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Cessna 172 - Airplane Information

The Cessna 172 Skyhawk is a four-seat, single-engine, high-wing fixed-wing aircraft. First flown in 1955 and still in production, more Cessna 172s have been built than any other aircraft.

Cessna 172
Role: Civil utility aircraft
Manufacturer: Cessna Aircraft Company
First Flight: November 1955
Introduction: 1956
Cost: 172 USD $8,700 (1956) [2], 172R USD $234,500 (2008) [3], 172S USD $283,500 (2008) [4]
Number Built: 43,000+[1]
Developed From : Cessna 170
Variants: T-41 Mescalero

Design and Development

Measured by its longevity and popularity, the Cessna 172 is the most successful mass produced light aircraft in history. The first production models were delivered in 1956 and they are still in production. As of 2008, more than 43,000 had been built. [1] The Skyhawk's main competitors have been the Beechcraft Musketeer and Grumman AA-5 series (neither in production), the Piper Cherokee and, more recently, the Diamond DA40.

The Cessna 172 started life as a tricycle landing gear variant of the taildragger Cessna 170, with a basic level of standard equipment. The first flight of the prototype was in November 1955. The 172 became an overnight sales success and over 1,400 were built in 1956, its first full year of production.

Early 172s were similar in appearance to the 170, with the same straight aft fuselage and tall gear legs, although the 172 had a straight vertical tail while the 170 had a rounded fin and rudder. Later 172 versions incorporated revised landing gear and the sweptback tail which is still in use today.The final aesthetic development in the mid-1960s, was a lowered rear deck that allowed an aft window. Cessna advertised this added rear visibility as "Omni-Vision" . This airframe configuration has remained almost unchanged since then, except for updates in avionics and engines, including the Garmin G1000 glass cockpit in 2005. Production had been halted in the mid-1980s, but was resumed in 1996 with the 160 hp (120 kW) Cessna 172R Skyhawk and was supplemented in 1998 by the 180 hp (135 kW) Cessna 172S Skyhawk SP.



The basic 172 appeared in November 1955 as the 1956 model and remained in production until replaced by the 172A in early 1960. It was equipped with a Continental O-300 145 hp (108 kW) six-cylinder, air-cooled engine and had a maximum gross weight of 2,200 lb (998 kg). Introductory base price was USD$8995 and a total of 4195 were constructed over the five years. [5]


The 1960 model 172A introduced a swept back tail and rudder, as well as float fittings. The price was USD$9450 and 1015 were built. [5]


The 172B was introduced in late 1960 as the 1961 model and introduced a shorter undercarriage, engine mounts lengthened three inches (76 mm) , a reshaped cowling and a pointed propeller spinner.[6] For the first time, the "Skyhawk" name was applied to an available deluxe option package. This added optional equipment included full exterior paint to replace the standard partial paint stripes and standard avionics. The gross weight was increased to 2,250 lb (1,021 kg). [5]


The 1962 model was the 172C. It brought to the line an optional autopilot and a key starter to replace the previous pull-starter. The seats were redesigned to be six-way adjustable. A child seat was made optional to allow two children to be carried in the baggage area. The 1962 price was USD$9895. A total of 889 172C models were produced. [5]


The 1963 172D model introduced the lower rear fuselage with wraparound Omni-Vision rear window and a one-piece windshield. New rudder and brake pedals were also added. 1146 172Ds were built.[5] 1963 also saw the introduction of the 172D Powermatic. This was equipped with a Continental GO-300E producing 175 horsepower (130 kW) and a cruise speed 11 mph (18 km/h) faster than the standard 172D. In reality this was not a new model but was a Cessna 175 Skylark that had been renamed for its last year of production. The Skylark had gained a reputation for poor engine reliability and the renaming of it as a 172 was a marketing attempt to regain sales through rebranding. The move was not a success and neither the 1963 Powermatic nor the Skylark were produced again after the 1963 model year. [5] [7]


The 172E was the 1964 model. The electrical fuses were replaced with circuit breakers. Gross weight was increased to 2,300 lb (1,043 kg) where it would stay until the 172P. 1401 172Es were built that year as production continued to increase. [5]


The 1965 model 172F introduced electrically-operated flaps to replace the previous lever-operated system.[8] It was built in France by Reims Cessna as the F172 until 1971. These models formed the basis for the US Air Force's T-41A Mescalero primary trainer.

A total of 1436 172Fs were completed. [5]


The 1966 model year 172G introduced a more pointed spinner and sold for USD$12,450 in its basic 172 version and USD$13,300 in the upgraded Skyhawk version. 1597 were built. [5]


The 1967 model 172H was the last Continental O-300 powered model. It also introduced a shorter-stroke nose gear oleo to reduce drag and improve the appearance of the aircraft in flight. A new cowling was used, introducing shock-mounts that transmitted lower noise-levels to the cockpit and reduced cowl cracking. The electric stall warning horn was replaced by a pneumatic one.

The 1967 model 172H sold for USD$10,950 while the Skyhawk version was USD$12,750. 839 were built that year, representing the first year that production was less than the year before. [5]


The 1968 model marked the beginning of the Lycoming powered 172s. The familiar 172 needed to be re-engined because Cessna had cancelled its contract with Continental for their venerable 0-300 6-cyl engine of 145 hp (108 kW). [citation needed]

The "I" model was introduced with a Lycoming O-320-E2D engine of 150 hp (112 kW), an increase of 5 hp (3.7 kW) over the Continental powerplant. The increased power resulted in an increase in optimal cruise from 130 mph (209 km/h) TAS to 131 mph (211 km/h) TAS. There was no change in the sea level rate of climb at 645 ft (197 m) per minute.

The 172I also introduced the first standard "T" instrument arrangement. The 172I saw an increase in production to record levels with 1206 built. [5]


The Cessna Company planned to drop the previous 172 configuration for the 1968 model year and replace it with a cantilever-wing/stabilator configuration that would be the 172J. However, as time for model introduction neared, those dealers who were aware of the change began applying pressure on the factory to continue the previous configuration. They felt the new model would be less usable as a trainer. Consequently, and at the last minute, the decision was made to continue the 172 in its original configuration. The planned 172J configuration would be introduced as a new model, the 177. The deluxe option would become the 177 Cardinal. The "J" designation was never publicly used.


The next model year was the 1969 "K" model. The 1969 172K had a redesigned vertical fin cap and reshaped rear windows. Optional long range 52 US gal (197 l) wing fuel tanks were offered. The rear windows were slightly enlarged by 16 square inches (103 cm2). The 1969 model sold for USD$12,500 for the 172 and USD$13,995 for the Skyhawk, with 1170 made. [5]

The 1970 model was still called the 172K but sported fiberglass, downward-shaped, conical wing tips. Fully articulated seats were offered as well. Production in 1970 was 759 units. [5]


The 172L, sold during 1971 and 1972, replaced the main landing gear, which were originally flat spring steel with tapered, tubular steel gear legs. The new gear had a width that was increased by 12 in (30 cm).[5] The new tubular gear was lighter, but required aerodynamic fairings to maintain the same speed and climb performance as experienced with the flat steel design. The "L" also had a plastic fairing between the dorsal fin and vertical fin to introduce a greater family resemblance to the 182's vertical fin.

The 1971 model sold for USD$13,425 in the 172 version and USD$14,995 in the Skyhawk version. 827 172Ls were sold in 1971 and 984 in 1972. [5]


The 172M of 1973-76 gained a drooped wing leading edge for improved low speed handling. This was marketed as the "camber-lift" wing. The 1974 172M was also the first to introduce the optional 'II' package which offered higher standard equipment, including a second nav/comm radio, an ADF and transponder. The baggage compartment was increased in size and nose-mounted dual landing lights were available as an option. [5]

The 1975 model 172M sold for USD$16,055 for the 172, USD$17,890 for the Skyhawk and USD$20,335 for the Skyhawk II. Total production of "M" models was 7306 over the four years it was manufactured. [5]

In 1976, Cessna stopped marketing the aircraft as the 172 and began exclusively using the "Skyhawk" designation. This model year also saw a redesigned instrument panel to hold more avionics. [5]


The Skyhawk N, or Skyhawk/100 as Cessna termed it, was introduced for the 1977 model year. The "100" designation indicated that it was powered by a Lycoming O-320-H2AD, 160 horsepower (119 kW) engine designed to run on 100 octane fuel, whereas all previous engines used 80/87 fuel. Unfortunately, this engine proved troublesome and it was replaced by the similarly rated O-320-D2J to create the 1981 172P.

The 1977 "N" model 172 also introduced rudder trim as an option and standard "pre-selectable" flaps. The price was USD$22,300, with the Skyhawk/100 II selling for USD$29,950. [5]

The 1978 model brought a 28-volt electrical system to replace the previous 14-volt system. Air conditioning was an option. [5]

The 1979 model "N" increased the flap extension speed for the first 10 degrees to 115 knots (213 km/h). Larger wing tanks increased the optional fuel to 66 US gallons (250 l). [5]

The "N" remained in production until 1980 when the 172P or Skyhawk P was introduced. [5]


There was no "O" ("Oscar") model 172. [5]


The 172P, or Skyhawk P, was introduced in 1981 to solve the reliability problems of the "N" engine. The Lycoming O-320-D2J was a great improvement.

The "P" model also saw the maximum flap deflection decreased from 40 degrees to 30 to allow a gross weight increase from 2,300 lb (1,043 kg) to 2,400 lb (1,089 kg). A wet wing was optional, with a capacity of 62 US gallons of fuel. [5]

The price of a new Skyhawk P was USD$33,950, with the Skyhawk P II costing USD$37,810 and the Nav/Pac equipped Skyhawk P II selling for USD$42,460. [5]

In 1982, the "P" saw the landing lights moved from the nose to the wing to increase bulb life. The 1983 model added some minor sound-proofing improvements and thicker windows. [5]

A second door latch pin was introduced in 1984. [6]

Production of the "P" ended in 1985 and no more 172s were built for eleven years as legal liability rulings in the USA had pushed Cessna's insurance costs too high, resulting in dramatically increasing prices for new aircraft. [citation needed]

There were only 195 172s built in 1984, a rate of fewer than 4 per week. [5]

172Q Cutlass

The 172Q was introduced in 1983 and given the name Cutlass to create an affiliation with the 172RG, although it was actually a 172P with a Lycoming O-360-A4N engine of 180 horsepower (134 kW). The aircraft had a gross weight of 2,550 lb (1,157 kg) and an optimal cruise speed of 122 knots (226 km/h) compared to the "P"s cruise speed of 120 knots (222 km/h) on 20 hp (15 kW) or less. It had a useful load that was about 100 lb (45 kg) more that the Skyhawk P and a rate of climb that was actually 20 feet (6 m) per minute lower, due to the higher gross weight. Production ended after only three years when all 172 production stopped. [5]


The Skyhawk R was introduced in 1996 and is powered by a derated Lycoming IO-360-L2A producing a maximum of 160 horsepower (120 kW) at just 2,400 rpm. This is the first Cessna 172 to have a factory fitted fuel-injected engine.

The 172R's maximum takeoff weight is 2,450 lb (1,111 kg). This model year introduced many improvements, including a new interior with soundproofing, an all new multi-level ventilation system, a standard four point intercom, contoured, energy absorbing, 26g front seats with vertical and reclining adjustments and inertia reel harnesses.


The Cessna 172S was introduced in 1998 and is powered by a Lycoming IO-360-L2A producing 180 horsepower (134 kW). The maximum engine rpm was increased from 2,400 rpm to 2,700 rpm resulting in a 20 hp (15 kW) increase over the "R" model. As a result, the maximum takeoff weight was increased to 2,550 lb (1,157 kg). This model is marketed under the name Skyhawk SP, although the Type Certification data sheet specifies it is a 172S. [9] [10]

The 172S is built primarily for the private owner-operator and is offered with the Garmin G1000 avionics package as standard equipment and leather seats. [11]

As of 2009, only the S model is in production. [12]

Cessna 172RG Cutlass

Cessna introduced a retractable-gear version of the 172 in 1980 and named it the Cutlass 172RG.

The Cutlass featured a variable pitch, constant speed propeller and more powerful Lycoming O-360-F1A6 engine of 180 horsepower (130 kW). The 172RG sold for about USD$19,000 more than the standard 172 of the same year and produced an optimal cruise speed of 140 knots (260 km/h), compared to 122 knots (226 km/h) for the contemporary 160 horsepower (120 kW) version. [5]

The 172RG did not find wide acceptance in the personal aircraft market, but was adopted by many flight schools as a complex aircraft trainer. Between 1980 and 1984 1177 RGs were built, with a small number following before production ceased in 1985.

While numbered and marketed as a 172, the 172RG was actually certified on the Cessna 175 type certificate. [7]

Reims FR172J and Cessna R172K Hawk XP

The FR172J Reims Rocket was produced by Reims Aviation in France from the late 60s to the mid 70s. It was powered by a Rolls-Royce built, fuel-injected, Continental IO-360D 210 hp (160 kW) engine with a constant speed prop.

The Reims Rocket led to Cessna producing the R172K Hawk XP, a model available from 1977 to 1981 from both Wichita and Reims. This configuration featured a fuel injected, Continental IO-360K (later IO-360KB) derated to 195 hp (145 kW) with a two bladed, constant speed propeller. The Hawk XP was capable of a 131-knot (243 km/h) cruise speed.

Owners claimed that the increased performance of the "XP" didn't compensate for its increased purchase price and the higher operating costs associated with the larger engine. The aircraft was well-accepted for use on floats, however, as the standard 172 is not a strong floatplane, even with only two people on board, while the XP's extra power improves water take-off performance dramatically. [5]

While numbered and marketed as 172s, the R172J and R172K models are actually certified on the Cessna 175 type certificate. [7]

Future Models


On October 4, 2007 Cessna announced its plan to build a diesel-powered Cessna 172 model starting in mid-2008. The planned engine was to be a Thielert Centurion 2.0, liquid-cooled, two-litre displacement, dual overhead cam, four-cylinder, in-line, turbo-diesel with full authority digital engine control.[13] The engine produced 155 hp (116 kW) and burns Jet-A fuel. The engines were to be installed at the Cessna Skyhawk factory in Independence, Kansas under an STC. The new model was designated the 172 Skyhawk TD, indicating "Turbo Diesel". [1]

Cessna had taken special measures to ensure that the Skyhawk TD would be only fueled with Jet-A and not misfueled with avgas. These included placards, key-shaped tank fillers that only accept jet fuel nozzles and a spring-loaded door activated with a jet-fuel nozzle. The aircraft was planned to be certified for Jet-A only and not automotive diesel. [14]

The TD was to be equipped with only one engine control, referred to as a "power control", although it resembled the push-pull style throttle used in previous 172 models. The prototype has no carburetor heat or mixture control. The prototype is equipped with a constant speed MT propeller, but this is controlled automatically and there is no propeller rpm control. [14]

The TD was designed to have the same gross weight as the "S" Skyhawk, 2,552 lb (1,158 kg), but at 155 hp (116 kW) was intended to have 25 hp (19 kW) less than the "S" model. Because it is turbonormalized the prototype's engine produces full power at all altitudes and actually puts out more power than the "R" and "S" models above 8,500 feet (2,600 m), where the normally aspirated powerplant's output drops off. [14]

To account for the fact that Jet-A has a higher density than avgas Cessna planned to reduce the tank capacity on the TD to 44.6 US gallons, giving the aircraft a similar range to other models, due to the better efficiency of the diesel engine. The Thielert 2.0 is reported to burn 5.8 gal/hr at 5,000 feet (1,500 m) and 75% power. This compares to 8 gal/hr at the same power setting and altitude for the "R" model and 10 gal/hr for the "S" model Skyhawks. [14]

Even with the reduced fuel tank capacity the full fuel payload of the TD will be 445 lb (202 kg)[14] compared to 519 lb (235 kg) for the Cessna 172S[15] and 440 lb (200 kg) for the 172R. [16]

Direct operating costs for the TD were forecast to be USD$96.39 per hour versus USD$101.81 for the higher powered "S" model. While the TD would burn less fuel per hour its engine replacement costs at 2400 hours, instead of overhaul, would almost make up for the difference, although these numbers will change as the price of fuel changes in future years. [14]

In early 2008 certification had been planned for the summer of 2008 and Cessna had forecast delivering about 125 TDs before the end of 2008. [14]

The TD was intended to sell for about USD$15,000 more than the top of the line "SP" Skyhawk and $35,000 more than the "R".[14] Base price was initially advertised as USD$269,500 versus USD$254,500 for the "SP" or $234,500 for the "R". [17]

In April 2008 the 172TD's engine manufacturer, Thielert filed for insolvency under German law, throwing the future of the aircraft into doubt. [18] [19] [20] [21]

On May 1, 2008 Cessna announced that they have cancelled all 2008 deliveries of the 172TD due to the insolvency of Thielert. The company stated: "At this point we have decided that we will not deliver 172TD aircraft during 2008, and we have informed our customers accordingly."[22] Cessna has indicated, however, that they will proceed with the certification of the 172TD. [23]

Cessna has indicated that they still wish to produce a diesel 172 as market demand is strong for this aircraft with over 100 orders. [22]

Aircraft type Clubs

The Cessna 172 is supported by a number of active aircraft type clubs, including The Cessna Pilots Association and The Cessna 172/182 Club. [24]

Military Operators

A variant of the 172, the T-41 Mescalero is used as a trainer with the United States Air Force and Army. Due to its high-wing design, stability at low airspeeds and relatively low stall speed, the 172 is used for search operations and is the primary platform for the Civil Air Patrol's operations. In addition, the United States Border Patrol uses a fleet of 172s for aerial surveillance along the Mexican-American border.

The Irish Air Corps uses the Reims version for aerial surveillance and monitoring of cash, prisoner & explosive escorts in addition to army co-operation and pilot training roles.[25] The type is popular and successful in service despite some accidents. Air Corps examples are painted dark green and carry the service roundels. Most are not fitted with the distinctive wheel spats.


  • Bolivian Air Force 3 x 172K [26]
  • Chilean Army 18 x R172K [27]
  • Ecuadorian Air Force 8 x 172F [28]
  • Ecuadorian Army 1 x 172G [26]
  • Guatemalan Air Force 6 x 172K [29]
  • Honduran Air Force 3 [30]
  • Iraqi Air Force [31] 12 [citation needed ]
  • Irish Air Corps 8 x FR172H, 1 x FR172K [32]
  • Air Reconnaissance Unit 2 [33]
  • Malagasy Air Force 4 x 172M [34]
  • Pakistan Air Force 4 x 172N [35]
  • Philippine Army - [36]
Saudi Arabia
  • Royal Saudi Air Force 8 x F172G, 4 x F172H, 4 x F172M [37]

Notable Flights

On December 4, 1958 Robert Timm and John Cook took off from McCarran Airfield, Las Vegas, NV in N9172B. Sixty four days, 22 hours, 19 minutes and 5 seconds later, they landed back at McCarran Airfield on February 4, 1959. The flight was part of a fund raising effort for the Damon Runyon Cancer Fund. Food and water were transferred by matching speeds with a chase car on a straight stretch of road in the desert, and hoisting the supplies aboard with a rope and bucket. Fuel was taken on by hoisting a hose from a fuel truck up to the aircraft, filling an auxiliary belly tank installed for the flight, pumping that fuel into the aircraft's regular tanks, and then filling the belly tank again. The drivers steered while a second person matched speeds with the aircraft with his foot on the vehicle's accelerator pedal.

Engine oil was added by means of a tube from the cabin that was fitted to pass through the firewall. Only the pilot's seat was installed. The remaining space was used for a pad on which the relief pilot slept. The right cabin door was replaced with an easy-opening, accordion-type door to allow supplies and fuel to be hoisted aboard. Early in the flight, the engine driven electric generator failed. A Champion wind driven generator (turned by a small propeller) was hoisted aboard, taped to the wing support strut, plugged into the cigarette lighter socket -- and served as the aircraft's source of electricity for the rest of the flight. The pilots decided to end the marathon-flight because, with over 1500 hours continuous running during the record-setting flight plus several hundred hours already on the engine beforehand (considerably in excess of its normal overhaul interval), the engine's power output had deteriorated to the point that they were barely able to climb away after refueling. The aircraft is on display in the passenger terminal at McCarran International Airport. Photos and details of the record flight can be seen in a small museum on the upper level of the baggage claim area. [38]

Specifications (172R)

General Characteristics

  • Crew: 1
  • Capacity: 3 passengers
  • Length: 27 ft 2 in (8.28 m)
  • Wingspan: 36 ft 1 in (11.0 m)
  • Height: 8 ft 11 in (2.72 m)
  • Wing area: 174 ft² (16.2 m²)
  • Airfoil: NACA 2412 (modified)
  • Empty weight: 1,620 lb (736 kg)
  • Useful load: 830 lb (376 kg)
  • Max takeoff weight: 2,450 lb (1,113 kg)
  • Powerplant: 1× Lycoming IO-360-L2A flat-4 engine, 160 hp (120 kW) at 2,400 rpm
  • * Zero-lift drag coefficient: 0.0319
  • Drag area: 5.58 ft² (0.52 m²)
  • Aspect ratio: 7.32
  • Lift-to-drag ratio: 11.6
  • Wing loading: 14.1 lb/ft² (68.8 kg/m²)
  • Power/mass15.3 lb/hp (9.25 kg/kW)


  • Never exceed speed: 163 knots (187 mph, 302 km/h)
  • Maximum speed: 123 knots (141 mph, 228 km/h) at sea level
  • Cruise speed: 122 knots (140mph, 226 km/h)
  • Range: 610 nm (790 mi, 1,272 km) at 55% power at 12,000 ft (3,040 m)
  • Service ceiling: 13,500 ft (4,116 m)
  • Rate of climb: 720 ft/min (3.7 m/s)


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