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.

Cessna CE-185 Skywagon / U-17 Article

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.

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.

Gallery

CE-185
Engine: Continental IO-470-F, 260 hp.

CE-185A
Engine: Continental IO-470-F, 260 hp.

CE-185B
Engine: Continental IO-470-F, 260 hp.

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-185D
Engine: Continental IO-470-F, 260 hp.

CE-185E
Engine: Continental IO-470-F, 260 hp. or Continental IO-520-D, 300 hp.

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.

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.

Gallery

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

182 JT-A
Fuel: Diesel

To counter competition from Beech’s Bonanza and North American’s Navion, work began, under the direction of project engineer Web Moore, on a higher performance aircraft based on the Cessna 170B.

Cessna took a Cessna 170 fuselage and installed a Conti¬nental six-cylinder engine 0-470, together with a Hartzell constant speed aluminium alloy propeller. In its original form, the 0-470-A, the engine developed 225 horsepower/168kW, and to compen¬sate for the extra torque on take-off the characteristic rounded tailfin (which had featured on all Cessnas since 1927) was replaced by a big bold square tail and larger and more powerful elevators were required. But by the time the prototype Cessna 180 (NX41697, c/n 604) had reached flying stage on 26 May 1952 (Piloted by Cessna’s chief pilot, Hank Waring), the type had gained a completely new fuselage.

The all metal wing section was of the classic ‘NACA 2412’ series the same wing and flap system as the Model 170B, and included slotted Fowler flaps and the chrome vanadium spring steel undercarriage legs also found in the Cessna 170 and Cessna 305 (Bird Dog). The tail wheel features a tubular steel spring with a steerable and full swiveling pneumatic tire and wheel. In those days the Fowler flaps were dubbed “Para Lift” flaps, by Cessna and were operated by a single lever (known as the Johnson bar). The flap lowering speed was initially 100 mph (87 knots), until 1964 when it was increased to 110 mph (95 knots). With the airspeed indicator now in knots, from 1976 onwards 10 degrees could be lowered at speeds up to 120 knots, with VFE for the 20- to 40-degree settings being 90 knots. The additional power available for the Model 180 permitted an increase in maximum take-off weight from 998 to 1157kg with the same wing area of 16.16sq.m.

Fuel was in gravity feed from wing tanks originally “cells” but “wet wings” eventually became the norm. The early models held 60 gallons, but between 1957 and 1964 the Cessna 180s were fitted with 65-gallon tanks and the 84-gallon tanks were a later option.

Certification of the type (#5A6) was achieved on 23 December 1952 and the first production machines rolled out in October 1952, customer deliveries began in February of 1953. Floats and skis were approved from the early days. All models of the Cessna 180 are approved for operation on floats. In 1955 the Edo Corporation introduced an amphibious model which could be installed on any 180. The Cessna 180 was the first aircraft of a four place type ever to be approved for use with retractable gear amphibious floats. In addition, a very wide variety of ski installations are also approved, including wheel replacement, wheel penetration and hydraulic retractable wheel skis. The “prototype” aircraft was scrapped in May 1954.

Production of the Cessna model 180 began in 1953 with the production prototype, N2800A. This model had no external baggage door and was powered by the Continental 0-470-A engine, which gave 225 hp at 2,600 rpm. In 1954 the outside baggage door was introduced and the powerplant was changed to the 0-470-J near the end of the production year, giving the same power output at 50 less rpm.
In 1955 the spring steel undercarriage was raked forward three inches to improve ground handling. A heavier windshield was fitted, as well as other sound proofing in the cabin. The fresh air inlets near the wing roots were moved further out along the wing leading edge-beyond the propeller slipstream in an effort to further reduce the interior noise levels.
In 1956 the Continental 0-470-K of 230 hp at 2,600 rpm came on stream with larger steel cast cylinder heads with thinner, and therefore more, cooling fins. Dynamic dampeners were fitted and revised engine mounts made for a smoother engine. A large single stainless steel muffler and exhaust pipe replaced the previous dual muffler system and accordingly the engine cowling was redesigned with the carburettor air scoop now at the bottom. The fuel vent to the main tanks was moved from above the left wing root to behind the left wing strut. This year also saw Cessna add a nosewheel to the 180 to create the model 182.
The Cessna 180A was released in 1957, which had an increase in its maximum take-off weight of 100 lbs and stronger undercarriage legs. Electric fuel gauges also appeared, replacing the manual variety, and the fuel capacity was upped to 65 gallons. In 1958 the exhaust was moved to the right-hand side to direct the outflow beneath the fuselage, instead of the previous tendency to stain along the left-hand side due to slipstream effects. A new ratchet mechanism was also added to prevent the trim wheel from creeping.
In 1959 the Model 180B was released. Changes included heavier door hinges and another revised instrument panel.

1960. Model 180C released. Mark ruled with Continental 0-470-L and incorporated a new cowl and nose cap. The wing fuel filler caps were made flush, and a redesigned bulkhead and fuselage top skin gave increased headroom in rear seat area.

In 1961 the Model 180D was released. Bendix “shower of sparks” magnetos were fitted. New lever type of cowl flap control introduced. A “heavy-duty” version of the Cessna 180 with more power and a greater useful load was introduced as the Cessna 185.
In 1962 the Model 180E was released, fitted with a Continental 0-470-R engine and new wingtips. New fuel tank outlets were also added (to give two per tank) to improve fuel flow.
Released in 1963 the Model 180F had magnetos changed to the impulse model, new magnesium cast rudder pedals fitted and lighting controls for the instruments were introduced into an overhead panel. A 10-degree flap position was also introduced.
The 1964 Model 180G featured a third window added to the fuselage side, with scaling for six an option. Cessna 185 landing gear with a strengthened axle fitted. VNE was increased to 192 mph (from 184), and flap extension speed increased to 110 mph. MAUW increased by 150 lbs. Generator replaced with a 52-amp alternator.
The Model 180H was released in1965 featuring the Cessna 182 firewall, making the 180 and the 185 basic airframe identical. The panel was redesign with a central radio stack. In 1967 a more pointed propeller spinner was introduced and the rear baggage area extended. A 60-amp alternater fitted, and Cleveland brakes became standard, and in 1969, the Skywagon name used for the first time. 1970 introduced the conical camber wingtip, which reduced the wingspan by four inches.
In 1973 the Model 180J was released and the “Camber Lift’ wing appeared with its bonded loading edge (the same modified 2412 airfoil, further modified). The instrument panel was again revised and now incorporated rocker switches, and the two landing lights moved from the wings to the engine cowling. In 1974 a redesigned vertical fin attachment was fitted.
In 1975 the powerplant changed to the Continental O-470-S and a float plane kit included the Cessna vertical fin/fillet.
In 1976 the airspeed indicator was changed to knots, the flap extension speed was increased to 120 knots and McCauley main wheels and brakes were introduced.
In 1977 Model 180K was released. The high compression Continental 0-470-U was fitted, which gave 230 hp at 200 rpm less to satisfy the noise certification requirements. This engine was actually the IO-470-U with the fuel injection removed and run at only 2400 revolutions; run at 2,600 rpm the engine produces 250 hp. A vernier mixture control became standard, and stronger McCauley tailwheel on strengthened spring tube was also fitted. The fuel bladder tanks were replaced by “wet wing” tankage of 88 gallons in 1979.

In the late 1970s the Model 180 was available in two forms: the basic Model 180 Skywagon, and the improved Model 180 Skywagon II with a factory-installed avionics package.
In 1981, thirty-five aircraft were built in this, the 180’s final production year. By 10 September 1981, when the last Cessna 180 rolled off the production line, 7203 had been built. This last aircraft (53203) became VH-MQQ on 10 October 1981.
The empty weights have changed from 1953, 1480 lbs; 1555 lbs, 1957, and 1525 lbs in 1964. The gross weights from 1953: 2550 lbs, 1957: 2650 lbs and 1964: 2800 lbs. Service ceiling of 19,000 ft.

The first 180s, 1953 through 1956, had a factory list price of $12,950. This was up to $30,150 for the 1976 model.

Gallery

Production:

1953 180
Engine: Continental O-470-A, 225 hp at 2600rpm
Wingspan: 36 ft
Length: 26 ft 2 in
Height: 7 ft 6.6 in
Wing area: 175 sq.ft
Empty weight: 1460 lb
Loaded weight: 2550 lb
Max speed: 165 mph
Cruise: 150 mph
ROC: 1150 fpm
Service ceiling: 19,800 ft
Endurance: 4.5 hr
Fuel: 80/87
Compression: 7-1
No made: 639
SN 30,000 through 30,639

1954 180
Engine: Continental O-470-J, 225 hp at 2550rpm
Fuel: 80/87
Compression: 7-1
No made: 619
SN 30,640 through 31,259

1955 180
The engine was changed to O-470-J near the end of 1954 production run.
No made: 890
SN 31,260 through 32,150

1956 180
Engine: Continental O-470-K, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 519
SN 32,151 through 32,661

1957 180
Engine: Continental O-470-K, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 442
SN 32,662 through 32,999 and 50,000 through 50,105

1958 180A
Engine: Continental O-470-K, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 249
SN 50,106 through 50,355

1959 180B
Engine: Continental O-470-K, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 305
SN 50,356 through 50,661

1960 180C
Engine: Continental O-470-L, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 249
SN 50,662 through 50,911

1961 180D
Engine: Continental O-470-L, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 151
SN 50,912 through 51,063

1962 180E
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 119
SN 51,064 through 51,183

1963 180F
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 128
SN 51,184 through 51,312

1964 180G
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
Wingspan: 36 ft 2 in
Length: 25 ft 6 in
Height: 7 ft 6.5 in
Wing area: 174 sq.ft
Empty weight: 1525 lb
Loaded weight: 2800 lb
Max speed: 170 mph at SL
Cruise 75%: 164 mph
ROC: 1090 fpm
Service ceiling: 19,600 ft
Max range: 1215 mi
No made: 132
SN 51,313 through 51,445

1965 180H
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 161
SN 51,446 through 51,607

1966 180H
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 166
SN 51,608 through 51,774

1967 180H
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 100
SN 51,775 through 51,875

1968 180H
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 117
SN 51,876 through 51,993

1969 180H
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 109
SN 51,994 through 52,103

1970 180H
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 71
SN 52,104 through 52,175

1971 180H
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 45
SN 52,176 through 52,221

1972 180H
Engine: Continental O-470-R, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 62
SN 52,222 through 52,284

1973 180J
Engine: Continental O-470-S, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 99
SN 52,285 through 52,384

1974 180J
Engine: Continental O-470-S, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 115
SN 52,385 through 52,500

1975 180J
Engine: Continental O-470-S, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 119
SN 52,501 through 52,620

1976 180J
Engine: Continental O-470-S, 230hp @ 2600rpm
Fuel: 80/87
Compression: 7-1
No made: 149
SN 52,621 through 52,770

1977 180K
Engine: Continental O-470-U, 230hp @ 2400rpm
Fuel: 100 LL
Compression: 8.6-1
No made: 134
SN 52,771 through 52,905

1978 180K
Engine: Continental O-470-U, 230hp @ 2400rpm
Fuel: 100 LL
Compression: 8.6-1
No made: 94
SN 52,906 through 53,000

1979 180K
Engine: Continental O-470-U, 230hp @ 2400rpm
Fuel: 100 LL
Compression: 8.6-1
No made: 114
SN 53,001 through 53,115

1980 180K
Engine: Continental O-470-U, 230hp @ 2400rpm
Fuel: 100 LL
Compression: 8.6-1
No made: 51
SN 53,116 through 53,167

1981 180K
Engine: Continental O-470-U, 230hp @ 2400rpm
Fuel: 100 LL
Compression: 8.6-1
No made: 35
SN 53,168 through 53,203

Specifications:

CE-180
Engine: Continental O-470A, 225 hp.
MTOW: 2550 lb.

CE-180A
Engine: Continental O-470K, J or R, 225 hp.
Prop: Hartzell.
Wheel track: 7 ft 8 in.

CE-180A (1970)
Engine: 230 hp.
Wing span: 35 ft 10 in.
Length: 25 ft 9 in.
Height: 7 ft 9 in.
Empty wt: 1560 lbs.
Gross wt: 2800 lbs.
Useful load: 1240 lbs.
Wing loading: 16.1 lbs/sq.ft.
Pwr loading: 12.2 lbs/hp.
Baggage cap: 400 lbs.
Max speed: 149 kts / 170 mph.
Cruise: 141 kts / 162 mph.
Stall: 48 kts / 55 mph.
Initial ROC: 1090 fpm.
Service ceiling: 19,600 ft.
Range (65 USG): 695 sm.

CE-180H
Engine: Continental O-470R.

1977 CE-180 Skywagon
Engine: 1 x Continental O-470-U, 230 hp.
Seats: 4/6.
Wing loading: 16.1 lb/sq.ft.
Pwr loading: 12.2 lb/hp.
Gross wt: 2800 lb.
Empty wt: 1617 lb.
Equipped useful load: 1097 lb.
Payload max fuel: 647 lb.
Range max fuel/75% pwr: 724nm/5.1hr.
Range max fuel / 55% pwr: 893 nm/ 7.2 hr.
Service ceiling: 17,700 ft.
75% cruise: 141 kt.
55% cruise: 125 kt.
Stall: 44-50 kt.
1.3 Vso: 57 kt.
ROC: 1100 fpm.
Min field length: 1365 ft.
Fuel cap: 336/450 lb.

1979 Cessna Skywagon 180
Engine: Continental 0 470 U, 230 hp.
Max speed: 148 kt.
Max cruise speed: 142 kt.
Max range: 1,010 nm.
Max usable fuel: 84 USG.
ROC: 1,100 fpm.
Service ceiling: 17,700 ft.
Takeoff dist 50 ft obstacle: 1,205 ft.
Landing dist 50 ft obstacle: 1,365 ft.
Max ramp wt: 2,810 lbs.
Max useful load: 1,167 lbs.
Seats: 6.

Cessna 1976 180J Skywagon
Engine: Continental O-470S, 230 hp
TBO: 1500 hr
Propeller: Const. spd.
Landing gear type: Fixed/Conv.
Gross weight: 2800 lb
Empty weight, std: 1617 lb
Useful load, std: 1183 lb
Fuel: 75 USgal
Wingspan: 36 ft.
Overall length: 25 ft. 9 in.
Height: 7 ft. 9 in.
Wing area: 174 sq. ft
Seating capacity: 4-6
Cabin width: 41 in
Cabin height: 47 in
Baggage capacity: 350lb
Cruise speed 75% power: 141kt
Cruise speed 65% power: 138 kt
Max range (w/ reserve) 75% power: 670 nm
Max range (w/ reserve) 65% power: 730 nm
Fuel consumption 75% power: 13.9 USgph
Fuel consumption 65% power: 12.2 USgph
Estimated endurance (65% power with 1-hr. reserve): 4 hrs.
Stall speed (gear, flaps down): 48 knots
Best rate of climb: 1090 fpm
Service ceiling: 19,600 ft
Takeoff ground roll: 625 ft
Landing ground roll: 480 ft

Cessna introduced the Cardinal in late 1967 as an all new design, fixed-gear model, aimed at producing a better model 172 with a performance closer to the more powerful model 182.
The number 172 was assigned to the Cardinal early in its development, and there was actually thought that it might replace the Skyhawk. But the Cardinal’s number was increased to 177, and any plan to drop the Skyhawk was halted. The engine in the Skyhawk was upgraded, from a 145 horsepower Continental to a 112kW / 150 hp Lycoming O-320-E21D. This engine was also used in the Cardinal, resulting in commonality between the two.
There were mechanical problems with such things as the flaps, and there was a major problem with handling qualities. Some of the airplanes were broken on landing, and it became clear that the Cardinal’s stabilator (Cessna’s first and last) was a bit sensitive for pilots used to other Cessnas. There were indications too, that the stabilator could stall under some circumstances, resulting in hard hits on the runway. All Cardinals were recalled for modifications and the primary fix was the addition of an inverted slot in the stabilator.
With the 1969 model, the Cardinal’s horsepower was increased to 180, and to make it fly better at low speeds led the manufacturer to recontouring the singlespar semi-laminar airfoil section to provide a more rounded, conventional leading edge (a “modified 2400 series.”). This was a major and very successful redesign, making the 1970 and subsequent Cardinals very different machines from those of the first two model years. In 1970, Cessna began offering two versions of the airplane: one with retractable gear and a 200 hp engine, plus a 180 hp, fixed gear version.
In 1971 Cardinal II and Cardinal RG II versions appeared, these differing by having more comprehensive equipment as standard.
The 1972 models differ externally from those of the previous year by a more more efficient prop blade section (Clark Y airfoil section) and by a boarding assist step. On 1971 models it is a round strut below each door opening, with a step at the bottom. For 1972 the step is welded to the gear leg so it goes out of the slipstream when, the gear is retracted. Between them, these two changes are credited by Cessna with making the 1972 RG a full five mph faster in cruise than the 1971 models.
On the floor is a simple fuel selector system, an on-off valve which feeds from both of the 25-gallon wing tanks, but does not give you the option of draining one at a time.
In 1976 the Model 177 was withdrawn, the Cardinal becoming regarded as the basic model of the remaining four versions. Two years later the Cardinal also disappeared, the Cardinal II being renamed the Cardinal Classic. Over 1000 were sold in the first year but sales fell and a total of only 2500 were completed by the time the design was dropped in 1978.

The 1977 new Cardinal was priced at US$32,600; Cardinal II, US$35,350, and Cardinal H with “Nav Pac,” US$39,200.

Total production of the retractable undercarriage 177RG reached 1366 by 1978 when it was replaced by the 172RG Cutlass. Of all Cardinals delivered, about half were sold in the late 1960s, rather than the 1970s.

Gallery

C-177 Cardinal
Engine: O-320 E2D, 150 hp @2700@SL
TBO: 2000 hr
Fuel Type: 80/87 Avgas
Propeller: fixed/76 in
Landing gear type: Fixed/tri
Max ramp weight: 2350 lb
Gross weight: 2350 lb
Landing weight: 2350 lb
Empty weight, std: 1415 lb
Empty weight, as tested: 1481 lb
Useful load, std: 935 lb
Payload, full std. fuel: 641 lb
Usable fuel, std. (gals.): 49
Wingspan: 35 ft. 7.5 in.
Overall length: 26 ft. 11.5 in.
Height: 9 ft. 1 in
Wing area:173 sq. ft
Wing loading: 13.6 lb/sq. ft
Power loading: 15.7 lbs./hp
Wheel track: 8 ft. 3.5 in
Wheel size, nose: 5.00×5 in
Wheel size, mains: 6.00×6 in
Seating capacity: 4
Cabin doors: 2
Baggage capacity:120 lb
Cruise speed 75% power (w/ reserve 5.6 hr): 117 kt
Cruise speed 55% power (w/ reserve 7.7 hr): 110 kt
Max cruise speed: 125 kt
Range: 591 nm
Fuel consumption, 75%: 8.5 USgph
Vs: 55 kt
Vso: 46 kt
Best rate of climb: 670 fpm
Service ceiling: 12,700 ft
Takeoff ground roll: 845 ft
Takeoff over 50-ft. obstacle: 1575 ft
Landing ground roll: 400 ft
Landing over 50-ft. obstacle: 1135 ft

CE-177B
Engine: Lycoming, 180 hp.
Prop: Fixed pitch.
Undercarriage: Fixed tricycle.
Seating Capacity: 4.
Fuel Capacity: 61 US Gal.
Max Level Speed; 139 kts / 160 mph.
Cruise 75% power; 130 kts / 150 mph.
Stall; 46 kts / 53 mph.
Max Range; 675 nm / 776 sm.
Fuel 65% power; 7.6 US Gal/hr.
Best Rate of Climb: 840 fpm.
Service Ceiling; 14,600 ft.
Take-off 50ft; 1,400 ft
Landing 50ft; 1,220 ft
Useful load; 875 lbs.
Power loading; 13.9 lbs / hp.
Wing Loading; 14.5 lbs / sq.ft.
Wing span: 35 ft 6 in.
Length: 26 ft 11.5 in.
Height: 9 ft 1in.
Empty wt: 1430 lbs.
Max wt: 2500 lbs
Baggage cap: 120 lbs.

1977 CE-177 Cardinal
Engine: 1 x Lycoming O-360-A1B6D, 200 hp.
TBO: 2000 hr
Propeller: Const. spd.
Wingspan: 35 ft. 6 in.
Wing area: 259 sq. ft
Overall length: 27 ft. 3 in.
Height: 8 ft. 7 in.
Wing loading: 14.4 lb/sq.ft.
Pwr loading: 13.9 lb/hp.
Gross wt: 2500 lb.
Empty wt: 1533 lb.
Equipped useful load: 903 lb.
Payload max fuel: 543 lb.
Fuel: 49 USgal
Fuel cap: 294/360 lb.
Range max fuel/75% pwr: 698nm/5.3hr.
Range max fuel / 55% pwr: 812 nm/ 7.5 hr.
Fuel consumption 75% power: 10.1 USgph
Fuel consumption 65% power: 8.6 USgph
Estimated endurance (65% power with 1-hr. reserve): 3 hrs. 54 mins.
Cabin width: 48 in
Cabin height: 46.5 in
Baggage capacity: 120 lb
Service ceiling: 14,600 ft.
75% cruise: 130 kt.
55% cruise: 109 kt.
Stall: 40-52 kt.
1.3 Vso: 52 kt.
Best rate of climb: 840 fpm
Min field length: 1400 ft
Takeoff ground roll: 750 ft
Landing ground roll: 600 ft
Seats: 4.
Undercarriage: fixed tricycle

Cessna Cardinal RG
Engine: 1 x Avco Lycoming IO-360-A1B6D, 149kW, 200hp
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: CS/two-blade
Max ramp weight: 2800 lb
Max Take-off weight: 1270 kg / 2800 lb
Empty weight: 772 kg / 1702 lb
Landing weight: 2800 lb
Useful fuel, std: 60 USgal
Fuel consumption 75% power: 10.5 USgph
Fuel consumption 65% power: 9.1 USgph
Wingspan: 10.82 m / 35 ft 6 in
Length: 8.31 m / 27 ft 3 in
Height: 2.62 m / 8 ft 7 in
Wing area: 16.16 sq.m / 173.94 sq ft
Wing loading: 16.1 lbs./sq.ft
Power loading: 14.0 lbs.hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 48 in
Cabin height: 44.5 in
Max. speed: 274 km/h / 170 mph
Cruise speed: 224 km/h / 139 mph
Service ceiling: 5210 m / 17100 ft
Max range (w/reserve) 75% power: 715 nm
Max range (w/reserve) 45% power: 895 nm
Vso: 50 kts
Best rate of climb: 925 fpm
Takeoff ground roll: 890 ft
Takeoff over 50-ft obstacle: 1585 ft
Landing ground roll: 730 ft
Landing over 50 ft obstacle: 1350 ft
Landing gear type: Tri./Retr.

In 1958 Cessna brought into production the Model 175. This was in effect the latest version of the Model 172 with a number of improvements (free-blown windscreen, glassfibre speed fairings, etc) and a 131kW GO-300-C geared engine driving a constant-speed propeller. In 1959 a de luxe version of the Model 175A was introduced as the Skylark, but the Model 175 / Skylark type was dropped from production in 1963.

In 1964 the Franklin Engine company or Syracuse, NY, offered a 180 hp Franklin engine conversion with a compact cowl and trim spinner. This gave significant increases in speed, rate of climb and glide ratio. Conversions could be done in the field or factory.

1960 Cessna 175 Skylark
Engine: Continental O-300C, 175 hp @3200@SL
TBO: 1200 hr
Fuel Type: 100/100LL
Propeller: Fixed 76-inch
Landing Gear type: Tri/Fixed
Max ramp weight: 2350 lb
Gross weight: 2350 lb
Landing weight: 2350lb
Empty weight, std: 1325 lb
Useful load, std: 1025 lb
Useful load, as equiped: 877 lb
Payload, full std. fuel: 767 lb
Usable fuel, std: 43 USgal
Wingspan: 36 ft.
Overall length: 25 ft.
Height: 8 ft. 5 in.
Wing area: 174 sq. ft
Wing loading: 13.5 lbs./sq. ft
Power loading: 13.4 lbs./hp
Wheel track:8 ft. 4 in.
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 40 in
Cabin height: 44 in
Baggage capacity:120 lb
Cruise speed 75% power @ 7,500 ft.: 122 kt
Max range (w/ reserve): 75% power: 417 nm
Fuel consumption (@ .48 lbs./hp/hr sfc) 75% power: 10.5
Fuel consumption (@ .48 lbs./hp/hr sfc) 65% power: 9.1
Fuel consumption (@ .48 lbs./hp/hr sfc) 55% power: 7.7
Vso: 44 kt
Best rate of climb (SL): 850 fpm
Service ceiling: 15,900 ft
Takeoff ground roll: 735 ft
Takeoff over 50-ft. obstacle: 1340 ft
Landing ground roll: 590 ft
Landing over 50-ft. obstacle: 1155 ft

1960 Cessna 175A Skylark
Engine: Lycoming 0-320 B-2A, 160-hp
TBO: 2000 hr
Fuel type:100 LL
Propeller: Sensenich 74 DM-0-60/74
Landing gear type: Tricycle steel spring Cessna’s Land-O-Matic with steerable nosewheel
Max ramp weight: 2350 lb
Gross weight: 2350 lb
Landing weight: 2350 lb
Empty weight, std: 1338 lb
Useful load: 980 lb
Usable fuel – std: 42 USgal
Payload, full std. fuel: 712.9 lb
Wingspan: 36 ft.
Overall length: 26 ft. 6 in.
Height: 9 ft. 6 in.
Wing area:175 sq. ft
Wing loading: 14.1 lbs./sq. ft
Power loading: 13.4 lbs./hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 40 in
Cabin height: 48 in
Baggage capacity: 120lb
Cruise speed: 107 kts
Cruise speed, 75% power: 105 kt
Max range (w/ reserve): 489 nm
Fuel consumption: 8.5 to 9.0 USgph
Vs: 54kt
Vso: 46 kt
Best rate of climb: 800 fpm
Best rate of climb at 8000 ft: 400 fpm
Service ceiling: 15,900 ft
Takeoff ground roll: 842 ft
Takeoff over 50-ft. obstacle: 495 ft
Landing ground roll (ft.): 600
Landing over 50-ft. obstacle: 1175 ft

Cessna took a model 170B, gave it a tricycle undercarriage and a new squared fin and rudder, and called it a model 172. First built in 1955, the 172 entered production in 1956. In 1956 some 1,170 Model 172s were sold, compared with 174 of the Model 170B, whose production was terminated.

Cessna CE-172 / T-41 Article

A new swept fin and rudder introduced in 1960 gave the CE-172A, followed by the near identical 1961 172B (989 produced) and 1962 172C. The Skyhawk version of this airplane appeared in 1961, with a complete paint job, gyro panel powered by an internal vacuum system, and speed fairing on the wheels. The “economy” 172 was been available each year since, although the Skyhawk accounted for most of the sales. The “omnivision” windows produced the 172D in 1963, a new engine in 1968 (150 hp Lycoming O-320-E2D), conical wingtips in 1970, tubular steel gear legs in 1971; new wing with modified aerofoil in 1973 for improved slow-flight characteristics, through to the 172P. A shorter nose strut gave improved vision over the nose for taxiing from in 1967. The Clark Y airfoil section was introduced for its propeller in 1974, and a quieter cabin with slightly re-shaped rudder in 1976.

A more luxurious version was marketed as the Skyhawk II.

The 1977 Cessna Skyhawk/100 was powered by a 100 octane engine a 160 hp Lycoming O 360 H is 10 horsepower stronger, cruises two knots faster and burns slightly less fuel than the old Skyhawk.
The Hawk XP (extra-performance) was first introduced by Reims Aviation in France (as the Reims Rocket). Based on the 172N but with a more powerful motor and different colour, which were about the sole distinguishing features. Introduced in the US in 1977 as the R172K Hawk XP.

The Hawk XP’s engine is basically the same as that used in the Cessna 337, where it is rated at 210 hp. What happened to 15 of its horses? They are still in there, but FAA noise standards preclude their use the Hawk XP’s engine turns 2,600 rpm for take-off instead of the 2,800 that is the norm on the 337.
The airframe is identical to the Skyhawk’s from the firewall aft. There are some differences inside. A prop control, cowl flap control and rudder trim have been added. Preselect for the flaps is standard on the Hawk XP, and the fuel selector arrangement is slightly different from the Skyhawk’s. For fuel, the Hawk XP has as standard, tanks that are offered as optional long range tanks in the Skyhawk, 49 USG of usable fuel.
In 1982 the 180 horsepower Hawk XP became the 172Q Cutlass, though differing greatly from the retractable undercart 172RG which was also marketed as the Cutlass. Introduced in 1980 the 172RG Cutlass used the same retractable undercarriage system already in use in the models R182 and 210. The new Cutlass was designed to appeal to businessman who wanted a model 172 with a higher cruising speed.

Versions available in 1982 included the Model 172 Skyhawk and Skyhawk II, the Cutlass RG and Cutlass RG II which is basically a Model 172 with retractable landing gear.

The Model 172 also appealed to the US military and in July 1964 the US Air Force ordered 170 standard Cessna 172Fs powered by 134kW Continental O-360 engines for the Air Academy, and these were designated T-41A. To be used for the first 30 hours of flight instruction the unit cost was $7292. Deliveries began in September 1964.

In August 1966, the US Army bought 255 Model R172Es fitted with the more powerful 157kW IO-360D fuel injection engine, as the T-41B Mescalero. These were followed by similarly powered T-41Cs for the US Air Force, and export version, designated T-41D, for a number of other air forces under the Mutual Air Programme. Total production of the military T-41 series reached 864 built between 1963-83.

A large number of older 172s have been up-graded by an Avcon conversion to 180 hp. A 180hp Lycoming O 360 Superhawk conversion results in an increase in cruise speed by 12 knots, reduces takeoff roll by some 50 percent and improves the rate of climb by 100 percent. Payload is increased by 120 lbs.
Both the S and R models are fitted with the same Lycoming 180-horsepower fuel injected engine, but the 172R is de-rated to operate at a lower RPM with a slightly smaller propeller, and so produces 160 horsepower. As a result the 172S can carry a higher payload but the higher horsepower engine uses more fuel and consequently range suffers although other performance characteristics (at maximum all up weight) are similar. The first 172R was delivered on 18 January 1997.

Cessna CE-172S Pilot’s Operating Handbook & Flight Manual

In the air the Skyhawk SP handling is similar to other models of 172, although you definitely notice the extra horsepower when four are on board and baggage and fuel are up to the allowable limits. The increased acceleration on take off, while slight, is also noticeable. The increased performance allows a better short field performance, and flight is quiet and comfortable thanks to increased attention paid to soundproofing in the cabin. The CE-172SP Skyhawk comes with leather seats and trim.

The FAA and the European Aviation Safety Agency (EASA) certified the Cessna Turbo Skyhawk JT-A with next-generation Garmin G1000 NXi avionics after more than five years of development.

Manufacturer Textron Aviation in Wichita, Kansas said the new model, equipped with the Continental CD-155 turbodiesel engine, has exceeded initial performance targets including improved maximum range. The Turbo Skyhawk JT-A is a factory option that includes an integrated powerplant, propeller and cockpit upgrade package.

Final performance figures include an improved range of 963 nautical miles, an increase of 78 nautical miles over original estimates and a 50 percent improvement over the gasoline-powered Skyhawk, a takeoff distance of 1,320 feet and a max climb rate of 767 feet per minute. Max speed is 134 knots.

The 155 horsepower turbodiesel Continental CD-155 includes direct fuel injection and a dual channel Fadec driven by a single power lever for around $450,000 in 2017.

Gallery

1957 Cessna 172
Engine: Continental O-300, 145 hp
TBO: 1800 hrs
Fuel Type: 100/100LL
Propeller: McCauley/Fixed
Landing Gear type: Tri/Fixed
Max ramp weight:2200 lb
Gross weight: 2200 lb
Landing weight:2200 lb
Empty weight, std: 1260 lb
Usable fuel: 37 USgals
Wingspan: 35 ft.
Overall length: 25 ft.
Wing area:159 sq. ft
Wing loading: 13.8 lbs./sq. ft
Power loading: 15.2 lbs./hp
Wheel size: 6 in.
Seating capacity: 4
Cabin doors: 2
Cabin width: 44 in
Baggage capacity:50 lb
Cruise speed 75% power: 108 kts
Cruise speed 65% power: 101 kts
Cruise speed 45% power: 98 kts
Max range (w/ reserve) 75% power: 395 nm
Max range (w/ reserve) 65% power: 420 nm
Max range (w/ reserve) 45% power: 440 nm
Fuel consumption 75% power: 8.0 USgph
Fuel consumption 65% power: 7.5 USgph
Fuel consumption 45% power: 7.1 Usgph
Estimated endurance (65%) (hrs): 3.9
Stall speed (flaps up): 54 knots
Stall speed (flaps down):50 knots
Best rate of climb: 660 fpm
Service ceiling: 13,300 ft
Takeoff ground roll: 950 ft
Landing ground roll: 600 ft

1958 Cessna 172 Skyhawk
Engine: Continental O-300A, 145 hp@SL
TBO: 1800 hrs
Fuel type: 80/100/100LL
Propeller type: Fixed pitch
Landing gear type: Tri./Fixed
Max ramp weight:2200 lb
Gross weight: 2200 lb
Landing weight:2200 lb
Empty weight, std: 1260 lb
Usable load, std: 940 lb
Payload, full std. fuel: 688 lb
Usable fuel, std: 42 USgal
Wingspan: 36 ft.
Overall length: 25 ft.
Height: 8 ft. 5 in.
Wing area:174 sq. ft
Wing loading: 12.6 lbs./sq. ft
Power loading: 15.2 lbs./hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 40 in
Cabin height: 45 in
Cruise speed 75% power: 108 kt
Fuel consumption: 8 USgph
Vso: 50 kt
Best rate of climb, SL:660 fpm
Service ceiling: 13,300 ft
Takeoff ground roll: 950 ft
Takeoff over 50-ft. obstacle:1650 ft
Landing ground roll: 600 ft
Landing over 50-ft. obstacle: 1115 ft

Cessna Skyhawk 172
Engine: Continental O-300C, 145 hp@SL
TBO: 1800 hrs
Fuel Type: 80/87
Propeller: McCauley FP/76
Landing gear type: Tri/Fixed
Max ramp weight:2200 lb
Gross weight: 2200 lb
Landing weight: 2200 lb
Empty weight, std: 1325 lb
Useful load, std: 875 lb
Payload, full opt. fuel: 623lb
Usable fuel, std: 42 USgal
Wingspan: 36 ft.
Overall length: 26 ft. 6 in.
Height: 8 ft. 11 in.
Wing area:174 sq. ft
Wing loading: 12.6 lbs./sq. ft
Power loading: 15.2 lbs./hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 41 in
Cabin height: 44 in
Baggage capacity: 120lb
Cruise speed 70% power @ 8,000 ft.: 113 kt
Cruise speed 50% power @ 10,000 ft: 87 kt
Stall speed (gear, flaps down): 44 knot
Best rate of climb (SL): 730 fpm
Service ceiling: 15,100 ft
Takeoff ground roll: 780 ft
Takeoff over 50-ft. obstacle:1370 ft
Landing ground roll: 680 ft
Landing over 50-ft. obstacle: 1115 ft

Cessna 172B
Engine: 145hp
TBO: 1800 hr
Fuel type: 100LL
Propeller type: Fixed
Landing gear type: Tri./Fixed
Gross weight: 2200 lb
Empty weight, std: 1325 lb
Useful load, std: 875 lb
Payload, full std. fuel: 623 lb
Useful fuel, std: 42 USgal
Wingspan: 33 ft. 2 in.
Overall length: 26 ft. 5 in.
Height: 8 ft. 6 in.
Wing area:159 sq. ft
Wing loading: 13.8 lbs./sq. ft
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 44 in
Cabin height: 50 in
Baggage capacity:50 lb
Cruise speed 75% power: 114 kt
Cruise speed 65% power: 108 kt
Cruise speed 55% power: 101 kt
Max range (w/ reserve) 75% power: 515 nm
Max range (w/ reserve) 65% power: 542 nm
Max range (w/ reserve) 55% power: 568 nm
Fuel consumption 75% power: 8.0 USgph
Fuel consumption 65% power: 7.5 USgph
Fuel consumption 55% power: 7.0 USgph
Estimated endurance (65%): 5.6 hr
Vs:46 kt
Vso:51 kt
Best rate of climb (SL): 730 fpm
Service ceiling: 15,100 ft
Takeoff ground roll: 875 ft
Takeoff over 50-ft. obstacle:1370 ft
Landing ground roll: 600 ft
Landing over 50-ft. obstacle: 1115 ft

CE-172F
Engine: 145 hp Continental O-300-C
Wingspan: 36 ft 2 in
Length: 26 ft 6 in
Height: 8 ft 11 in
Wing area: 174 sq.ft
Empty weight: 1264 lb
Loaded weight: 2300 lb
Max speed: 138 mph
Cruise 75%: 130 mph
ROC: 645 fpm
Range: 595 mi

CE-172J
Engine: Lycoming, 150 hp.

CE-172M
Engine: Lycoming O-320-E2D, 150 hp.
TBO: 2000 hr
Propeller: Const. spd.
Landing gear type: Tri/Fixed
Gross weight: 2300 lb
Empty weight, std: 1370lb
Useful load, std: 930lb
Fuel: 38 USgal
Wingspan: 35 ft. 10 in.
Overall length: 26 ft. 11 in.
Height: 8 ft. 10 in.
Wing area:174 sq. ft
Seating capacity: 4
Cabin width: 39.5 in
Cabin height: 48 in
Baggage capacity:120 lb
Cruise speed 75% power: 120 kt
Cruise speed 65% power: 115 kt
Max range (w/ reserve) 75% power: 600 nm
Max range (w/ reserve) 65% power: 640 nm
Fuel consumption 75% power: 8.0 USgph
Fuel consumption 65% power: 6.8 USgph
Stall speed (gear, flaps down):43 knot
Best rate of climb: 645 fpm
Service ceiling: 13,100 ft
Takeoff ground roll: 865 ft
Landing ground roll: 520 ft

CE-172N Skyhawk
Engine: Lycoming O 320 H2AD, 160 hp.
TBO: 2,000 hrs.
Prop: fixed pitch, 75 in. dia.
Length: 26 ft. 11 in.
Height: 8 ft. 9 in.
Wingspan: 35 ft. 10 in.
Wing area: 174 sq.ft.
Wing loading: 13.2 lb/sq.ft.
Power loading: 14.4 lb/hp.
Seats: 4.
Empty weight: 1,589 lb.
Useful load: 711 lb.
Payload with full fuel: 411 lbs.
Max ramp wt: 2,307 lbs
Gross weight: 2,300 lb.
Usable fuel capacity: 50 USG/300 lbs.
Maximum rate of climb: 770 fpm.
Service ceiling: 14,200 ft.
Maximum speed: 125 kts.
Max cruise, 75% power (2,650 rpm) at 8,000ft: 122 kts.
Econ cruise, 61 % power (2,500 rpm) at 10,000 ft: 114 kts.
Duration at max cruise: 5.3 hrs.
Duration at econ cruise: 7.1 hrs.
Max range: 750 nm.
Stalling speed, clean: 50 kts.
Stalling speed, full flaps: 44 kts.
Takeoff dist 50ft obstacle: 1,440 ft.
Landing dist 50ft obstacle: 1,250 ft.

CE-172P
Engine: 1 x Lycoming O-320-D2J, 160 hp.
TBO: 2000 hrs.
Prop: McCauley 2 blade, fixed pitch 72 in.
Seats: 4.
Length: 26.9 ft.
Height: 8.8 ft.
Wingspan: 35.8 ft.
Wing area: 174 sq.ft.
Wing aspect ratio: 7.4.
Max ramp wt: 2407 lbs.
Max take off wt: 2400 lbs.
Standard empty wt: 1427 lbs.
Max useful load: 980 lbs.
Max landing wt: 2400 lbs.
Wing loading: 13.8 lbs/sq.ft.
Power loading: 15 lbs/hp.
Max useable fuel: 372 lbs.
Climb rate: 700 fpm @ 76 kts.
Climb gradient: 555 ft/nm.
Rate of climb @ 8000 ft: 330 fpm.
Service ceiling; 13,000 ft.
Max speed: 123 kts.
Cruise @ 65% power @ 8,000ft: 112 kts.
Fuel flow @ 65% power @ 8,000ft: 46 pph.
Endurance @ 65% power @ 8,000ft: 7.8 hr
Stalling speed clean: 51 kts.
Stall speed flaps down: 46 kts.
Turbulent air penetration speed: 99 kts.
Fixed undercarriage.

CE-172 Hawk XP
Engine: Teledyne Continental IO 360 K, 195 hp.
TBO: 2,000 hrs.
Prop: constant speed, two blade, 76 in.
Length: 27 ft. 2 in.
Height: 8 ft. 10 in.
Wingspan: 36 ft.
Wing area: 174 sq. ft.
Wing loading: 14.7 lb/sq.ft.
Power loading: 13.1 lb/hp.
Seats: 4.
Useful load: 932 lb.
Payload with full fuel: 638 lbs.
Gross weight: 2,550 lbs.
Max ramp wt: 2,558 lbs.
Usable fuel: 49 USG/294 lbs.
Max usable fuel: 66 USG
Maximum rate of climb: 870 fpm.
Service ceiling: 17,000 ft.
Max speed: 133 kts.
Max cruise, 80% power (2,550 rpm) at 6,000 ft: 130 kts.
Cruise 75% power; 129 kts / 149 mph.
Econ cruise, 50 % power, 10,000 ft: 101 kts.
Duration at max cruise: 4.2 hrs.
Duration at econ cruise: 6.5 hrs.
Max Range; 635 nm / 731 sm.
Fuel 65% power; 9.0 US Gal/hr.
Stalling speed, clean: 53 kts.
Stall speed, full flap: 46 kt.
Undercarriage; Fixed tricycle.
Seats: 4.
Take-off 50ft; 1,360 ft.
Landing 50ft; 1,345 ft.

CE-R172K Hawk XP
Engine: Teledyne-Continental IO-360-K, 195 hp.
Prop: CS 76”.
Max wt: 2550 lbs.
Useful load: 1001 lbs.
Max speed: 134 kts.
Cruise (80% pwr @ 5500 ft): 131 kts.
Range @ 80% pwr: 485 nm.
Max range: 595 nm.
ROC sl: 870 fpm.
T/O 50ft: 1360 ft.
Ldg 50 ft: 1270 ft.
Stall: 46-53 kts.
Fuel cap: 52 USG.

Cessna 1998 172SP Skyhawk
Engine: Lycoming IO-360-L2A, 180 hp
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: McCauley Fixed
Landing gear type: Tri/Fixed
Max ramp weight: 2558 lb
Gross weight: 2550lb
Empty weight, std: 1650 lb
Landing weight: 2550 lb
Useful load, std: 900 lb
Payload, full std. fuel: 577 lb
Usable Fuel: 53 USgal
Wingspan: 36 ft. 1 in.
Overall length: 26 ft. 11 in.
Height: 8 ft. 11 in.
Wing area: 175.5 sq. ft
Wing loading: 14.7 lbs./sq. ft
Power loading: 14.2 lbs./hp
Seating capacity: 4
Cabin doors: 2
Cabin width: 39.5 in
Cabin height: 48 in
Baggage capacity: 120 lb
Cruise speed 75% power @ 8,000 ft: 124kt
Cruise speed 65% power @ 12,000 ft: 119 kt
Cruise speed 45% power @ 12,000 ft: 109 kt
Max range (w/ reserve) 75% power: 475 nm
Fuel consumption 75% power: 9.5 gph
Fuel consumption 65% power: 8.6 USgph
Fuel consumption 55% power: 7.3 USgph
Estimated endurance (65% power with 1-hr. reserve): 5 hrs. 30 mins.
Stall speed (gear, flaps down) (s): 47 knot
Best rate of climb: 820 fpm
Service ceiling: 14,000 ft
Takeoff ground roll: 810 ft
Landing ground roll: 550 ft
Takeoff over 50-ft. obstacle:1630 ft
Landing over 50-ft. obstacle: 1335 ft
Wheel size: 6.00 x 6 in

CE-172RG
Engine: 1 x Lycoming O-360-F1A6, 180 hp.
TBO: 2000 hrs.
Prop: McCauley 2 blade, constant speed 76.5 in.
Seats: 4.
Length: 27.4 ft.
Height: 8.8 ft.
Wingspan: 35.8 ft.
Wing area: 174 sq.ft.
Wing aspect ratio: 7.4.
Max ramp wt: 2658 lbs.
Max take off wt: 2650 lbs.
Standard empty wt: 1591 lbs.
Max useful load: 1067 lbs.
Max landing wt: 2650 lbs.
Wing loading: 15.2 lbs/sq.ft.
Power loading: 14.7 lbs/hp.
Max useable fuel: 62 USG/372 lbs.
Climb rate: 800 fpm @ 84 kts.
Climb gradient: 581 ft/nm.
Rate of climb @ 8000 ft: 465 fpm.
Service ceiling: 15,200 ft.
Max speed: 145 kts.
Cruise @ 65% power @ 8,000ft: 129 kts.
Fuel flow @ 65% power @ 8,000ft: 53 pph.
Endurance @ 65% power @ 8,000ft: 6.8 hr.
Cruise, 75% power at 6,000 ft, (23 inches and 2,500 rpm): 136 kts.
Fuel flow at 75 % power: 10 gph.
Endurance at 75% power, no res: 6 hrs.
Stalling speed clean: 54 kts.
Stall speed flaps down: 50 kts.
Turbulent air penetration speed: 106 kts.
Retractable nose wheel undercarriage.

Avcon 180 CE-172
Engine: 1 x Lycoming O-360-A1A, 180 hp.
Prop: CSU.
Seats: 4.
Wing loading: 13.1 lb/sq.ft.
Pwr loading: 12.8 lb/hp.
Max TO wt: 2300 lb.
Empty wt: 1289 lb.
Equipped useful load: 946 lb.
Payload max fuel: 718 lb.
Range max fuel / 75% cruise: 523 nm/3.2 hr.
Service ceiling: 19,500 ft.
75% cruise: 134 kt.
Cruise (23in x 2400 rpm): 113 kts.
Stall: 42-50 kt. 1.3
Vso: 55 kt.
ROC: 1100 fpm.
Min field length: 500 ft.
Fuel cap: 228 lb.

Cut¬lass II
Engine Avco Lycoming O 360 A4N, 180 hp.
Prop McCauley, 2 blade, fixed pitch, 76 in. dia.
TBO 2,000 hrs.
Length 26.9 ft.
Height 8.9 ft.
Wingspan 36 ft.
Wing area 174 sq. ft.
Max ramp weight 2,558 lbs.
Max takeoff weight 2,550 lbs.
Standard empty weight 1,513 lbs.
Max useful load 1,045 lbs.
Max landing weight 2,550 lbs.
Wing loading 14.7 lb/sq.ft.
Power loading 14.2 lb/hp.
Max usable fuel 62 USG/372 lbs.
Max rate of climb, sea level 730 fpm.
Max rate of climb, 8,000 ft 405 fpm.
Max operating altitude 17,000 ft.
Max speed at sea level 124 kts.
Cruise, 75% power at 8,000 ft. 122 kts.
Fuel flow at 75% power 10.1 USG/hr.
Endurance at 75% power, no reserve 6.1 hrs.
Stalling speed, clean 50 kts.
Stalling speed, flaps down 40 kts.
Turbulent air penetration speed 105 kts.

CE-172Q II
Engine: 1 x Lycoming O-360, 180 hp.

Cessna 1997 172R Skyhawk
Engine: Lycoming IO-360-L2A, 160 hp
TBO: 2000 hr
Fuel type:100/100LL
Propeller: Fixed McCauley 2 blade 75 in
Landing gear type: Tri/Fixed
Max ramp wt: 2457 lb
Gross weight: 2457 lb
Landing weight: 2450 lb
Empty weight, std: 1600 lb
Useful load, std: 857 lb
Useable fuel: 53 USgal
Wingspan: 36 ft.
Overall length: 26 ft. 11 in.
Height: 8 ft. 11 in.
Wing area:175.5 sq. ft
Wing loading: 14.1 lbs./sq. ft
Power loading: 15.4 lbs./hp
Seating capacity: 4
Wheel size: 6.00 x 6 in
Cabin doors: 2
Cabin width: 39.5 in
Cabin height: 48 in
Baggage capacity: 120 lb
Cruise speed 75% power: 122 kt
Cruise speed 65% power: 116 kt
Max speed SL: 123 kt.
Vne: 163 kt.
Vno: 129 kt.
Max range (w/ reserve) 75% power: 580 nm
Max range (w/ reserve) 65% power: 615 nm
Fuel consumption 75% power: 9.2 USgph
Fuel consumption 65% power: 8.1 USgph
Estimated endurance (65% power with 1-hr. reserve): 5 hrs. 30 mins.
Stall speed (gear, flaps down): 47 knot
Best rate of climb: 720 fpm
Service ceiling: 13,500 ft
Takeoff ground roll: 945 ft
Landing ground roll: 550 ft
Takeoff over 50 ft. obstacle: 1685 ft
Landing over 50 ft. obstacle: 1295 ft

2006 Cessna 172S Skyhawk SP
Engine: Lycoming IO-360-L2A, 180 hp@SL
TBO: 2000 hr
Fuel type:100/100LL
Propeller: 76 in. McCauley
Landing gear type: Tri./Fixed
Max ramp weight: 2558 lb
Gross weight: 2550 lb
Landing weight: 2550 lb
Empty weight, std: 1663 lb
Useful load, std: 895 lb
Payload, full std. fuel: 577 lb
Useful fuel, std: 53 USgal
Wingspan: 36 ft. 1 in.
Overall length: 27 ft. 2 in.
Height: 8 ft. 11 in.
Wing area: 174 sq. ft
Wing loading: 14.7 lbs./sq. ft
Power loading: 14.2 lbs./hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 40 in
Cabin height: 48 in
Cruise speed @ 8500 ft: 75% power: 124kt
Max range (w/45 min. reserve) 75% power: 516 nm
Max range (w/45 min. reserve) 45% power: 638 nm
Vso: 48 kt
Best rate of climb (SL): 730 fpm
Max operating altitude: 14,000 ft
Takeoff ground roll: 960 ft
Takeoff over 50-ft. obstacle:1630 ft
Landing ground roll: 575 ft
Landing over 50-ft. obstacle: 1335 ft

2009 Cessna Skyhawk 172S
Engine: Lycoming IO-360-L2A, 180 hp@SL
TBO: 2000 hr
Fuel type: 100LL
Propeller t: FP McCauley
Landing gear type: Tri./Fixed
Gross weight: 2558 lb
Max takeoff weight: 2550 lb
Empty weight, std: 1717 lb
Useful load, std: 841/833 lb
Usable fuel, std: 53 Usgal / 318 lb
Payload, full std. fuel: 523lb
Wingspan: 36 ft. 1 in.
Overall length: 27 ft. 2 in.
Overall height: 8 ft. 11 in.
Wing area: 174 sq. ft
Wing loading: 14.7 lbs./sq. ft
Power loading: 14.2 lbs./hp
Baggage capacity: 30 cu. ft
Seating capacity: 4
Cabin doors: 2
Cabin width: 39.5 in
Cabin height: 48 in
Vso: 47 kt
Best rate of climb, SL: 730 fpm
Service ceiling: 14,000 ft
Cruise speed 75% power : 126 kt
Fuel consumption, 75% power (gph): 9.7
Takeoff ground roll: 945 ft
Takeoff over 50 ft. obstacle: 1633 ft
Landing ground roll: 550 ft
Landing over 50 ft. obstacle: 1335 ft

Reims Cessna F.172M

Reims Cessna FR.172 Rocket

CE-172 (Floatplane)
Engines: Lycoming, 150 hp.
Wing span: 35 ft 10 in (10.92 m).
Length: 27 ft 0 in (8.23m).
Height: 9 ft 11 in (3.02 m).
Max TO wt: 2220 lb (1007 kg).
Max level speed: 108 mph (174 kph).

Cessna T-41 Mescalero
Engine: 1 x 108kW (145hp) Continental O-300-C
Propeller: 2-blade fixed pitch.
Maximum Speed: 139mph / 224kmh / 121kts
Maximum Range: 640miles (1,030km)
Rate-of-Climb: 645ft/min (197m/min)
Service Ceiling: 16,995ft (5,180m)
Accommodation: 2 + 2

The Cessna 170 first appeared on the American market in 1948 as a four-seat version of the earlier all-metal two-seat Cessna 120 and the four-seat Cessna 140. The 140, which had been lengthened, had extra windows fitted as well as having an electric starter motor installed. The first 170 had a fabric-covered wing, two wing struts on each side, and a vertical tail.

Metal covered wings, and one wing strut in place of two and a new dorsal fin, were introduced on the 1949 model 170A, and the model was improved in 1952 as the all-metal 170B (2,907 built) with L-19 type flaps, followed later by the CE-170C.

The 1953 CE-170B featured a number of new features including a redesigned and lengthened engine cowl. The 1955 version featured enlarged rear windows, an additional flap position (10 degrees) and revised tailwheel steering.

In 1955 the company developed the Model 172, which was essentially a Model 170B with detail improvements and the tailwheel landing gear replaced by a spatted tricycle unit.

The 170’s 145-hp Continental delivers 65 percent power at 5,000 feet pressure altitude turning 2,450 rpm, and produces 120 mph true using only eight USG per hour. Since later model Cessnas, with a similar engine, cruise at 2700 rpm, the 170’s recommended cruise setting should extend engine life.

In 1956 some 1,170 Model 172s were sold, compared with 174 of the Model 170B, whose production was terminated.

By the time production ceased in 1957, 5,174 Cessna 170s had been built.

Gallery

170B
Engine: Continenal O-300, 145 hp@2700@SL
TBO: 1800 hrs
Fuel type: 80/87 Autogas STC
Propeller: McCauley two-blade fixed
Max ramp weight:2200lb
Gross weight: 2200 lb
Landing weight: 2200 lb
Empty weight, std: 1220 lb
Useful load, std: 980 lb
Payload, full std. fuel: 728 lb
Usable fuel: 37 USgal
Wingspan: 36 ft.
Overall length: 25 ft.
Height: 6 ft. 5 in.
Wing area:174.6 sq. ft
Wing loading: 12.6 lbs./sq. ft
Power loading: 15 lbs./hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 40 in
Cabin height: 48 in
Baggage capacity:120lb
Cruise speed 75% power @ 5,000 ft: 114kt
Cruise speed 65% power @ 7,500 ft: 109 kt
Cruise speed 55% power @ 7,500 ft: 102 kt
Vne: 160 mph.
Max range (w/ reserve) 75% power: 325 nm
Max range (w/ reserve) 65% power: 376 nm
Max range (w/ reserve) 55% power: 437 nm
Fuel consumption 75% power: 9.6 USgph
Fuel consumption 65% power: 8.3 USgph
Fuel consumption 55% power: 7.0 USgph
Estimated endurance (65%): 3.7 hr
Stall speed (flaps up): 50knot
Stall speed (flaps down):45 knots
Best rate of climb (SL): 660 fpm
Service ceiling: 14,000 ft
Takeoff ground roll: 650 ft
Landing ground roll: 460 ft

1976 CE-170B
Engine: 145 hp Continental C145-2
Wingspan: 36 ft 0 in
Length: 24 ft 11.5 in
Height: 6 ft 7 in
Wing area: 174 sq.ft
Empty weight: 1205 lb
Loaded weight: 2200 lb
Max speed: 143 mph
Cruise: 75%: 121 mph
ROC: 690 fpm
Service ceiling: 15,500 ft
Normal range: 590 mi

In 1977 the Cessna 150 range was replaced on the production lines by the basically similar Cessna Model 152. It was introduced with the intention of providing an airplane that burns 100-octane fuel with lower sound levels, better fuel consumption, and an increased payload. The Lycoming “Blue Streak” O-235 engine produces 81kW / 110-hp at a low 2,500 rpm, plus installation and a one piece upper cowling changes to reduce engine noise and vibration, together with a McCauley propeller of a modified blade section. A marked improvement is the increase in maximum useful load by over 100 pounds to 589. With full fuel, the 152 has 433 pounds of payload for people, baggage, and/or accessories. Contributing to the useful load is an unusable fuel quantity of only 1-1/2 gallons. Cessna’s 69-inch prop teams with the derated engine to produce more efficient climb and cruise performance at a reduced RPM. There’s also a 28 volt electrical system.

The 152 Aerobat is also available. It meets requirements for aerobatic maneuvers of 6Gs positive and 3Gs negative load. The an improvement included a system that injects fuel evenly into all four cylinders for prompt ignition and even combustion. With the 152’s optional fuel tanks, it can cover 794 miles while traveling at 122 mph at 7,000 feet and carrying a useful load of 1,101 pounds. Cessna offered a training version for the first time in 1981; the Trainer included a package price for the most frequently ordered avionics and accessories for training purposes. Main gear tires are 15-6.00 x 6 to reduce frontal area and save weight.
Spinning is approved in both the standard and aerobatic models.
Between 1977 and 1986 the aircraft was available in four versions; the standard Model 152, the slightly heavier Model 152 II with a package of factory installed avionics and omni-directional light beacon, the further improved Model 152 Trainer with other improvements including an intercom system and transponder, and the Model 152 Aerobat with the same aerobatic capabilities as the 150 Aerobat. When production ceased in 1986, 7,482 Model 152 and Aerobats had been produced including 640 built under licence in France by Reims Aviation.

Cessna 152 Operator Handbook

Reims Aviation in France built 89 FA152 Aerobats for the European market, similiar to the 315 that Cessna produced.
Custom Aircraft Conversions of Texas provide a bolt on conversion to tail wheel configuration. The tail cone is beefed up with an inner sleeve, the same main gear, leaf or tube, is retained, and a Scott tailwheel is fitted. It was claimed that the cruise improved by 9 mph and the rate of climb by 65 fpm.

Gallery

Model 152 Standard
Engine: 1 x Avco Lycoming O-235-N2C, 81kW
Max Take-off weight: 757 kg / 1669 lb
Empty weight: 501 kg / 1105 lb
Wingspan: 9.97 m / 32 ft 9 in
Length: 7.34 m / 24 ft 1 in
Height: 2.59 m / 8 ft 6 in
Wing area: 14.59 sq.m / 157.05 sq ft
Max. speed: 202 km/h / 126 mph
Ceiling: 4480 m / 14700 ft
Range: 1158 km / 720 miles

CE-152
Engine: 1 x Lycoming O-235-L2C, 110 hp.
TBO: 2000 hrs.
Prop: McCauley 2 blade, fixed pitch 69in.
Length: 24.1 ft.
Height: 8.1 ft.
Airfoil: NACA 2412.
Wingspan: 33.2 ft.
Wing area: 160 sq.ft.
Wing aspect ratio: 6.7.
Max ramp wt: 1675 lbs.
Max take off wt: 1670 lbs.
Standard empty wt: 1112 lbs.
Max useful load: 563 lbs.
Max landing wt: 1670 lbs.
Wing loading: 10.5 lbs/sq.ft.
Power loading: 15.2 lbs/hp.
Fuel capacity (standard): 26 USG/156 lbs.
Fuel capacity (optional): 39 USG /234 lbs.
Climb rate: 715 fpm @ 67 kts.
Climb gradient: 649 ft/nm.
Rate of climb @ 8000 ft: 380 fpm.
Service ceiling; 14,700 ft.
Max speed: 110 kts.
Max cruise speed (75% @ 8,000 ft): 107 kt.
Range @ max cruise (45 min res): 350 nm.
Duration @ max cruise (no res): 4.2 hrs.
Cruise @ 65% power @ 8,000ft: 95 kts.
Fuel flow @ 65% power @ 8,000ft: 31 pph.
Endurance @ 65% power @ 8,000ft: 6.8 hr.
Economy cruise (45% @ 10,000 ft.): 80 knots.
Range @economy cruise (45 min res): 415 nm.
Stalling speed clean: 48 kts.
Stall speed flaps down: 43 kts.
Turbulent air penetration speed: 104 kts.
Fixed undercarriage.
Max X-wind: 12 kt.
Max range: 690 nm.
Takeoff dist. 50 ft obstacle: 1340 ft.
Landing dist 50 ft. obstacle: 1,200 ft.
Seats: 2.
Baggage capacity: 120 lbs.

CE-A152 Aerobat
Engine: Lycoming O-235-L2C, 110 hp.
TO dist: 725 ft.
ROC: 715 fpm.
Cruise: 107 kt.
Useful load: 589 lb.