Cessna’s Model 185 had the civil name Skywagon and when an improved version was evolved this was designated Cessna Model 206 Super Skywagon. Changes included replacement of the tailwheel landing gear with one of tricycle type; introduction of conical-camber wingtips to reduce induced drag; enlargement of the tailplane and flaps; addition of double cargo doors measuring 1.22 by 0.91m; and a more powerful 213kW Continental IO-520-A flat-six engine.
Cessna U206 F
The Super Skylane series is the P-206 Model, because the U-206 Model, produced 1964-1971 inclusive, is called the Skywagon 206. In fact, it was called the Super Skywagon until 1969, but the Model 207 Skywagon was introduced that year, and Cessna dropped the “Super.” Cessna eventually simplified this by dropping the Super Skylanes and 206 Skywagons (plural because both were offered with turbocharging) in 1972, replacing them with the Stationair, which continued in production, along with the 207 Skywagon. The 206 and 207 use the same airframe, except that the 207 Skywagon is 3 feet 6¾ inches longer.
A redesign in 1972 gave the U206, now marketed as the Stationair, double loading doors to enable bulky items to be loaded with ease. Between 1972 and 1976 1820 “206F” models were built. Factory prices for 1976 Stationairs begin at $41,850, and range up to $58,200 for the Turbo Stationair II with complete avionics.
Production figures climbed dramatically so that more than 5000 had been built by 1984. The 1981 TU206 sold for US$78,400 standard. Replaced by the Model 208 Caravan, volume production of the 206 and 207 ended in 1985, although around 100 more airframes were produced and sold. By 31 December 1987, no less than 7,652 Model 206 Skywagon and Stationairs had been delivered, including 643 Super Skylane luxury versions.
August 1996 marked the first flight of new Turbo 206 Stationair prototype. The Stationair Model U206H is offered in two versions: the normal aspirated 206H and a turbo T206H. The turbo 206 actually flew before the standard model on 6 August 1996, while the 206H flew on 6 November 1996 with the Lycoming 580 engine fitted. Cessna switched to the 540 because of reliability concerns and production was pushed back by about 10 months, but the 206H was certified two years later on 9 September 1998 and the T206H followed on 1 October 1998. The all-metal Stationair 206H is equipped with a tricycle landing gear and the main undercarriage is the proven leaf spring system and the 206H has options for large tires and spats and there is a floatplane option. The NZ 1999 fly-away price of the IFR equipped 206H is NZ$625,000.
CE-206 Super Skywagon Engine: 260 hp Continental IO-470-S Wingspan: 36 ft 7 in Length: 27 ft 4 in Height: 9 ft 9 in Wing area: 175.5 sq.ft Empty weight: 1730 lb Loaded weight: 3300 lb Max speed: 173 mph at SL Cruise 75%: 162 mph at 6500 ft ROC: 965 fpm Service ceiling: 16,100 ft Max range: 1275 mi
CE-206 Super Skywagon Engine: 260 hp Continental IO-520-A Wingspan: 36 ft 7 in Length: 27 ft 9 in Height: 9 ft 9 in Wing area: 175.5 sq.ft Empty weight: 1780 lb Loaded weight: 3300 lb Max speed: 177 mph at SL Cruise 75%: 166 mph at 6000 ft ROC: 1075 fpm Service ceiling: 16, 700 ft Max range: 1075 mi
CE-P206 Skylane Engine: 300 hp. Wing span: 35 ft 10 in. Length: 28 ft 3 in. Height: 9 ft 7.5 in. Empty wt: 1835 lbs. Gross wt: 3600 lbs. Useful load: 1765 lbs. Wing loading: 20.7 lbs/sq.ft. Pwr loading: 12 lb/hp. Max speed: 152 kts / 174 mph. Cruise speed: 142 kts / 163 mph. Stall speed: 53 kts / 61 mph. Initial ROC: 920 fpm. Service ceiling: 14,800 ft. Range (63 USG): 650 sm.
CE-U206G Stationair 6 Engine: 1 x Lycoming IO-520-F, 300 hp. TBO: 1700 hrs. Prop: McCauley 3 blade, constant speed 80 in. Seats: 6. Length: 28 ft. Height: 9.6 ft. Wingspan: 35.8 ft. Wing area: 174 sq.ft. Wing aspect ratio: 7.4. Max ramp wt: 3612 lbs. Max take off wt: 3600 lbs. Standard empty wt: 1942 lbs. Max useful load: 1670 lbs. Max landing wt: 3600 lbs. Wing loading: 20.7 lbs/sq.ft. Power loading: 12 lbs/hp. Max useable fuel: 528 lbs. Climb rate: 920 fpm @ 84 kts. Climb gradient: 644 ft/nm. Rate of climb @ 8000 ft: 470 fpm. Service ceiling; 14,800 ft. Max speed: 156 kts. Cruise @ 65% power @ 8,000ft: 140 kts. Fuel flow @ 65% power @ 8,000ft: 82 pph. Endurance @ 65% power @ 8,000ft: 6.2 hr. Stalling speed clean: 62 kts. Stall speed flaps down: 54 kts. Turbulent air penetration speed: 120 kts. Fixed undercarriage. First built in 1963
CE-206H Stationair Engine: Textron Lycoming I0-540-ACIA5, 300-bhp (at 2,700 rpm). Prop: 3-blade, cs, 2.01-m dia McCauley. Fuel cap: 348 litres (333 litres usable). Useful load: 1,404 lbs. MAUW: 1,633 kgs (3,600lbs). TO Dist: 910 ft (1,395 ft to 50-ft). ROC: 900 fpm. Cruise 6,200 ft: 142 kts (75 % pwr). Range std res: 605 nm. Stall: 62-54 kts.
CE-TU206G Turbo Stationair 6 Engine: 1 x Continental TSIO-520-M, 310 hp 285 hp continuous. TBO: 1400-1700 hrs. Prop: McCauley 3 blade, constant speed 80 in. Seats: 6. Length: 28.25 ft. Height: 9.33 ft. Wingspan: 35.8 ft. Wing area: 174 sq.ft. Wing aspect ratio: 7.4. Max ramp wt: 3616 lbs. Max take off wt: 3600 lbs. Standard empty wt: 2021 lbs. Max useful load: 1595 lbs. Max landing wt: 3600 lbs. Wing loading: 20.7 lbs/sq.ft. Power loading: 11.6 lbs/hp. Max useable fuel: 528 lbs / 88 USG. Climb rate SL: 1010 fpm @ 88 kts. Climb gradient: 687 ft/nm. Rate of climb @ 8000 ft: 910 fpm. Service ceiling; 27,000 ft. Max speed: 174 kts at 17,000 ft. Cruise @ 65% power @ 8,000ft: 1136 kts. Cruise @ 65% pwr @ 18,000 ft: 148 kts. Fuel flow @ 65% power @ 18,000ft: 86 pph. Endurance @ 65% power @ 18,000ft: 5.66 hr. Stalling speed clean: 62 kts. Stall speed flaps down: 54 kts. Turbulent air penetration speed: 120 kts. Fixed undercarriage. First built in 1966.
1996 Cessna 206 Stationair Engine: Textron Lycoming IO 540, 296 hp Length: 28.248 ft / 8.61 m Height: 9.285 ft / 2.83 m Wingspan: 35.991 ft / 10.97 m Wing area: 173.839 sq.ft / 16.15 sq.m Max take off weight: 3618.4 lb / 1641.0 kg Weight empty: 2273.4 lb / 1031.0 kg Max. speed: 178 kt / 330 km/h Cruising speed: 164 kt / 304 km/h Initial climb rate: 1049.21 ft/min / 5.33 m/s Service ceiling: 27001 ft / 8230 m Cruising altitude: 20013 ft / 6100 m Wing load: 20.91 lb/sq.ft / 102.0 kg/sq.m Range: 813 nm / 1506 km Endurance: 6 h Crew: 1 Payload: 5 pax (max. 609kg)
1999 Cessna 206 Stationair Engine: Lycoming IO-540-AC1A, 300 hp TBO hrs.: 2000 Propeller: Const. spd. Landing gear type: Tri/Fixed Gross weight (lbs.): 3600 Empty weight, std. (lbs.): 2146 Useful load, std. (lbs.): 1404 Fuel (USgals.): 88 Wingspan: 35 ft. Overall length: 28 ft. 3 in. Height: 9 ft. 4 in. Wing area (sq. ft.):174 Seating capacity: 6 Cabin width (in.): 44 Cabin height (in.): 49 Baggage capacity (lbs.): 180 Cruise speed (kts.) 75% power: 142 Cruise speed (kts.) 65% power: 134 Max range (w/ reserve) (nm) 75% power: 600 Max range (w/ reserve) (nm) 65% power: 660 Fuel consumption (USgph) 75% power: 16.5 Fuel consumption (USgph) 65% power: 14.3 Estimated endurance (65% power with 1-hr. reserve): 5 hrs. Stall speed (gear, flaps down) (knots):54 Best rate of climb (fpm): 988 Service ceiling (ft.): 15,700 Takeoff ground roll (ft.): 910 Landing ground roll (ft.): 735
2001 Cessna Turbo Stationair Base price: US$364,900 Engine: Lycoming TIO-540-AJ1A, 310 hp@2700@SL TBO hrs.: 2000 Fuel Type:100/100LL Propeller type: McCauley CS Landing Gear type: Tri/Fixed Max ramp weight (lbs.): 3616 Gross weight (lbs.): 3600 Empty weight, std. (lbs.): 2279 Useful load, std. (lbs.): 1324 Oil capacity (qts.): 11 Wingspan: 35 ft. Overall length: 28 ft. 3 in. Height: 9 ft. 4 in. Wing area (sq. ft.):174 Wing loading (lbs./sq. ft.): 20.7 Power loading (lbs./hp.): 11.6 Wheel track (in.): 8 ft. 1 in. Wheel size (in.): 8.00 x 6 Seating capacity: 6 Cabin doors: 2-3 Cabin width (in.): 44 Cabin height (in.): 49 Cabin length (in.): 144 Baggage capacity (lbs.):180 Cruise speed (kt) 75% power @ 20,000 ft.: 164 Cruise speed (kt) 75% power @ 10,000 ft.: 150 Cruise speed (kt) 65% power @ 20,000 ft.: 152 Cruise speed (kt) 65% power @ 10,000 ft.: 141 Max range (w/ reserve) (nm) 75% power @ 20,000 ft.: 568 Max range (w/ reserve) (nm) 75% power @ 10,000 ft.: 541 Fuel consumption (USgph) 75% power: 19.1 Fuel consumption (USgph) 65% power: 16.7 Fuel consumption (USgph) 55% power: 14.0 Estimated endurance (65%) (hrs): 4.0 Stall speed (flaps up) (knots): 62 Stall speed (flaps down) (knots): 54 Best rate of climb (fpm): 1050 Service ceiling (ft.): 27,000 Takeoff ground roll (ft.): 910 Takeoff over 50 ft. obstacle (ft.):1740 Landing ground roll (ft.): 735 Landing over 50 ft. obstacle (ft.): 1395
2003 Cessna Turbo Stationair Engine: Lycoming TIO-540-AJ1A, 310 hp@2500@SL TBO hrs.: 2000 Propeller type/diameter: McCauley CS/79 in Landing gear type: Tri./Fixed Max ramp weight (lbs.): 3617 Gross weight (lbs.): 3600 Empty weight, std. (lbs.): 2933 Useful load, std. (lbs.): 1324 Payload, full std. fuel (lbs.): 802 Usable fuel (USgals.): 87 Oil capacity (qts.): 11 Wingspan: 36 ft. Overall length: 28 ft. 3 in. Height: 9 ft. 4 in. Wing area (sq. ft.): 174 Wing loading (lbs./sq. ft.): 20.7 Power loading (lbs./hp): 11.6 Wheel track: 8 ft. 1 in. Wheel size (in.): 8.00 x 6 Seating capacity: 6 Cabin doors: 2-3 Cabin width (in.): 44 Cabin height (in.): 49 Cabin length (in.): 144 Baggage capacity (lbs./cu. ft.): 180 Cruise speed (kt) 75% power @ 10,000/20,000 ft.: 150/163 Cruise speed (kt) 65% power @ 10,000/20,000 ft.: 141/152 Max range (w/ reserve) (nm) 75% power @ 10,000/20,000 ft.: 541/568 Max range (w/ reserve) (nm) 55% power @ 10,000/20,000 ft.: 692/713 Fuel consumption (USgph) 75% power:19.1 Fuel consumption (USgph) 65% power: 16.7 Fuel consumption (USgph) 45% power: 14 Estimated endurance (65%) (hrs): 4.2* Vs (kts.): 62 Single-engine rate of climb (fpm): 54 Best rate of climb (SL fpm): 1050 Service ceiling (ft.): 27,000 Takeoff ground roll (ft.): 910 Takeoff over 50-ft. obstacle (ft.): 1740 Landing ground roll (ft.): 735 Landing over 50-ft. obstacle (ft.): 1395
2005 Cessna Turbo Stationair Engine: Lycoming TIO-540-AJ1A, 310 hp@2500@SL TBO hrs.: 2000 Fuel type:100/100LL Propeller type/diameter: McCauley CS/79 Landing gear type: Tri./Fixed Max ramp weight (lbs.):3617 Gross weight (lbs.): 3600 Empty weight, std. (lbs.): 2279 Useful load, std. (lbs.): 1321 Payload, full std. fuel (lbs.): 793 Usable fuel, std. (gals.): 88 Oil capacity (qts.):11 Wingspan: 36 ft. Overall length: 24 ft. 3 in. Height: 9 ft. 4 in. Wing area (sq. ft.):174 Wing loading (lbs./sq. ft.): 20.7 Power loading (lbs./hp.): 11.6 Wheel track: 8 ft. 1 in. Wheel size (in.): 6.00 x 6 Seating capacity: 6 Cabin doors: 2-3 Cabin width (in.): 44 Cabin height (in.): 50 Baggage capacity (lbs.):180 Cruise speed (kt) 75% power @ 10,000/20,000 ft.: 150/164 Cruise speed (kt) 65% power @ 10,000/20,000 ft.: 141/152 Max range (w/ reserve) (nm) 75% power @ 10,000/20,000 ft.: 541/568 Fuel consumption (USgph) 75% power:19.1 Fuel consumption (USgph) 65% power: 16.7 Fuel consumption (USgph) 55% power: 14.0 Estimated endurance (65%) (hrs): 4.0 Vs (kts.): 62 Vso (kts):54 Best rate of climb (fpm): 1050 Service ceiling (ft.): 27,000 Takeoff ground roll (ft.): 910 Takeoff over 50-ft. obstacle (ft.): 1740 Landing ground roll (ft.): 735 Landing over 50-ft. obstacle (ft.): 1395
2007 Cessna T206H Stationair Engine:Lycoming TIO-540-AJ1A, 310 hp@SL TBO hrs.: 2000 Fuel Type:100/100LL Propeller type: CS/3-blade McCauley Landing Gear type: Tri./Fixed Max ramp weight (lbs.):3617 Gross weight (lbs.): 3600 Landing weight (lbs.): 3600 Empty weight, std. (lbs.): 2362 Useful load, std. (lbs.): 1255 Useful fuel, std. (USgals.): 87 Payload, full std. fuel (lbs.): 733 Wingspan: 36 ft. Overall length: 28 ft. 3 in. Height: 9 ft. 4 in. Wing area (sq. ft.):174 Wing loading (lbs./sq. ft.): 25.5 Power loading (lbs./hp.): 12 Seating capacity: 6 Cabin doors: 2/3 Cabin width (in.): 44 Cabin height (in.): 49 Cruise speed @ 10,000 ft.(kt) 75% power: 150 Cruise speed @ 10,000 ft.(kt) 65% power: 141 Cruise speed @ 10,000 ft.(kt) 55% power: 129 Cruise speed @ 20,000 ft.(kt) 75% power: 164 Cruise speed @ 20,000 ft.(kt) 65% power:152 Cruise speed @ 20,000 ft.(kt) 5% power:136 Max range (nm) 75% power: 570 Max range (nm) 65% power: 620 Max range (nm) 55% power: 670 Fuel consumption (USgph) 75% power: 19.1 Fuel consumption (USgph) 65% power: 16.7 Fuel consumption (USgph) 55% power: 14.4 Vso (kts.): 54 Best rate of climb (SL fpm): 1050 Service ceiling (ft.): 27,000 Takeoff ground roll (ft.): 910 Takeoff over 50-ft. obstacle (ft.): 1740 Landing ground roll (ft.): 735 Landing over 50-ft. obstacle (ft.): 1385
2009 CESSNA TURBO STATIONAIR T206 Engine: Lycoming TIO-540-AJ1A, 310 hp@SL to 20,000 feet TBO (hrs.): 2000 Fuel type: 100LL Propeller type: CS/3-blade Landing gear type: Tri./Fixed Gross weight (lbs.): 3600 Empty weight, std. (lbs.): 2349 Useful load, std. (lbs.): 1268 Usable fuel, std. (gals./lbs.): 87/522 Payload, full std. fuel (lbs.): 746 Wingspan (ft.): 36 Overall length: 28 ft. 3 in. Overall height: 9 ft. 3 in. Wing area (sq. ft.): 175.6 Wing loading (lbs./sq. ft.): 20.5 Power loading (lbs./hp): 11.6 Seating capacity: 6 Cabin doors: 3 Cabin width (in.): 42.5 Cabin height (in.): 49.5 Cruise speed, 75% power (kts.): 164@20,000 feet Range, 75% power (nm): 630 Best rate of climb, SL (fpm): 1051 Service ceiling (ft.): 27,000 Vso (kts.): 54 Takeoff ground roll (ft.): 910 Takeoff over 50 ft. obstacle (ft.): 1740 Landing ground roll (ft.): 735 Landing over 50 ft. obstacle (ft.): 1395
The Cessna Model 205, introduced in 1962 and dubbed a 1963 model, was developed from the Model 182, although in appearance it was a fixed landing gear version of the Cessna 210 with omnivision windows. Without retracting undercarriage taking up cabin space the 205 was a full 6 seater. The cabin had doors on each side of the fuselage and a smaller door for access to the rear row of seats. FAA certification on 14 June 1962 was under the designation Model 210-5. Powered by a 194kW Continental engine, the Model 205 was complementary to the tailwheel Model 185 Skywagon, having similar performance at slightly greater weight.
Deliveries began in August 1962, and in December 1963 Cessna introduced the Model 205A with detail improvements. Cessna 205A (officially listed as a 210 5A) of 1964 vintage were the last of 577 Cessna 205s built. The Model 205/205A series could be flown with floats, skis or various sizes of wheels.
Model 205A Engine: 1 x Continental IO-470-S, 260 hp / 194kW Take-off weight: 1497 kg / 3300 lb Empty weight: 794 kg / 1750 lb Wingspan: 11.15 m / 36 ft 7 in Length: 8.46 m / 27 ft 9 in Height: 2.97 m / 9 ft 9 in Wing area: 16.3 sq.m / 175.45 sq ft Max. speed: 278 km/h / 173 mph Cruise speed: 261 km/h / 162 mph Ceiling: 4905 m / 16100 ft Range: 1633 km / 1015 miles
The T 50 lived on long past its time in the form of Cessna’s very first postwar project, the Model 190. The prototype 190 was essentially a pre-war Cessna Airmaster airframe with metal wings and tail and leftover T 50 engine, prop and cowling. After a brief pause to rush out the two seat 120/140, Cessna returned to the 190 project. They decided to go all metal on the fuselage as well as the wings and tail, re-placed the T 50 engine with a 300 hp Jacobs under a distinctive tight fitting, dimpled cowl and produced the last of the classics the Cessna 190, their very first all metal airplane. Unique amongst postwar Cessna single-engined light-planes in being powered by radial engines.
CE-195
Sharing the same airframe as the CE-190, the 195 offered a choice of three Jacob radial engines, including the 179kW Continental R-670-23. The two types were produced in parallel between 1947 and 1954. The 190 series came from the factory with 4 different engines: the Jacobs R 755-A2 at 300 hp (223.71 KW) the Jacobs R755-B2 at 275 hp the Jacobs R755-9 at 245 hp the 240 hp Continental W670-23.
Model 195 prototype
If it was factory fitted with a Jacobs the data plate said it was a 195 (with appropriate dash number) and if it started life with a Continental it was called a 190. The Continental was really the old 220 hp (164.05 kw) rated 240 hp for 2 minutes for takeoff. The TC data sheets in effect say that all SN airframes are elegible for all these engines. There have been modifications, some STC’s and some “one time STC’s” and possibly 337’s to put the Continental IO 470 flat 6 cylinder in the airframe as well as the L6 Jacobs rated at 330 hp. Also some have been fitted with the R985 P&W at 450 hp. Built 1947 to 1954, a total of 204 model 190 were built. Production Models of the 195 built in 1953 and 1954 195A were identifiable by their close-cowled engines, a small propeller spinner, and an increase of 50% in the area of the flaps let into the undersurfaces of the high-set unbraced wings. The series is also notable for the fact that it introduced Cessna’s now-celebrated spring-steel main landing gear legs. There were 6 versions of the 195: 195 (300hp Jacobs R755-A2 engine) 195A (240hp R755-L4) 195B (275hp R755-B2) LC-126A (US Air Force version – 15 built) LC-126B (US Army National Guard – 5 built) LC-126C (US Army – 63 built).
All 83 LCs were equipped with the 300hp Jacobs R755-A2 engines. The differences between the three LC variants were mostly minor: i.e. different radios & instruments. However, the LC-126C version included a double-width baggage door for use in loading/unloading stretcher (litter) patients when used in an airborne ambulance role. The U.S.A.F. has acquired a number of these aircraft for Arctic rescue duties, with interchangeable wheel, float and ski undercarriage.
890 CE-195s were produced 1947-1957, plus 83 delivered to the military as U-20, LC-126, LC-126B and LC-126Cs.
LC-126A
The 195 has an important AD Note calling for rebuild of the center spar.
195 Engine: Jacobs R755-A2, 300hp / 183kW TBO (hrs.): 1200 Fuel type: 80 octane (minimum) Propeller type: Ham Std. CS/2-blade Wing span: 36 ft 2 in. / 11.02 m Length: 27 ft 4 in. / 8.33 m Height: 7 ft 2 in. / 2.18 m Wing area: 20.26 sq.m / 218.08 sq ft Wing loading: 15.36 lbs/sq.ft. Empty weight, std. (lbs.): 2030 Useful load, std. (lbs.): 1320 Gross wt: 3350 lbs. / 1520 kg Landing weight (lbs.): 3350 Max ramp weight (lbs.): 3350 Useful load: 1250 lbs. Usable fuel (USgals.): 82 Payload, full std. fuel (lbs.): 828 Pwr loading: 11.16 lbs/hp. Baggage cap: 220 lbs. Max speed: 161 kts / 185 mph. Cruise speed 75% power: 143 kt Fuel consumption 75% power: 14.3 USgph Stall: 54 kts / 62 mph. Best rate of climb (SL fpm): 1210 Service ceiling: 18,300 ft. Range (75 USG): 800 sm. Takeoff over 50 ft. obstacle (ft.):1500 Landing over 50 ft. obstacle (ft.): 1495 Wheel size (in.): 6.5 x 10 Seating capacity: 5 Cabin doors: 1 Cabin width (in.): 46 Cabin height (in.): 48 Landing gear type: Conv./Fixed
195A Engine: 240hp R755-L4
195A Engine: 245hp Jacobs R-744-A2 Wingspan: 36 ft 2 in Wing area: 218.125 sq.ft Length: 27 ft 4 in Height: 7 ft 2 in Empty weight: 2030 lb Loaded weight: 3350 lb Max speed: 173 mph Cruise: 155 mph ROC: 1050 fpm Service ceiling: 16,000 ft Range: 750 mi
1952 CE-195B Businessliner Engine: Jacobs R-755-B2, 275 hp. TBO hr: 1200 Fuel type: 100LL Propeller type: Ham Std 2B20 Landing gear type: Fixed/Conv. Max ramp weight (lbs.): 3350 Gross weight (lbs.): 3350 Landing weight (lbs.): 3350 Empty weight, std. (lbs.): 2050 Useful load (lbs.): 1300 Payload, full std. fuel (lbs.): 845 Usable fuel, std. (USgals.): 80 Wingspan: 36 ft. 2 in. Overall length: 27 ft. 3 in. Height: 7 ft. 2 in. Wing area (sq. ft.): 218 Wing loading (lbs./sq. ft.): 15.4 Power loading (lbs./hp.): 11.1 Seating capacity: 5 Cabin doors: 2 Baggage capacity (lbs.): 220 Cruise speed 75% power, 7,000 ft: 143 kts Max Range (w/reserve): 583 nm Fuel consumption: 13 to 15 USgph Estimated endurance, 65%: 6 hrs Vso: 54 kts Best rate of climb: 1135 fpm Best rate of climb, 8,000 ft: 550 fpm Service ceiling: 16,250 ft Takeoff over 50-ft. obstacle: 1605 ft Landing over 50-ft. obstacle: 1495 ft
LC-126A Engine: Jacobs R-755-A2, 300 hp. Span: 36 ft. 2 in Weight: 3,350 lb Max. Speed: 180 m.p.h. Seats: 4-5 Range: over 750 miles at 165 m.p.h. 15 built
LC-126B Engine: Jacobs R-755-A2, 300 hp Span: 36 ft. 2 in. Length: 27 ft. 4 in. Height: 8 ft. 4 in. Weight: 3,350 lbs. loaded Armament: None Crew: One Passengers: Four 5 built
First flown on 19 February 1965, the Agwagon was Cessna’s first production low-wing single. Utilising as many model 180 parts as possible, the Agwagon was sensibly priced and proved a good seller. The Cessna Model 188 AGwagon (later renamed AG Wagon) is a braced low-wing monoplane of all-metal construction, with non-retractable tailwheel landing gear, and accommodation for the pilot in an enclosed cabin protected by a steel overturn structure.
AGwagon
Power was provided by either a 172kW Continental IO-470-R or a 224kW Continental IO-520-D engine for the AGwagon 230 or AGwagon 300 respectively. Standard agricultural equipment included a 757-litre or 816kg capacity glassfibre hopper between the engine firewall and the cabin, and optional dusting or spraying equipment was available.
An increasing market for the AGwagon resulted in the introduction of a new model of this aircraft in late 1971; plus two additional versions designated as the AGpickup and AGtruck. The AGpickup was the basic model, a new name applied to the Continental O-470-R version of the original AGwagon; the Continental IO-520-D AGwagon was renamed AGwagon C and introduced a number of detail refinements; and the AGtruck was generally similar to the AGwagon C, except for the provision of a 1060-litre hopper plus a complete spray system and a wide range of equipment as standard. Of these three types the AGpickup was discontinued in 1976, and production of the AGwagon ended during 1981, after 1,589 had been built.
The final production version, introduced in 1979, was the T188C AG-HUSKY was powered by a turbocharged 310 hp / 231kW TSIO-520-T engine. US conversions to 400 hp are known of. Three hundred and eighty-five Cessna T188C AgHuskys, variants of the popular Cessna Agwagon and AgTruck agricultural aircraft, were built until late in 1985 when production ended. In total, 3976 CE-188 were built
A two seat conversion was performed on three Cessna Al88 Agwagons for Hazelton Air Services of Cudal, NSW. Aerosmith converted VH DOD (s/n AI 88 0125) at Sydney in 1967. Major work included widening the rear fuselage and installing a raised turtledeck. The cockpit sides are near vertical and a much larger windscreen fitted. The flying controls were shifted to the port side, but dual controls were not fitted. When a second aircraft was required, Aerosmith converted and certified another aircraft on 18 January 1971. The aircraft, VH KVA (s/n A188 0169), was registered as a Cessna A.188A/2 on 07 May 1971. A third aircraft (s/n A188 0066) was also converted and registered in February 1972. This aircraft was damaged beyond repair in January 1984 and first conversion, VH-DOD, was written off in 1986.
Aviones de Colombia Sa, originally a Cessna dealership (1961), then also assembled selected Cessna aircraft, produced a two-seat training derivative of the Cessna AgTruck, known as AgTrainer.
CE-A188 AgPickup Engine: Continental O-470-R, 230 hp Length: 26 ft (8 m) Wingspan: 41 ft 8 in (12.7 m) Maximum speed: 121 mph (195 kph) Range: 370 miles (595 km) Service Ceiling: 11,000 ft (3,383 m)
CE-A188A Agtruck
AGwagon Engines: Continental IO-520-D, 300 hp. Seats: 1. Wing loading: 16.3 lb/sq.ft. Pwr loading: 13.3 lb/hp. Max TO wt: 4000 lb. Empty wt: 2189 lb. Equipped useful load: 1759 lb. Payload max fuel: 1447 lb. Range max fuel 75% pwr: 253 nm / 2.6 hr. Service ceiling: 11,100 ft. Hopper cap: 200 USG. 75% cruise: 99 kt. Working speed: 105 kt. Working endurance: 3.1 hr. Stall: 50-53 kt. ROC: 690 fpm. Min field length: 1265 ft. Fuel cap: 312 lb.
CE-A188A Agwagon B
CE-A188B Agwagon C Engine: Continental IO 520 D, 300 hp. Cruise speed: 113 mph. Std empty wt: 2,164 lbs. Max wt Restricted Category: 4,000 lb. Hopper cap: 200 USG. Range 75% pwr: 295 sm. Takeoff dist 50 ft obstacle: 1,090 ft. Landing dist 50 ft obstacle: 1,265 ft.
CE-A188B AGtruck First built: 1972. Engine: 1 x Continental IO-520-D, 300 hp, 224kW. TBO: 1200 hrs. Prop: McCauley 2 blade, constant speed 86 in. Seats: 1. Length: 7.9 m / 25 ft 11 in Height: 2.49 m / 8 ft 2 in Wingspan: 12.7 m / 41 ft 8 in. Wing area: 19.05 sq.m / 205.05 sq ft Wing aspect ratio: 8.47. Max ramp wt: 4200 lbs. Max take off wt: 4200 lbs. Standard empty wt: 1012 kg / 2231 lb Max useful load: 1901 lbs. Max landing wt: 3300 lbs. Wing loading: 20.5 lbs/sq.ft. Power loading: 14 lbs/hp. Max useable fuel: 324 lbs. Hopper capacity: 280 USG. Climb rate: 465 fpm. Service ceiling; 7,800 ft. Max speed: 122 kts. Working speed: 100 kts. Cruise speed: 187 km/h / 116 mph Fuel flow @ working speed: 82 pph. Endurance @ working speed: 3.7 hr. Stalling speed clean: 66 kts. Stall speed flaps down: 56 kts. Ceiling: 2375 m / 7800 ft Range: 466 km / 290 miles Turbulent air penetration speed: 98 kts. Fixed tail-wheel undercarriage.
CE-T188C AGhusky First built: 1978. Engine: 1 x Continental TSIO-520-T, 310 hp. Prop: McCauley 3 blade, constant speed 80 in. Seats: 1. Length: 26.69 ft. Height: 8.2 ft. Wingspan: 41.7 ft. Wing area: 205 sq.ft. Wing aspect ratio: 8.2. Max ramp wt: 4400 lbs. Max take off wt: 4400 lbs. Standard empty wt: 2322 lbs. Max useful load: 2078 lbs. Max landing wt: 3300 lbs. Wing loading: 21.5 lbs/sq.ft. Power loading: 14.2 lbs/hp. Max useable fuel: 324 lbs. Hopper capacity: 280 USG. Climb rate: 510 fpm. Rate of climb @ 8000 ft: 255 fpm. Certificated ceiling: 14,000 ft. Max speed: 113 kts. Working speed: 100 kts. Fuel flow @ working speed: 93 pph. Endurance @ working speed: 3.2 hr. Stalling speed clean: 62 kts. Stall speed flaps down: 58 kts. Turbulent air penetration speed: 98 kts. Fixed tail-wheel undercarriage.
In July 1960 Cessna flew the prototype of the Model 185 Skywagon. This was in most respects similar to the Model 180 apart from the provision of extra power in the form of a 224kW / 260 hp injected version of the Continental IO-520 engine.
Normal gross weight for the 185 is 3,000 to 3,300 pounds, depending on the model. The rear wall of the passenger cabin was placed further back and this change to the centre of gravity made the model 185 quite different to fly when compared to the 180, particularly for those used for topdressing. Exterior dimensions are the same as the 180, but internally the 185 has additional bracing, a stronger wing, and a dorsal fin. The two Model 185 versions were to carry under the fuselage a detachable glassfibre Cargo-Pack, capable of carrying some 136kg. The 185 joined the Cessna utility fleet in 1961, and it was powered with the IO-470-F Continental of 260-hp through the 185E Model of 1966. But the 1966 185E also was offered with the Continental IO-520-D of 300-hp, and in 1967 dropped the 260-hp 185 altogether. A lot of detail changes/improvements have been made since – like raising the flap extension speed from 111 to 138 mph, bigger windows, and better cabin heating – but the 1976 185 is basically the same machine as the 1966 model. The advertised 300 hp is “take-off horsepower” the maximum continuous rating of this engine is 285 hp. The 185 factory list in 1976 was US$35,5503.
During 1962 the USAF sought a suitable light utility aircraft for supply to countries eligible for MAP aid. Cessna’s Model 185 was selected and ordered under the designation U-17, more than 450 being supplied. These comprised the U-17A with a 194kW Continental IO-470-F flat-six engine, followed by the U-17B with a 224kW Continental IO-520-D. The final U-17C production version had a Continental O-470-L engine which had a carburettor instead of fuel injection. In 1966 the Al85E was introduced featuring an optional 300 hp IO-520 Continental, and in 1967 the 260 hp option was dropped.
Cessna A185F Skywagon
In 1971 Cessna introduced the Model 185 AGcarryall. This was designed principally for an agricultural role, for spraying procedures, ferry people and equipment. It failed to attract sufficient sales and production ended in 1979 after 108 had been built. By February 1980, 4,000 Model 185 variants had been delivered and when production ceased, in mid-1985 4,356 Skywagons had been built, including 497 U-17A/B/C military versions.
Twenty-five Skywagons were delivered to the South African Air Force.
CE-185C Engine: Continental IO-470-F, 260 hp Max speed: 176 mph at SL Cruise 75%: 168 mph at 6000 ft ROC: 1000 fpm Range: 700 mi Max range: 1235 mi Service ceiling: 17,300 ft Empty weight: 1560 lb Loaded weight: 3200 lb Wingspan: 36 ft 0 in Length: 26 ft 2 in Height: 7 ft 9 in Wing area: 174 sq.ft
CE-A185F Skywagon Engine: Continental IO-520-D, 300 hp. TBO: 1700 hrs. Prop: McCauley 3-blade, 80-in. Seats: 6. Length: 25.6 ft. Height: 7.8 ft. Wingspan: 35.8 ft. Wing area: 174 sq.ft. Wing aspect ratio: 7.4. Maximum ramp weight: 3362 lbs. Maximum takeoff weight: 3350 lbs. Standard empty weight: 1700 lbs. Maximum useful load: 1662 lbs. Maximum landing weight: 3350 lbs. Wing loading: 19.3 lbs/sq.ft. Power loading: 11.2 lbs/hp. Maximum usable fuel: 504 lbs. Best rate of climb: 1075 @ 90 kts. Climb gradient: 738 ft/nm. ROC @ 8000 ft: 640 fpm. Service ceiling: 17,900 ft. Maximum speed: 154 kts. Normal cruise @ 65% pwr @ 8000 ft: 138 kts. Fuel flow @ normal cruise: 82 pph. Endurance at normal cruise: 5.9 hrs: Stalling speed clean: 56 kts. Stalling speed flaps down: 49 kts. Turbulent-air penetration speed: 115 kts. Fixed tail wheel under carriage.
Engine: Continental IO 520 D, 285 hp max continuous power. TBO: 1,500 hrs. Prop: three blade, constant speed. Length: 25 ft. 7 in. Height: 7 ft. 9 in. Wingspan: 36 ft. Wing area: 173.5 sq.ft. Wing loading: 19.3 lb/sq.ft. Power loading: 11.2 lb/hp. Seats: 6. Empty weight: 1,854 lbs. Useful load: 1,496 lbs. Payload with full fuel: 1,052 lbs. Gross weight: 3,350 lbs. Usable fuel capacity: 74 USG/444 lbs. Maximum landing weight: 3,350 lbs. Maximum rate of climb: 1,010 fpm. Service ceiling: 17,150 ft. Maximum speed: 155 kts. Max cruise, 75% power (2,550 rpm) at 7,500 ft: 145 kts. Econ cruise, 55 % power at 10.000 ft: 129 kts. Duration at max cruise: 4.6 hrs. Duration at econ cruise: 6.3 hrs. Stalling speed, clean: 55 kts. Stalling speed, full flaps: 48 kts.
1970 Engine: Continental IO-520-D, 300 hp. Wing span: 35 ft 10 in. Length: 25 ft 9 in. Height: 7 ft 9 in. Empty wt: 1575 lbs. Gross wt: 3350 lbs. Useful load: 1776 lbs. Wing loading: 19.3 lbs/sq.ft. Pwr loading: 11.2 lbs/hp. Baggage cap: 400 lbs. Max speed: 155 kts / 178 mph. Cruise: 147 kts / 169 mph. Stall: 52 kts / 59 mph. Initial ROC: 1010 fpm. Service ceiling: 17,150 ft. Range (65 USG): 660 sm.
1978 Cessna 185 Skywagon Engine:Continental IO-520-D, 300 hp TBO hrs.: 1700 Landing gear type: Conv./FixedMax ramp weight (lbs.): 3350 Gross weight (lbs.): 3350 Max Landing weight (lbs.): 3350 Empty weight, std. (lbs.): 1750 Useful load, std. (lbs.): 1600 Usable fuel (USgals.): 88 Payload – full std. fuel(lbs.): 959 Wingspan: 35 ft. 10 in. Overall length: 25 ft. 8 in. Height: 7 ft. 9 in. Seating capacity: 6 Max Speed (kts): 155 Cruise speed (kts): 145 Range (nm): 645 Vs (kts.): 49 Best rate of climb (fpm): 1075 Service ceiling (ft.): 17,900 Takeoff ground roll (ft.): 825 Takeoff over 50-ft. obstacle (ft.): 1430 Landing ground roll (ft.): 610 Landing over 50-ft. obstacle (ft.): 1400
1979 Cessna Skywagon 185 Engine: Continental IO 520 D, 300 hp. Max speed: 155 kt. Max cruise speed: 145 kt. Max range: 836 nm. Max unable fuel: 84 USG. ROC: 1,010 fpm. Service ceiling: 17,150 ft. Takeoff dist 50 ft obstacle: 1,365 ft. Landing dist 50 ft obstacle: 1400ft. Max ramp wt: 3,362 lbs. Max useful load: 1,681 lbs. Seats: 6.
AGcarryall Engine: Continental IO-520-D, 300 hp. Seats: 2/6. Wing loading: 19.3 lb/sq.ft. Pwr loading: 11.2 lb/hp. Max TO wt: 3350 lb. Empty wt: 1905 lb. Equipped useful load: 1393 lb. Payload max fuel: 949 lb. Range max fuel/ 75% pwr: 481 nm/ 4 hr. Service ceiling: 13,400 ft. Hopper cap: 151 USG. 75% cruise: 122 kt. Stall: 49-57 kt. ROC: 845 fpm. Min field length: 1450 ft. Fuel cap: 330/444 lb.
1967 Cessna 185 (Robinson STOL vortex generators) Engine:Continental IO-520-D, 300 hp Max continuous hp: 285 TBO hrs.: 1700 Fuel Type: 100/100LL Propeller type: McCauley/CS Landing Gear type: Tailwheel Max ramp weight (lbs.): 3350 Gross weight (lbs.): 3350 Landing weight (lbs.): 3350 Usable fuel (USgals.): 76 Oil capacity (qts.): 12 Wingspan: 36 ft. 2 in. Overall length: 25 ft. 9 in. Height: 7 ft. 9 in. Wing area (sq. ft.): 174 Wing loading (lbs./sq. ft.): 18.9 Power loading (lbs./hp.): 11 Wheel track: 7 ft. 8 in. Wheel size (in.): 8.5 x 6 Seating capacity: 4 Cabin doors: 2 Cabin width (in.): 40.25 Cabin height (in.): 42.75 Baggage capacity (lbs.): 350 Cruise speed 75% power: 140kt Cruise speed 65% power: 128 kt Cruise speed 55% power: 122 kt Max range (w/ reserve) 75% power: 600 nm Max range (w/ reserve) 65% power: 640 nm Max range (w/ reserve) 55% power: 710 nm Fuel consumption (USgph) 75% power: 15.5 Fuel consumption (USgph) 65% power: 13.5 Fuel consumption (USgph) 55% power: 11.7 Estimated endurance (65% power with 1-hr. reserve) (hrs): 4.5 Stall speed (gear, flaps up) (knots): 44 Stall speed (gear, flaps down) (knots): 39 Best rate of climb (SL fpm): 1040 Service ceiling (ft.): 25,000 Takeoff ground roll (ft.): 487 Landing ground roll (ft.): 328
The evolution of the Skylane actually began at the 1949 Model 170A, an all-metal, 145 hp, four seat taildragger. Bigger flaps arrived in 1952 with the 170B, and one year later came that design’s first off-spring, the 180, with 225 hp. Tricycle gear was added in 1956; it was now called the 182. Introduced at the same time as the model 172, the more powerful and luxurious 182 was in the 1956 Cessna line-up. Essentially the 182, 182A and 182B produced between 1956 and 1959 was a tricycle-undercarriage version of the 180. As expected, sales of the 180 dropped off as those of the 182 picked up. An addition to the standard fixed-gear family, it was powered by a 172kW Continental O-470-S and available in Standard, Skylane and Skylane II versions. The earliest models had straight tails and no rear windows. That first Skylane retained the basic hull of the 170 and the 172. They had relatively narrow fuselages and a gross weight of 2,650 pounds. The airplane was lowered when the landing gear was widened in 1957 and again in 1962. In 1958, the Skylane version was introduced a deluxe 182 with added soundproofing and extra standard equipment. The first airplanes held only 60 USG of fuel. But the capacity was increased to 65 USG in 1958, and in 1962, the optional 84 USG (79 usable) long range tanks were first offered. In that year, the airplane was given a new four inch wider fuselage, a rear window, electric flaps and a low, flat cockpit floor. Consequently, the gross weight was raised 150 pounds. The 1960 and 1961 model 182C and 182D introduced the swept tail (1960) and third cabin window. The 1962 model 182 introduced the omnivision window arrange¬ment and elctric flaps. Apart from changes to the rear window shape, cowling, spinner, and spats, there have been few changes apart from cosmetic ones. Early 180s were equipped with a Conti¬nental O 470 A engine rated at 225 hp. There were a lot of maintenance problems, notably cracked cylinders. The engines were prone to overheating, as were the Goodyear brakes. After 1957, the engine was the 230¬hp K version, and after 1961, the R; both gave excellent service, until a Continental service bulletin called for tapping the valve guides to improve valve stem lubrication. This modification proved disastrous; guides wore out rapidly, valves bounced around, and several small bush operations went bankrupt trying to keep up with the top overhauls. Me-chanics started reverting to the original guides, and eventually, Continental decided to do so as well.
The 1962 m182E featured some fuselage re-design with 360 degree cabin visibility. The 182F and 182G were externally similar.
In 1964 the MTOW increased to 2800 lbs, and in 1970, to 2950 lbs. On the other hand, Cessna has cleaned up the fuselage to the point that cruise airspeeds on the more modern 182s are slightly better than those of their lightweight predecessors. In 1967, the size of the long range tanks was reduced to 80 USG. Tending to be a low maintenance machine, the 182 has been the target of only a few expensive airworthiness directives, one of which mandated the replacement of many nose gear forks in 1971. For ’72 the Skylane gets a radiused leading edge of the type popularized by the Robertson STOL conversions a more rounded contour with a slightly convex lower lip, and a pronounced twist tailored along the span to provide a controlled stall progression and keep the outboard section at a lower angle of attack. Originally a Robertson rework that included drooping ailerons and a stall fence, it was later offered by other modifiers without the extra cost and complexity of the aileron/flap interconnection. The drooped, large radius leading edge does a lot for the 180 and 185’s slow flying characteristics, preserving aileron effectiveness right into the stall and possibly shaving a bit off the stalling speed though apparent stall speed reductions of 10 or 20 miles an hour are the result of errors in the airspeed indicating system. The all important decrease in runway requirements results from the greater precision with which minimum speed approaches can be flown. Earlier Skylanes with the long popular spring steel slab gear legs had a maximum landing weight 150 pounds lower than allowable takeoff gross, but this year the ‘Lane gets a tapered tubular steel gear similar to that on the rest of the fixed-gear line (except the 180 and 185). This new gear has three important advantages – it is attached further back on the fuselage, and so widens the center of gravity envelope by 7½ %, it puts the main wheels nearly a foot further apart than they were on the old gear for an even more solid ground stance, and it permits landings at 2,950 lb. In 1977, a new, higher compression version of the same engine was installed. It develops the 230 horse-power at 2,400 rpm, 200 rpm less than the earlier engines, and it is rated for 100LL fuel. It has a 1,500 hour TBO. Introduced in 1978 the Skylane RG replaced the 177RG Cardinal RG in the model lineup. It was simply a model 182Q fitted with the same type of retractable gears as fitted to the R172 and 210 Centurion, and a 28v electric system. Nearly 2000 were produced. The 182 had a total production run of over 10,000 to 1993. The only addition to the Cessna single engined line of general aviation aircraft for 1981 was the Turbo Skylane, a turbo supercharged version of the basic Model 182 Skylane. The 235 hp Lycoming engine already used to power the retractable undercarriage Turbo Skylane RG was offered in the standard fixed gear Skylane to boost the performance and payload. At the same time, Cessna has announced a 150 lb (68¬ kg) increase in the gross weight of the basic Skylane model, to match the weight of the Turbo Skylane version. A number of small improvements were also adopted as standard for both models, and a three bladed propeller is an optional alternative for the two blader on the Turbo Skylane. The CE182T involves a cleaned up airframe, give a four knot cruise over the 182S model, plus the Lycoming TIO-540-AK1A turboed engine of 235 hp at 2400 rpm as an option. A small number of the turbocharged 182s were built in 1981 and 1982. Versions available in 1982 included the Model 182 Skylane/Skylane II which was available also in Turbo Skylane and Turbo Skylane II with a 175kW Avco Lycoming O-540-L3C5D turbo-charged engine, and in Skylane RG and Skylane RG II and Turbo Skylane RG and Turbo Skylane RG II retractable landing gear equivalents.
Cessna TR182 Turbo Skylane RG II
All three of the 1979 Skylanes share usable fuel ca¬pacity up to 88 USG (from a previ¬ous 75). The new tanks are formed by sealing off part of the wing. There’s a forward facing fuel vent for each tank, located behind the wing strut in what should be an ice free area. The caps are also vented. The conversion to tail wheel (CE-182TW) essentially makes the 182 into a 180.
In July 1996 Cessna flew the first Model 182 Skylane produced in more than 10 years.
Cessna’s diesel 182 JT-A, still in its certification process, was forced to make an emergency landing in a field due to an engine failure late August 2013. The pilot flying at the time reported that the “engine blew” necessitating an emergency landing in a field near the intersection of two roads outside Pretty Prairie, KS. The pilot was uninjured.
The 182 JT-A first flew in May 2013 and had flown over 200 hours during its certification process.
The CE-182 were also assembled by Reims Aviation in France.
Four CE-182 were delivered to the Royal Canadian Army, designated L-19L.
1956 Cessna 182 Engine: Continental O-470L, 179 hp @5000ft TBO: 1500 hr Fuel Type: 100LL Propeller type: CS Landing Gear: Tri./Fixed Max ramp weight: 2800 lb Gross weight: 2800 lb Empty weight, std: 1560 lb Useful load, std: 1005 lb Payload, full std. fuel: 645 lb Fuel capactiy, std: 55 USgal Wingspan: 36 ft. 2 in. Overall length: 27 ft. 10 in. Height: 9 ft. Wing area:174 sq. ft Seating capacity: 4 Cabin doors: 2 Cabin width: 45 in Cabin height: 46 in Baggage capacity: 120 lb Cruise speed @ 5,000 ft 75% power: 160 mph Cruise speed @ 5,000 ft 65% power: 151 mph Cruise speed @ 5,000 ft 55% power: 141 mph Max range (w/ reserve) @ 5,000 ft 75% power: 680 nm Max range (w/ reserve) @ 5,000 ft 65% power: 750 nm Max range (w/ reserve) @ 5,000 ft 55% power: 790 nm Fuel consumption 75% power: 13.0 USgph Fuel consumption 65% power:11.1 USgph Fuel consumption 55% power: 10.0 USgph Estimated endurance (65%) (hrs): 4.9 Vs: 62 mph Vso: 59 mph Best rate of climb: 1200 fpm Service ceiling: 20,100 ft Takeoff ground roll: 620 ft Takeoff over 50-ft. obstacle:1020 ft Landing ground roll: 610 ft Landing over 50-ft. obstacle: 1290 ft
CE-182D Engine: Continental, 230 hp. Wing span: 35 ft 10 in. Length: 28 ft 2 in. Height: 9 ft 1.5 in. Empty wt: 1645 lbs. Gross wt: 2950 lbs. Useful load: 1305 lbs. Wing loading: 16.9 lbs/sq.ft. Pwr loading: 12.8 lbs/hp. Baggage cap: 200 lbs. Max speed: 146 kts / 168 mph. Cruise: 139 kts / 160 mph. Stall: 50 kts / 57 mph. Initial ROC: 890 fpm. Service ceiling: 17,700 ft. Range (49 USG): 690 sm.
Engine: Continental 0-470-R, 230 hp. Wing Span: 35 ft 10 in / 10.92 m Length: 28 ft 2in / 8.59 m Height: 9 ft 1.5 in. Gross weight: 2950 lb / 1338 kg Empty weight: 1595 lb / 723 kg Wing Load: 16.9 lbs/sq. ft. Power Load: 12.8 lbs/hp. Top Speed: 168 mph. Cruise Speed, 75%: 157 mph / 136 kt / 253 kph at 6500 ft / 1980 m Range, max, (aux fuel): 1,160 st. miles / 1007 nm / 1864 km at 97 kt / 112 mph / 180 kph Rate of Climb: 890 fpm / 271 m/min Service Ceiling: 17,700 ft / 5395 m Takeoff roll: 705 ft. Takeoff Over 50 ft: 1,350 ft. Landing Roll: 590 ft. Landing Over 50 ft: 1,350 ft. Stall Speed: 57 mph Seats: 4
1979 Skylane Engine: Continental O 470 U, 230 hp. TBO: 1,500 hrs. Prop: two blade, constant speed. Length: 28 ft. Height: 9 ft. 3 in. Wingspan: 36 ft. Wing area: 174 sq.ft. Max ramp weight: 2,960 lbs. Max takeoff weight: 2,950 lbs. Standard empty weight: 1,700 lbs. Max useful load: 1,260 lbs. Empty weight: 1,838 lbs. Useful load: 1,122 lbs. Max landing weight: 2,950 lbs. Wing loading: 16.9 lb/sq.ft. Power loading: 12.8 lb/hp. Max usable fuel: 88 USG/528 lbs. Max rate of climb, sea level: 1,010 fpm. Max rate of climb, 8,000 ft: 565 fpm. Service ceiling: 16,500 ft. Max speed: 148 kts. Max cruise speed: 144 kt. Max range: 1,095 nm. Cruise, 65 % power at 8,000 ft: 135 kts. Fuel flow at 65% power: 11.1 USG/hr. Endurance at 65% pwr, 45 min. res: 7.8 hrs. Stalling speed, clean: 56 kts. Stalling speed, flaps down: 50 kts. Turbulent air penetration speed: 111 kts. Takeoff dist 50 ft obstacle: 1350 ft. Landing Dist 50 ft obstacle: 1,350 ft. Seats: 4.
Skylane II Engine: Continental O 470 U, 230 hp. TBO: 1,500 hrs. Prop: Constant speed, two blade, 82 in. dia. Length: 28 ft. 1.5 in. Height: 9 ft. 1.75 in. Wingspan: 36 ft. Wing area: 174.55 sq. ft. Wing loading: 16.9 lbs./sq. ft. Seats: 4. Empty wt: 1,837 lbs. Useful load: 1,113 lbs. Gross weight: 2,950 lbs. Power loading: 12.8 lb/hp. Fuel cap: 75 USG/450 hp. Minimum runway requirement: 1,350 ft. Rate of climb: 1,010 fpm. Service ceiling: 16,500 ft. Maximum speed: 148 knots. Maximum cruise, 75% power at 8,000 ft: 144 knots. Economy cruise, 59% power at 8,000 ft: 129 knots. Range at max cruise (45 min res): 735 nm. Range at economy cruise (45 min res): 830 nm. Duration at max cruise (45 min res): 5.22 hrs. Stalling speed, full flaps: 52 knots.
CE-182G Engine: 230 hp Continental O-307-R Wingspan: 36 ft 2 in Length: 27 ft 4 in Height: 9 ft 0 in Wing area: 174 sq.ft Empty weight: 1545 lb Loaded weight: 2800 lb Max speed: 167 mph Cruise 75%: 159 mph ROC: 980 fpm Max range: 1190 mi
1965 Cessna 182H Skylane Engine: Continental O-470R, 230 hp TBO: 1500 hr Propeller: Const. spd. Landing gear: Tri/Fixed Gross weight: 2800 lb Empty weight, std: 1560 lb Useful load, std: 1240lb Fuel: 79 USgal Wingspan: 36 ft. 2 in. Overall length: 27 ft. 10 in. Height: 9 ft. Wing area: 174 sq. ft Seating capacity: 4 Cabin width: 45 in Cabin height: 46 in Baggage capacity:120 lb Cruise speed 75% power: 140 kt Cruise speed 65% power: 133 kt Max range (w/ reserve) 75% power: 655 nm Max range (w/ reserve) 65% power: 735 nm Fuel consumption 75% power: 13.9 USgph Fuel consumption 65% power: 12.1 USgph Estimated endurance (65% power with 1-hr. reserve): 5 hr 12 min Stall speed (gear, flaps down): 48 knot Best rate of climb: 980 fpm Service ceiling: 18,900 ft Takeoff ground roll: 625 ft Landing ground roll: 590 ft No built: 840.
1997 Cessna 182 Skylane Engine: Lycoming IO-540-AB1A5, 230 hp TBO: 2000 hr Propeller: Const. spd. Landing gear: Tri/Fixed Gross weight: 3100 lb Empty weight, std: 1881 lb Useful load, std: 1219 lb Fuel: 88 USgals Wingspan: 36 ft. Overall length: 28 ft. Height: 9 ft. 3 in. Wing area:175.5 sq. ft Seating capacity: 4 Cabin width: 42 in Cabin height: 48 in Baggage capacity:200 lb Cruise speed 75% power: 140 kt Cruise speed 65% power: 135 kt Max range (w/ reserve) 75% power: 813 nm Max range (w/ reserve) 65% power: 870 nm Fuel consumption 75% power: 13.5 USgph Fuel consumption 65% power:12.2 USgph Estimated endurance (65% power with 1-hr. reserve): 6 hrs. 12 mins. Stall speed (gear, flaps down): 46 knot Best rate of climb: 924 fpm Service ceiling: 18,100 ft Takeoff ground roll: 795 ft Landing ground roll: 540 ft
CE-182P
CE-182Q Engine: 1 x Continental O-470-U, 230 hp. TBO: 1500 hrs. Prop: McCauley 2 blade, constant speed, 82 in. Seats: 4. Length: 28 ft. Height: 9.3 ft. Wingspan: 35.8 ft. Wing area: 174 sq.ft. Wing aspect ratio: 7.4. Max ramp wt: 3110 lbs. Max take off wt: 3100 lbs. Standard empty wt: 1730 lbs. Max useful load: 1380 lbs. Max landing wt: 2950 lbs. Wing loading: 17.8 lbs/sq.ft. Power loading: 13.5 lbs/hp. Max useable fuel: 528 lbs. Climb rate: 865 fpm @ 81 kts. Climb gradient: 640 ft/nm. Rate of climb @ 8000 ft: 455 fpm. Service ceiling; 14,900 ft. Max speed: 146 kts. Cruise @ 65% power @ 8,000ft: 133 kts. Fuel flow @ 65% power @ 8,000ft: 67 pph. Endurance @ 65% power @ 8,000ft: 7.6 hr. Stalling speed clean: 54 kts. Stall speed flaps down: 49 kts. Turbulent air penetration speed: 109 kts. Fixed undercarriage.
CE-182RG Engine: Lycoming O 540 J3C5D, 235 hp. TBO: 2,000 hrs. Prop: two blade, constant speed. Length: 28 ft. 8 in. Height: 8 ft. 11 in. Wingspan: 36 ft. Wing area: 174 sq.ft. Max ramp weight: 3,112 lbs. Max takeoff weight: 3,100 lbs. Standard empty weight: 1,732 lbs. Max useful load: 1,380 lbs. Empty weight: 1,876 lbs. Useful load: 1,236 lbs. Max landing weight: 3,100 lbs. Wing loading: 17.8 lb/sq.ft. Power loading: 13.2 lb/hp. Max usable fuel: 88 USG/528 lbs. Max rate of climb, sea level: 1,140 fpm. Max rate of climb, 8,000 ft: 555 fpm. Service ceiling: 14,300 ft. Max speed: 160 kts. Max cruise speed: 156 kt. Cruise, 65 % power at 8,000 ft: 148 kts. Fuel flow at 65% power: 11.8 USG/hr. Endurance at 65% pwr, 45 min. res: 6.6 hrs. Stalling speed, clean: 54 kts. Stalling speed, flaps down: 50 kts. Turbulent air penetration speed: 111 kts. Max X-wind: 18 kts. Takeoff dist 50 ft obstacle: 1,570 ft. Landing dist 50 ft obstacle: 1,320 ft. Seats: 4.
CE-182S Engine: Lycoming IO-540-AB1A5, 230 hp. Prop: McCauley 2 blade CS. Empty wt: 1910 lbs. Range: 825 nm. Cruise 75% 8000 ft: 140 kt. Cruise SL: 146 kt. Service ceiling: 14,900 ft. ROC: 865 ft. TO dist: 805 ft. Max ramp wt: 3110 lb. Usable fuel: 88 USG. Useful load: 1360 lb.
2000 Cessna 182S Engine: Lycoming IO-540-AB1A5, 230 hp @SL TBO: 2000 hr Fuel Type: 100/100LL Propeller type: McCauley CS three-blade/79 in. Landing Gear: Tri./Fixed Max ramp weight:3110 lb Gross weight: 3100 lb Landing weight: 2950lb Empty weight, std: 1928 lb Useful load, std: 1182 lb Payload, full std. fuel: 654lb Usable fuel: 88 USgal Wingspan: 36 ft. Overall length: 29 ft Height: 9 ft. 4 in. Wing area:174 sq. ft Wing loading: 17.8 lbs./sq. ft Power loading: 13.5 lbs./hp Wheel track: 9 ft. Wheel size: 6.00 x 6 in Seating capacity: 4 Cabin doors: 2 Cabin width: 42 in Cabin height: 48.5 in Baggage capacity: 200 lb Cruise speed 75% power @ 6,000 ft: 140 kt Cruise speed 65% power @ 8,000 ft: 130 kt Cruise speed 45% power @ 10,000 ft: 121 kt Max range (w/ reserve) 75% power @ 6,000 ft: 820 nm Max range (w/ reserve) 65% power @ 8,000 ft: 910 nm Max range (w/ reserve) 45% power @ 10,000 ft: 968 nm Fuel consumption 75% power @ 6,000 ft: 12.5 USgph Fuel consumption 65% power @ 8,000 ft: 11.1 USgph Fuel consumption 45% power @ 10,000 ft: 9.5 USgph Estimated endurance (65%): 7.0 hr Stall speed (gear, flaps up): 56 knot Stall speed (gear, flaps down): 50 knot Best rate of climb: 924 fpm Best rate of climb (@8,000 ft): 565 fpm (est.) Service ceiling: 18,100 ft Takeoff ground roll: 795 ft Takeoff over 50 ft. obstacle: 1514 ft Landing ground roll: 590 ft Landing over 50 ft. obstacle: 1350 ft
2004 Cessna 182T Skylane Engine: Lycoming IO-540-AB145, 230 hp Propeller: 3-blade CS/79 in Landing gear type: Tri/Fixed Max ramp weight: 3110 lb Gross weight: 3110 lb Max landing weight: 2950 lb Empty weight, std: 1897 lb Max useful load, std: 1213 lb Payload, full std. fuel: 728 lb Usable fuel, std: 88 USgal Wingspan: 36 ft. Overall length: 29 ft. Height: 9 ft. 4 in. Wing area (sq. ft.):174Wing loading (lbs./sq. ft.): 17.8 Power loading (lbs./hp.): 13.5 Wheel size, nose (in.):5.00 x 5 Wheel size, main (in.): 6.00 x 6 Seating capacity: 4 Cabin width (in.): 42 Cabin height (in.): 48.5 Baggage capacity (lbs.):200 Max speed, SL (kts.): 149 80% power @ 6,000 ft. (kts.): 145 Cruise: 80% @ 12,500 ft: 158 kts. Max range (nm): 75% power @ 6,000 ft.: 968 55% power @ 10,000 ft.: 845 Vs (kts.): 54Vso (kts.): 49 Rate of climb (SL fpm): 924 Service ceiling (ft.): 18,100 Takeoff ground roll (ft.): 795 Takeoff over 50-ft. obstacle (ft.):1514 Landing ground roll (ft.): 590 Landing over 50-ft. obstacle (ft.): 1350 Source: Cessna Aircraft Corporation
CE-R182 First built in 1977. Engine: 1 x Lycoming O-540-J3C5D, 235 hp. TBO: 2000 hrs. Prop: McCauley 2 blade, constant speed 82 in. Seats: 4. Length: 28.6 ft. Height: 8.9 ft. Wingspan: 35.8 ft. Wing area: 174 sq.ft. Wing aspect ratio: 7.4. Max ramp wt: 3112 lbs. Max take off wt: 3100 lbs. Standard empty wt: 1757 lbs. Max useful load: 1355 lbs. Max landing wt: 3100 lbs. Wing loading: 17.8 lbs/sq.ft. Power loading: 13.2 lbs/hp. Max useable fuel: 528 lbs. Climb rate: 1140 fpm @ 88 kts. Climb gradient: 784 ft/nm. Rate of climb @ 8000 ft: 560 fpm. Service ceiling: 18,000ft. Max speed: 160 kts. Cruise @ 65% power @ 8,000ft: 148 kts. Fuel flow @ 65% power @ 8,000ft: 71 pph. Endurance @ 65% power @ 8,000ft: 7.3 hr. Stalling speed clean: 54 kts. Stall speed gear/flaps down: 50 kts. Turbulent air penetration speed: 112 kts. Retractable nose wheel undercarriage.
Cessna T182T Skylane Engine: Lycoming IO-540-AK1A, 235 hp @SL to 20,000 ft TBO: 2000 hr Fuel Type: 100/100LL Propeller type: McCauley 3-blade CS Landing Gear: Tri/Fixed Max ramp weight: 3112 lb Gross weight: 3100 lb Landing weight: 2950 lb Empty weight, std: 2048 lb Useful load, std: 1052 lb Payload, full std. fuel: 524 lb Usable fuel, std: 88 USgal Wingspan: 36 ft. Overall length: 29 ft. Height: 9 ft. 4 in. Wing area: 174 sq. ft Wing loading: 17.8 lbs./sq. ft Power loading: 13.2 lbs./hp Wheel base: 5 ft. 6 in. Wheel track: 9 ft. Wheel size: 6.00 x 6 in Seating capacity: 4 Cabin doors: 2 Cabin width: 44 in Cabin height: 48.5 Baggage capacity: 200 lb Cruise speed 88% power @ 12,000 ft.: 160 kt Max range (w/ reserve) 75% power @ 10,000 ft.: 700 nm Estimated endurance (65%): 5.5 hr Stall speed (gear, flaps up): 54 knot Stall speed (gear, flaps down): 49 knot Best rate of climb (SL): 1060 fpm Best rate of climb, 10,000 ft: 1000 fpm Service ceiling: 20,000 ft Takeoff ground roll: 790 ft Takeoff over 50 ft. obstacle: 1475 ft Landing ground roll: 590 ft Landing over 50 ft. obstacle: 1350 ft
CE-TR182 First built in 1978. Engine: 1 x Lycoming O-540-L3C5D, 235 hp. TBO: 2000 hrs. Prop: McCauley 2 blade, constant speed 82 in. Seats: 4. Length: 28.6 ft. Height: 8.9 ft. Wingspan: 35.8 ft. Wing area: 174 sq.ft. Wing aspect ratio: 7.4. Max ramp wt: 3112 lbs. Max take off wt: 3100 lbs. Standard empty wt: 1794 lbs. Max useful load: 1318 lbs. Max landing wt: 3100 lbs. Wing loading: 17.8 lbs/sq.ft. Power loading: 13.2 lbs/hp. Max useable fuel: 528 lbs. Climb rate SL: 1040 fpm @ 90 kts. Climb gradient: 711 ft/nm. Rate of climb @ 8000 ft: 930 fpm. Certificated ceiling: 20,000 ft. Max speed (20,000ft): 187 kts. Cruise @ 65% power @ 8,000ft: 146 kts Cruise @ 65% pwr @ 18,000 ft: 159 kts. Fuel flow @ 65% power @ 18,000ft: 74 pph. Endurance @ 65% power @ 18,000ft: 7 hr Stalling speed clean: 54 kts. Stall speed gear/flaps down: 50 kts. Turbulent air penetration speed: 112 kts. Undercarriage: Retractable nose wheel. Max Range: 1030 nm Take-off 50ft: 1570 ft Landing 50 ft: 1320 ft
CE-TR182T Engine: 1 x Lycoming O-540-L3C5D, 235 hp. TBO: 2000 hrs. Prop: McCauley 2 blade, constant apeed 82 in. Seats: 4. Length: 28.4 ft. Height: 9.2 ft. Wingspan: 35.8 ft. Wing area: 174 sq.ft. Wing aspect ratio: 7.4. Undercarriage track, 9 ft 0 in (2,74 m) Wing dihedral, 1 deg 44 sec constant Max ramp wt: 3112 lbs. Max take off wt: 3100 lb Standard empty wt: 1740 lb Max useful load: 1372 lbs. Max landing wt: 2950 lbs. Wing loading: 17.8 lbs/sq.ft. Power loading: 13.2 lbs/hp. Max useable fuel: 528 lbs. Climb rate: 965 fpm @ 87 kts. Climb gradient: 670 ft/nm. Rate of climb @ 8000 ft: 850 fpm. Certificated ceiling; 20,000 ft Max speed: 168 kts at 20,000 ft (6 100 m) Cruising speed at 20,000 ft (6 100 m) 75 per cent power: 158 kts (293 km/h) Cruising speed at 10,000 ft (3050 m) 75 per cent power: 145 kts (269 km/h) Cruise @ 65% power @ 8,000ft: 133 kts Cruise @ 65% pwr @ 18,000ft: 145 kts Fuel flow @ 65% power @ 18,000ft: 75 pph Endurance @ 65% power @ 18,000ft: 6.8 hr Range at 20,000 ft (6 100 m) at 75 per cent power: 745 nm (1380 km) Max range at 10,000 ft (3 050 m): 920 nm (1704 km). Stalling speed clean: 54 kts. Stall speed flaps down: 49 kts. Turbulent air penetration speed: 111 kts. Take off distance to 50 ft (15,2 m): 1,475 ft (450 m) Landing distance from 50 ft (15,2m): 1,350 ft (411 m). Undercarriage: Fixed. First built:1981.
2005 Cessna Turbo Skylane 182 Engine: Textron Lycoming TIO-540 AK1A, 235 hp @20,000 ft TBO: 2000 hr Fuel Type: 100/100LL Propeller type: McCauley CS Landing Gear type: Tri./Fixed Max ramp weight: 3112 lb Max landing weight: 2950 lb Empty weight, std: 2017 lb Max useful load: 1089 lb Payload, full std. fuel: 567lb Useful fuel, std: 87 USgals Wingspan: 36 ft Overall length: 29 ft Height: 9 ft. 4 in. Wing area: 174 sq. ft Wing loading: 17.8 lbs./sq. ft Power loading: 13.2 lbs./hp Wheel size: 6.00 x 6 in Seating capacity: 4 Cabin doors: 2 Cabin width: 42 to 44 in Cabin height: 48.5 in Cruise speed 88% power @ 12,500 ft: 158kt Fuel consumption 88% power: 14.0 USgph Vso: 49 kt Best rate of climb (SL): 1040 fpm Max operating altitude: 20,000 ft Takeoff ground roll: 775 ft Takeoff over 50-ft. obstacle: 1385 ft Landing ground roll: 590 ft Landing over 50-ft. obstacle: 1350 ft
2008 Cessna Turbo Skylane Engine: Lycoming TIO-540-AK1A, 250 hp TBO: 1700 hr Fuel type: 100/100LL Propeller: CS McCauley Undercarriage; Fixed/Retractable Max ramp weight (lbs.): 3112 Gross weight (lbs.): 3100 Landing weight (lbs.): 2950 Empty weight, std. (lbs.): 2082 Useful load, std. (lbs.): 1030 Payload, full std. fuel (lbs.): 508 Usable fuel, std. (gals.): 87 Wingspan (ft.): 36 Overall length (ft.): 29 Height: 9 ft. 4 in. Wing area (sq. ft.): 174 Wing loading (lbs./sq. ft.): 17.8 Power loading (lbs./hp.): 13.2 Wheel size (in.): 6.00 x 6 Seating capacity: 4 Cabin doors: 2 Cabin width (in.): 42 Cabin height (in.): 48.5 Cruise speed, 88%, FL200: 176 kt Cruise speed, 88%, 12,500 ft: 159 kt Range@FL200 88% power: 763 nm Range@FL200 45% power: 915 nm Vso (kts.): 49 Best rate of climb, SL (fpm): 1040 Service ceiling (ft.): 20,000 Takeoff distance (ft.): 775 Takoff over 50 ft. obstacle (ft): 1385 Landing distance (ft.): 590 Landing over 50 ft. obstacle (ft): 1350
Cessna Turbo Skylane RG II Engine: Lycoming 0-540L3C5D, 235 hp TBO hrs: 2000 Fuel type: 100LL Propeller: Constant speed / 82 in Landing gear type: Tri./Retr. Max ramp weight (lbs.): 3112 Gross weight (lbs.): 3100 Landing weight (lbs.): 3100 Empty weight, std. (lbs.): 1815 Useful load, std. (lbs.): 1297 Usable fuel, std. (USgals.): 88 Wingspan: 36 ft. Overall length: 28 ft. 7.5 in. Height: 8 ft. 11 in. Wing area (sq. ft.): 174 Wing loading (lbs./sq. ft.): 17.8 Power loading (lbs./hp.): 13.2 Wheel base: 5 ft. 4 in. Wheel track (ft.): 9 Wheel size, nose (in.): 5 Wheel size, mains (in.): 6 Seating capacity: 4 Cabin doors: 2 Cabin width (in.): 42 Cabin height (in.): 48.5 Baggage capacity, two areas (lbs.): 120/80 Cruise speed 75% power: 128 kt Max range (w/ reserve) 75% power: 444 nm Max range (w/ reserve) 65% power: 487 nm Max range (w/ reserve) 55% power: 522 nm Vs (kts.): 45 Best rate of climb, SL (fpm): 667 Service ceiling (ft.): 15,100 Takeoff distance (ft.): 1135 Takeoff over 50-ft. obstacle (ft.): 1608 Landing distance (ft.): 920 Landing over 50-ft. obstacle (ft.): 1400
Cessna 1979 182 Turbo Skylane RG Engine: Lyc. O-540-L3C5D, 235 hp TBO hr: 2000 Propeller: Const. spd. Landing gear type: Tri/Retr. Gross weight (lbs.): 3100 Empty weight, std. (lbs.): 1844 Useful load, std. (lbs.): 1256 Fuel (USgals.): 88 Wingspan: 35 ft. 10 in. Overall length: 28 ft. 7.5 in. Height: 8 ft. 11 in. Wing area (sq. ft.): 174 Seating capacity: 4 Cabin width (in.): 42 Cabin height (in.): 48.5 Baggage capacity (lbs.): 200 Cruise speed 75% power: 173kt Cruise speed 65% power: 162 kt Max range (w/ reserve) 75% power: 825 nm Max range (w/ reserve) 65% power: 905 nm Fuel consumption 75% power: 14.2 USgph Fuel consumption 65% power: 12.4 USgph Estimated endurance (65% power with 1-hr. reserve): 6 hrs. Stall speed (gear, flaps down) (knots): 50 Best rate of climb (fpm): 1040 Service ceiling (ft.): 20,000 Takeoff ground roll (ft.): 820 Landing ground roll (ft.): 600
Cessna 182 Texas Skyways O-550 Conversion Engine: Continental O-550-F/TS, 285 hp TBO hr: 2500 Fuel Type: 100LL Propeller type: Hartzell/McCauley two- or three-blade Landing Gear type: Tri/Fixed Max ramp weight (lbs.): 2950/3100 Gross weight (lbs.): 2950/3100 Max landing weight (lbs.): 2950/3100 Empty weight, std. (lbs.): 1600 Usable fuel (USgals.): 74 Wingspan: 36 ft. Overall length: 28 ft. 1.5 in. Height: 9 ft. 2 in. Wing area (sq. ft.): 174 Wing loading (lbs./sq. ft.): 16.9 Power loading (lbs./hp.): 10.6 Wheel track: 9 ft. 1 in. Wheel size (in.): 6 Seating capacity: 4 Cabin doors: 2 Cabin width (in.): 42 Cabin height (in.): 48.5 Baggage capacity (lbs.): 120 Cruise speed @ 6,500 ft 75% power: 162 kts Cruise speed @ 6,500 ft 65% power: 159 kts Cruise speed @ 6,500 ft 55% power: 148 kts Max range (w/ reserve)(88 USgal) 75% power: 850 nm Max range (w/ reserve)(88 USgal) 65% power: 976 nm Max range (w/ reserve)(88 USgal) 55% power: 1084 nm Fuel consumption 75% power: 15 USgph Fuel consumption 65% power: 13 USgph Fuel consumption 55% power: 11 USgph Estimated endurance (65%) (1-hr. reserve) (hrs): 5.7 Vs (kts.): 50 Vso (kts.): 45 Best rate of climb (fpm): 1600 Takeoff ground roll (ft.): 400 Landing ground roll (ft.): 600 Max level speed (knots): 170
2004 Cessna Skylane 182T 230 hp @SL Gross weight (lbs.): 3110 Wing loading (lbs./sq. ft.): 17.8 Power loading (lbs./hp.): 13.5 Cruise speed, 80% power @ 6000 ft. (kts.): 145 Range, 75% power @ 6000 ft. (nm): 968 Fuel Capacity (USgals.) 88 Best rate of climb, SL (fpm): 924 Takeoff distance (ft.): 795 Landing distance (ft.): 590
Cessna 182 SMA Diesel Skylane Engine: SMA SR305-230, 230 hp TBO hrs: 2000 Fuel type: Jet A Propeller: MT/CS Landing gear type: Tri./Fixed Gross weight (lbs.): 2950 Landing weight (lbs.): 2950 Empty weight, std. (lbs.): 1843 Useful load, std. (lbs.): 1007 Payload, full std. fuel (lbs.): 479 Useful fuel, std. (USgals.): 88 Wingspan: 35 ft. 10 in. Overall length: 28 ft. Height: 79 ft. 3 in. Wing area (sq. ft.): 183.4 Wing loading (lbs./sq. ft.): 16.1 Power loading (lbs./hp.): 12.8 Wheel size (in.): 6.00 x 6 Seating capacity: 4 Cabin doors: 2 Cabin width (in.): 43 Cabin height (in.): 47 Max cruise speed SL: 129 kt Max cruise speed @ 10,000 ft.: 138 kt Max cruise speed @ 12,500 ft.: 140 kt Fuel consumption 100%: 12.4 USgph Fuel consumption 85% power: 8.9 USgph Fuel consumption 65% power: 6.6 USgph Vso (kts.): 45 Best rate of climb (SL fpm): 1000 Maximum operating altitude (ft.): 12,500 Takeoff ground roll (ft.): 780 Takeoff over 50-ft. obstacle (ft.): 1440 Landing ground roll (ft.): 590 Landing over 50-ft. obstacle (ft.): 1350
