Cessna 310

The Cessna 310 is an American four-to-six-seat, low-wing, twin-engined monoplane produced by Cessna between 1954 and 1980. It was the first twin-engined aircraft that Cessna put into production after World War II.

N364NY_Cessna_310_CVT_12-08-15_(20333207180)

Cessna 310R

Development

The 310 first flew on January 3, 1953 with deliveries starting in late 1954. The sleek modern lines of the new twin were backed up by innovative features such as engine exhaust thrust augmenter tubes and the storage of all fuel in tip tanks in early models. In 1964, the engine exhaust was changed to flow under the wing instead of the augmenter tubes, which were considered to be noisy.

Typical of Cessna model naming conventions, a letter was added after the model number to identify changes to the original design over the years. The first significant upgrade to the 310 series was the 310C in 1959, which introduced more powerful 260 hp (194 kW) Continental IO-470-D engines. In 1960 the 310D featured swept back vertical tail surfaces. An extra cabin window was added with the 310F.

Commercial applications

The Cessna 310 was a common charter aircraft for the many air taxi firms that sprang up in the general aviation boom that followed World War II. The advantages of the Cessna 310 over its contemporaries, such as the Piper PA-23, were its speed, operating costs and aftermarket modifications such as the Robertson STOL kits which made it popular worldwide for its bush flying characteristics. It could use short runways while at the same time carrying a large useful load of 2,000 lb (910 kg). or more, at high speeds for a twin-engine piston aircraft.

  •  Role: Twin-engined cabin monoplane
  • Manufacturer: Cessna
  • First flight: January 3, 1953
  • Introduction: 1954
  •   Primary users:  General Aviation; United States Air Force
  • Produced: 1954–1980
  • Number built: 5449 (310) ; 577 (320)
  •  Unit cost: US$48,500 (310A, 1955); US$147,750 (310R, 1978); US$228,000 (T310R, 1981)

Specifications 1956 model 310 (Data from 1956 Observers Book of Aircraft)

General characteristics

  • Crew: one
  • Capacity: four passengers
  •  Length: 27 ft 0 in (8.23 m)
  • Wingspan: 35 ft 0 in (10.67 m)
  • Height: 10 ft 6 in (3.20 m)
  • Wing area: 175 sq ft (16.3 m2) [68]
  •  Empty weight: 2,850 lb (1,293 kg)
  • Gross weight: 4,600 lb (2,087 kg)
  • Powerplant: 2 × Continental O-470-B horizontally opposed piston engines, 240 hp (180 kW) each

Performance

  • Maximum speed: 220 mph (354 km/h; 191 kn)
  • Cruise speed: 205 mph (330 km/h; 178 kn)
  • Range: 1,000 mi (869 nmi; 1,609 km)
  • Service ceiling: 20,000 ft (6,100 m)
  • Rate of climb: 1,700 ft/min (8.6 m/s)

Variants

310-Initial production variant, powered by two 240 hp (180 kW) Continental O-470-B or O-470-M engines with carburettors, with maximum takeoff weight of 4,600 pounds (2,100 kg); in production for 1955-1957 model years, 547 built.

310A-Military version of the 310 for the United States Air Force, designated L-27A and later U-3A; with Continental O-470-M engines and maximum takeoff weight of 4,830 pounds (2,190 kg); 161 built.

220px-Cessna_310B_(VH-REK)_at_Illawarra_Regional_Airport

1957 Cessna 310B (VH-REK), with straight fin and overwing augmentor tube exhaust system 

 

310B-Model produced in 1958, with new instrument panel, O-470-M engines and maximum takeoff weight of 4,700 pounds (2,100 kg); 225 built.

310C-Model produced in 1959, with 260 hp (190 kW) Continental IO-470-D fuel-injected engines and maximum takeoff weight increased to 4,830 pounds (2,190 kg); and minor changes; 260 built. Unit cost $59,950 in 1959.


 

Songbird_III

Cessna 310D with early rounded nose and ‘tuna’ style wingtip fuel tanks 

310D-First model with swept vertical tail, other minor detail changes; 268 built for 1960 model year.

310E-Military version of the 310F, designated the L-27B and later U-3B; with maximum takeoff weight of 4,990 pounds (2,260 kg); 36 built.

310F-Model produced in 1961, with extra cabin window each side, pointed nose and other minor changes; maximum takeoff weight of 4,830 pounds (2,190 kg); 155 built.

310G-First model with canted slimline tip tanks and optional six-seat cabin, with maximum takeoff weight increased to 4,990 pounds (2,260 kg) and detail changes, 156 built in 1962.

310H-Model produced in 1963 with maximum takeoff weight increased to 5,100 pounds (2,300 kg) and enlarged cabin interior. E310H-Version of 310H with the  4,990-pound (2,260 kg) maximum takeoff weight of the 310G; combined total of 148 310H and E310H built.

310I-First model with baggage compartments in rear of engine nacelles, Continental IO-470-U engines and minor detail changes; 200 built in 1964. 310J-Model produced in 1965 with minor detailed changes and maximum takeoff weight of 5,100 pounds (2,300 kg).

Cessna310J

Cessna 310J 

310J-1-Version of 310J type-certified in the Utility Category; with maximum takeoff weight increased to 5,150 pounds (2,340 kg); seating limited to four people instead of the 310J’s six; and reduced baggage weight limit. E310J-Version of 310J with maximum takeoff weight reduced to 4,990 pounds (2,260 kg); combined total of 200 310J, 310J-1 and E310J built.

310K-First model with optional three-blade propellers and long ‘vista view’ side windows; also increased maximum takeoff weight of 5,200 pounds (2,400 kg) with IO-470-V or IO-470-VO engines; 245 built in 1966.

310L-First model with increased fuel capacity via fuel tanks inside wings and optional fuel tanks in engine nacelles, also single-piece windshield, redesigned landing gear, and minor changes; 207 built in 1967.

310M-Revised designation for the 310E.

220px-Cessna.310n.g-yhpv.arp

1968 Cessna 310N 

 310N-Model produced in 1968, with revised instrument panel and minor changes; 198 built.

220px-CessnaT310PC-GXXN

Cessna T310P equipped with a nose-mounted IR detection system for forest fire detection 

310P-Model produced in 1969, with Continental IO-470-VO engines, ventral fin and a shorter nosegear leg. T310P-Version of 310P with turbocharged Continental TSIO-520-B or TSIO-520-BB engines producing 285 hp (213 kW) and maximum takeoff weight of 5,400 pounds (2,400 kg); combined total of 240 310P and T310P built.

220px-Cessna310Q (1)

Cessna 310Q

310Q-Last short-nose model, introduced in 1970, with maximum takeoff weight increased to 5,300 lb (2,400 kg) and detailed changes, from the 401st aircraft fitted with a bulged rear cabin roof with rear view window. T310Q–Version of 310Q with turbocharged Continental TSIO-520-B or TSIO-520-BB engines and maximum takeoff weight increased to 5,500 lb (2,500 kg); combined total of 871 310Q and T310Q built.

220px-1977CessnaT310R

1977 Cessna T310R 

310R–Last production model, introduced in the 1975 model year, with 285 hp (213 kW) Continental IO-520-M or IO-520-MB engines; three-blade propellers as standard; lengthened nose containing a baggage compartment; and 5,500 lb (2,500 kg) maximum takeoff weight. T310R-Version of 310R with turbocharged Continental TSIO-520-B or TSIO-520-BB engines; combined total of 1,332 310R and T310R built.

310S-Original designation for the Cessna 320.

Cessna_320_OE-FBW_HAN_07.05.66_edited-3

Austrian-registered Cessna 320  (OE-FBW) Skyknight at the 1966 Hanover Air Show, displaying this variant’s fourth side window 

The turbocharged 320 Skyknight was developed from the 310F. Equipped with TSIO-470-B engines and featuring an extra cabin window on each side, it was in production between 1961 and 1969 (the 320E was named the Executive Skyknight), when it was replaced by the similar Turbo 310.

 

The 310G was certified in 1961 and introduced the canted wingtip fuel tanks found on the majority of the Cessna twin-engined product line, marketed as ‘stabila-tip’ tanks by Cessna because they were meant to aid stability in flight. A single side window replaced the rear two windows on the 310K (certified in late 1965), with optional three-blade propellers being introduced as well. Subsequent developments included the 310Q and turbocharged T310Q with a redesigned rear cabin featuring a skylight window, and the final 310R and T310R, identifiable by a lengthened nose containing a baggage compartment. Production ended in 1980.

Over the years there were several modifications to the 310 to improve performance. Noted aircraft engineer Jack Riley produced two variants, The Riley Rocket 310 and the Riley Turbostream 310. Riley replaced the standard Continental 310 hp (230 kW) engines with 350 hp (261 kW) Lycoming TIO-540 engines. These turbocharged intercooled engines were installed with three-blade Hartzell propellers in a counter-rotating configuration to further increase performance and single-engine safety. At 5,400 lb (2,400 kg). gross weight the aircraft had a weight to power ratio of 7.71 lb (3.50 kg). per horsepower. This resulted in a cruising speed of 260 knots (480 km/h) at 18,000 feet (5,500 m) and a 3,000fpm rate of climb.

320 Skyknight-Enlarged version of the 310F with six seats, larger cabin and two turbocharged engines; 110 built.

  • 320A Skyknight-First model with canted fuel tanks and minor changes; 47 built.
  • 320B Skyknight-First model with nacelle baggage lockers, minor changes; 62 built.
  • 320C Skyknight-Model with a longer cabin, optional seventh seat and minor changes; 73 built.
  • 320D Executive Skyknight-Model with reshaped rear windows and 285 hp (213 kW) TSIO-520-B engines; 130 built.
  • 320E Executive Skyknight-Model with pointed nose, single piece windshield, modified landing gear, increased takeoff weight and minor changes; 110 built.
  • 320F Executive Skyknight-Model with minor changes compared to 320E; 45 built.

Riley 65

  • Conversion offered for Cessna 310 to 310G by fitting two 240-260 hp (179–194 kW) Continental O-470D/-470M engines.
  • Riley Super 310-Conversion of Cessna 310/320 by fitting two 310 hp (231 kW) Continental TSIO-520-J/-N engines.
  • Riley Turbostream-Conversion of Cessna 310 by fitting two 350 hp Lycoming engines.
  • Riley Rocket-Conversion of Cessna 310 by fitting two 290 hp (216 kW) Lycoming IO-540-A1A5 engines and more fuel.

Accidents and incidents

  • On October 28, 1959, a Cessna 310 carrying Cuban revolutionary Camilo Cienfuegos disappeared over the Atlantic Ocean on a night flight from Camaguey to Havana. Neither the aircraft nor the body of Cienfuegos were ever found.
  • On November 26, 1962, a VASP Saab Scandia 90A-1 registration PP-SRA en route from São Paulo-Congonhas to Rio de Janeiro-Santos Dumont collided in the air over the Municipality of Paraibuna, State of São Paulo with a private Cessna 310 registration PT-BRQ en route from Rio de Janeiro-Santos Dumont to São Paulo-Campo de Marte. Both were flying on the same airway in opposite directions and failed to have visual contact. The two aircraft crashed killing all 23 passengers and crew of the Saab and the four occupants of the Cessna.
  • On July 19, 1967, a Boeing 727 operating as Piedmont Airlines Flight 22 collided with a Cessna 310 at Hendersonville, North Carolina, USA, killing all 79 people on board the Boeing 727 and the three people in the Cessna.
  • On October 16, 1972, U.S. Congressmen Nick Begich of Alaska, and Hale Boggs of Louisiana, disappeared over Alaska while flying in a Cessna 310 during a campaign trip.
  • On 19 December 1992, Cuban defector Major Orestes Lorenzo Pérez returned to Cuba in a 1961 Cessna 310 to retrieve his wife Vicky and his two sons. Flying without lights, at low speed and very low altitude to avoid Cuban radar, Pérez picked up his family by landing on the coastal highway of Varadero beach, Matanzas Province, 93 mi (150 km) east of Havana and managed a successful safe return to Marathon, Florida.

As of July 2017, the NTSB has recorded 1,787 incidents for Cessna 310s since 12 January 1964. Only 436 of those incidents were fatal.

By courtesy of Wikipedia.org

 

One thought on “Cessna 310

  1. Cessna 310B (AP-AKP) was the aircraft on which I first got my instrument rating in the PIA Flying Academy in 1969. I think it is on display in Lahore in a public park.
    An instrument rating is an authorization issued by the civil aviation authority on behalf of the government which authorizes the pilot to conduct flight solely by reference to instruments. You have to demonstrate this ability in the air to an examiner and are required to conduct an instrument approach in simulated bad weather by arriving over the initial approach fix (radio beacon) and proceeding via the intermediate fix to the final approach fix in stages for a landing. (The radar can substitute for all this and guide you in in real time world. But the radar is not responsible for terrain clearance or obstacle avoidance until the controller affirms: “radar contact along with your radio call sign”, and then the responsibility is shared).
    For takeoff, a parameter of forward visibility has to be met in poor visibility and night conditions. For a landing in the same conditions an added parameter of height above airport (HAA)(HAT) must be met along with the visibility requirements. 300-1/4, would mean a landing minima of 300 feet HAT (Height Above Threshold) and a visibility of a quarter mile or better. The visibility requirement can be interchanged with the runway visual range (RVR). The RVR is the forward distance a pilot will normally see from the height of his cockpit while landing.

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