The Cessna P-780 was a five-seater powered by a Jacobs R-775-9 engine of 245 hp.
Cessna P-780
Post WW2
Cessna XMC / 1014 / 1034
The two-seat Cessna XMC prototype technology demonstrator was built to test several concepts in light aircraft design including a ducted propeller and swept cantilever wing. The XMC employed metal-to-metal bonding, allowing for experimentation in expanded use for bonding in other types in the Cessna commercial product line. Additional stress testing was also conducted as necessary as the aircraft entered further testing and modification.
The sole prototype was registered as N7174C and given Cessna serial number 674. It was powered by a Continental O-200 100 hp (75 kW) engine mounted in pusher configuration. This was the same powerplant used in the then-current production Cessna 150. The tail boom was similar in design to that used on the Cessna Skymaster.
The first flight of the 1014 model was made on January 22, 1971 by Cessna test pilot Bruce Barrett. Then testing ground handling, flying characteristics and visibility.
Phase II testing began in May 1971, exploring methods of reducing weight and production costs for single and twin-engine Cessnas.
The aircraft was modified in 1972 and given a new model number, 1034. In this configuration it was first flown June 1, 1972, again with Bruce Barrett at the controls, using a shrouded propeller to test improvements in propeller efficiency and reduction of noise in Phase III. The spatted nose gear was replaced by a wheel fairing, as was the main gear. An increased vertical stabilizer area and revised wing tips were also tested.
The XMC project ended in 1972. The aircraft configuration proved to have higher cabin noise levels than the production Cessna 150 and offered no performance advantages over the older design.
Cessna XMC prototype
Powerplant: 1 × Continental O-200, 100 hp (75 kW)
Wingspan: 32 ft 0 in (9.75 m)
Length: 23 ft 0 in (7.01 m)
Seats: 2
Cessna 620
The four-engine, pressurized Cessna Model 620 first flew on August 11, 1956 with Ralph Harmon at the controls. This attempt at a business transport was soon dropped in 1957 as it was apparent that there were too many surplus airplanes on the market for this approach to be a financial success. By all accounts, the airplane did fly nicely. The fuselage was sold as scrap and became a house trailer.
Engines: 4 x Continental GSO-526-A, 320 hp
Wing span: 55 ft
Length: 31 ft 6 in
Height: 16 ft 6 in
Cruise: 235 mph
Max speed: 269 mph
Cessna CE-550 Citation II / Bravo / T-47A
The success of the first Citation led Cessna to look at building larger and faster versions and development continued with the Model 550 Citation II. Announced in September 1976, the prototype first flew on 31 January 1977. Powered by two 1130kg JT15D-4 engines, the 8-12-seat aircraft featured a nearly 4 feet lengthened fuselage, increased span wings and more fuel and baggage space. Certification followed in March 1978.
Cessna CE-550 Citation II Article
In October 1983 the revised Citation S/ll was announced and the first production aircraft made its initial flight on 14 February 1984, with deliveries following soon after. This version has the JT15D-4B engine giving more power at higher altitudes, a new aerofoil section wing, leading-edge extensions, modified engine pylons and increased cabin headroom and baggage capacity. The Citation II/SP was cleared for single-pilot operation in July 1984.
A modified version of the Model 552 Citation S/ll was selected in May 1983 by the US Navy for training radar intercept operators designated T-47A. These have shorter span wings to increase rate of climb and maximum speed at altitude and more powerful 1315kg JT15D-5 engines. The T-47A first flew on 15 February 1984. Delivery of 15 T-47A was completed in May 1985. The T-47s are used to train aircrew in the operation of radar in both air-to-air and air-to-surface modes, and are equipped with nose-mounted Emerson APQ-159 radars. The US Customs Service operates seven Citations fitted with Westinghouse APG-66 (F-16A) radar. These are used to intercept and track drug smuggling aircraft.
The Citation II was taken out of production in 1984 when 503 had been built, but resumed in 1987. By the end of 1989 667 plus 15 T-47As had been delivered, making the Model 550 the best selling business jet.
The Citation II has now become Cessna Bravo.
1979 Citation II
Engines: 2 x Pratt & Whitney JT15D-4, 2,500 lb thrust.
Cruise speed: 385 kts.
Max range: 1,903 nm.
Max usable fuel: 742 USG.
ROC: 3,370 fpm.
ROC SE: 1,055 fpm.
Max Cert Alt: 43,000 ft.
Max cert alt SE: 25,200 ft.
Balanced field length: 2,990 ft.
Max ramp wt: 13,500 lbs.
Max zero fuel wt (opt): 11,000 lbs.
Useful load: 6,400 lbs.
Seats: 12.
CE-550 Citation II
Engines: 2 x P&W JT15D-4, 2,500 lbs thrust.
Seats: 8/10.
Length: 47.2 ft.
Height: 14.8 ft.
Wingspan: 51.7 ft.
Wing area: 323 sq.ft.
Wing aspect ratio: 8.3.
Maximum ramp weight: 13,500 lbs.
Maximum takeoff weight: 13,300 lbs.
Standard empty weight: 7196 lbs.
Maximum useful load: 6104 lbs.
Zero-fuel weight: 11,000 lbs.
Maximum landing weight: 12,700 lbs.
Wing loading: 41.2 lbs/sq.ft.
Power loading: 2.7 lbs/lb.
Maximum usable fuel: 5009 lbs.
Best rate of climb: 3370.
Certificated ceiling: 43,000 ft.
Max pressurisation differential: 8.7 psi.
8000 ft cabin alt @: 43,000 ft.
Maximum single-engine rate of climb: 1055 fpm @ 114 kts.
Single-engine climb gradient: 555 ft/nm.
Single-engine ceiling: 25,200ft.
Maximum speed: 385 kts.
Normal cruise @ 37,000ft: 369 kts.
Fuel flow @ normal cruise: 990 pph.
Stalling speed clean: 95 kts.
Stalling speed gear/flaps down: 81 kts.
Turbulent-air penetration speed: 180 kts.
Citation II
Engines: P&W JT15D-4B of 2,500 lbs / 1135 kp thrust.
Seats: 8/10
Length: 14.39 m / 47 ft 3 in
Height: 4.57 m / 15 ft.
Wingspan: 15.9 m / 52 ft 2 in
Wing Area: 342.6 sq.ft.
Wing Aspect Ratio: 7.8.
Max Ramp Weight: 14,900 lbs.
Max Take-off Weight: 14,700 lbs.
Std Empty Weight: 7,716 lbs.
Max Useful Load: 7,184 lbs.
Zero-Fuel Weight: 11,000 lbs.
Max Landing Weight: 14,000 lbs.
Wing Loading: 42.9 lbs/ sq.ft.
Power Loading: 2.9 lbs/lb.
Max Usable Fuel: 5,638 lbs.
Max Rate of Climb: 3,100 fpm.
Ceiling (certificated): 43,000 ft. Max
Pressurisation Differential: 8.8.
8,000 ft Cabin Altitude at: 43,000 ft.
SE Rate of Climb: 930 fpm.
SE Ceiling; 26,000 ft.
Speed, Max: 403 kts.
Normal Cruise 37,000 ft: 399 kts.
Fuel Flow at Normal Cruise: 1,092 pph.
Stall Speed, Clean: 95 kts.
Stall Speed, Flaps/Gear Down: 81 kts.
Turbulent Air Penetration Speed: 180 kts.
Range: 1807 nm / 3347 km
Bravo
Engines: two 2,885-lb. Pratt & Whitney PW503A turbofans.
Seats: 7-10.
Gross wt. 14,800 lb
Empty wt. 8,750 lb
Max cruise 401 kts
Initial climb rate 3,195 fpm
Range 1,739-1,900 nm
Ceiling 45,000
Cruise: 403 kts
Range: 1800 nm
Cessna Fanjet 500 / CE-500 Citation / CE-501 Citation I
Announced in 7 October 1968, Cessna’s first business jet, the FanJet 500, made its maiden flight on September 15, 1969. Renamed the Model 500 Citation shortly after the first flight, the eight-seat Model 500 has an overall configuration similar to that of earlier Cessna twins except for its powerplant installation. This featured two 990kg Pratt & Whitney Canada JT15D-1 turbofans, mounted in pods on each side of the rear fuselage just aft of the wing trailing edge.
Cessna CE-500 Citation Article
First flown on 15 September 1969, development flying resulted in a number of changes, and it was not until 1972 that initial deliveries were made. The Citation received FAR Part 25 certification in September 1971 and the first Citation business jet was delivered to Levitz Furniture Corp in 1972.
In 1976 deliveries began of an improved Model 501 Citation I with increased wing span and similarly rated but improved JT15D-1A engines. This was followed soon after by the Citation 1/SP version certificated for single-pilot operation. This had JT15D-1A engines, thrust reversers, and a slightly increased wingspan.
When production ceased in June 1985, 691 Citation Is had been delivered.
CE-500 Citation I
Engines: 2 x P&W JT15D-1A, 2,200 lbs thrust.
Seats: 7/8.
Length: 43.5 ft.
Height: 14.3 ft.
Wingspan: 47.1 ft.
Wing area: 279 sq.ft.
Wing aspect ratio: 7.8.
Maximum ramp weight: 12,000 lbs.
Maximum takeoff weight: 11,850 lbs.
Standard empty weight: 6605 lbs.
Maximum useful load: 5395 lbs.
Zero-fuel weight: 9500 lbs.
Maximum landing weight: 11,350 lbs.
Wing loading: 42.5 lbs/sq.ft.
Power loading: 2.7 lbs/lb.
Maximum usable fuel: 3807 lbs/564 USG.
Best rate of climb: 2680 fpm.
Certificated ceiling: 41,000 ft.
Max pressurisation differential: 8.5 psi.
8000 ft cabin alt @: 41,000 ft.
Maximum single-engine rate of climb: 800 fpm @ 108 kts.
Single-engine climb gradient: 425 ft/nm.
Single-engine ceiling: 21,000 ft.
Maximum speed: 352 kts.
Max range: 1,326 nm.
Normal cruise @ 33,000ft: 352 kts.
Fuel flow @ normal cruise: 967 pph.
Stalling speed clean: 93 kts.
Stalling speed gear/flaps down: 82 kts.
Balanced field length: 2,930 ft.
Turbulent-air penetration speed: 183 kts.
Seats: 10.
Takeoff distance (50 ft) 3,275 ft.
Landing distance (50 ft) 2,300 ft
Cessna CE-441 Conquest
On 15 November 1974, Cessna announced the development of a new turboprop-powered pressurised executive transport designated Cessna Model 441. The prototype was flown for the first time on 26 August 1975 and by the time that initial deliveries began in September 1977 the type had been given the name Conquest and the basic airplane sold for US$850,000. The aircraft was certified on 19 August 1977, and powered by two Garrett TPE331 turboprop engines to provide the high-altitude/high-speed performance that Cessna required for this 11-seat transport.
The Model 441 Conquest incorporated the wing and landing gear of the Model 404 Titan, with the span increased by the use of wingtip extensions. The pressurised and air-conditioned cabin could accommodate up to 10 passengers, although a four-seat de luxe version was offered for executive use.
The Cessna 441 wings are of “failsafe” construction, meaning there is no life limit requiring either fail safe design or established fatigue life limits. The useful load of the 441 is 48 percent of its gross weight. The cabin is pressurized to 6.3 psi for a 10,000 foot cabin at 33,000 feet. The 441 will climb to 33,000 in 22 minutes. The wing is of bonded construction, with 30 percent chord Fowler type flaps utilized to lower the landing speed. Maximum cruise is 277 knots. VFR range with 10 and baggage will be 1,150 nm; it will be 1,830 nm with five and baggage. The airplane exceeded every performance standard set for it before the certification program began, including a 10 knot increase in maximum cruising speed at 33,000 feet, to 287 knots.
In early 1978, one of the first production aircraft being involved in a crash resulting in the Conquest being grounded by Cessna. Modification of the tail unit was carried out before the type was re-certificated, and aircraft that were already completed had to be modified with a new tailplane.
A 400 lb gross weight increase is possible for the Corsair when owners fit the later standard stronger wheels and change tyres from 8 to 10 ply. On completing these changes they now have a Conquest I and the original big brother becomes Conquest II.
In 1983 the Model 441 was redesignated and marketed as the Conquest II and by 1986 when production ceased, 353 examples had been sold.
Conquest – Engines: 2 x Garrett AiResearch TPE 331 8 401S/402S, 635.5 shp, 474kW
Props: Hartzell three blade, constant speed, full feathering, reversible, 90 in dia.
TBO: 3,000 hrs.
Length: 11.89 m / 39 ft 0 in
Height: 4.01 m / 13 ft 2 in
Wingspan: 15.04 m / 49 ft. 4 in.
Wing area: 23.56 sq.m / 253.60 sq ft
Wing loading: 38.8 lb/sq.ft.
Power loading: 7.88 lb/hp.
Seats: 9.
Empty wt: 5,929 lbs.
Useful load: 3,996 lbs.
Payload with full fuel: 813 lbs.
Max ramp wt: 9,925 lbs.
Max Take-off weight: 4468 kg / 9850 lb
Usable fuel cap: 475 USG/3,183 lb.
Max landing wt: 9,360 lbs.
Max zero fuel wt: 8,100 lbs.
Max allowable payload: 2,171 lbs.
Max ROC: 2,435 fpm.
SE ROC: 715 fpm.
SE climb gradient at 120 kt (Vyse): 358 ft. per nm.
Service ceiling: 37,000 ft.
Maximum operating altitude without oxygen for each occupant: 25,000 ft.
Maximum operating altitude with oxygen for each occupant: 33,000 ft.
SE service ceiling: 21,380 ft.
Max speed: 295 kts.
Max cruise, at 24,000 ft: 293 kts.
Max range cruise, at 33,000 ft: 257 kts.
Duration at max cruise: 5.68 hrs.
Duration at max range cruise: 9.4 hrs.
Max range: 2,196 nm / 4245 km / 2638 miles.
Stalling speed, clean: 89 kt.
Stalling speed, full flaps: 74 kts.
Pressurization differential: 6.3 psi.
10,000 ft. cabin at: 33,000ft.
Takeoff dist 50 ft obstacle: 2,465 ft.
Landing Dist 50 ft obstacle: 1,875 ft.
Seats: 11.
CE-441 Conquest
Engines: 2 x Garrett TPE-331-8-403S, 635 shp.
Props: McCauley 3-blade, 93-in.
Seats: 8.
Length: 34.7 ft.
Height: 12.8 ft.
Wingspan: 42.7 ft.
Wing area: 229 sq.ft.
Wing aspect ratio: 9.5.
Maximum ramp weight: 9925 lbs.
Maximum takeoff weight: 9850 lbs.
Standard empty weight: 5682 lbs.
Maximum useful load: 4243 lbs.
Zero-fuel weight: 8500 lbs.
Maximum landing weight: 9360 lbs.
Wing loading: 38.8 lbs/sq.ft.
Power loading: 7.8 lbs/hp.
Maximum usable fuel: 3183 lbs.
Best rate of climb: 2435 fpm.
Certificated ceiling: 35000 ft.
Max pressurisation differential: 6.3 psi.
8000 ft cabin alt @: 28500 ft.
Maximum single-engine rate of climb: 715 fpm @ 120 kts.
Single-engine climb gradient: 358 ft/nm.
Single-engine ceiling: 21380 ft.
Maximum speed: 295 kts.
Normal cruise @ 33,000ft: 287 kts.
Fuel flow @ normal cruise: 372 pph.
Endurance at normal cruise: 7.4 hrs:
Stalling speed clean: 90 kts.
Stalling speed gear/flaps down: 76 kts.
Turbulent-air penetration speed: 167 kts.
Cessna CE-425 Corsair I
In November 1977 Cessna initiated the design of a new pressurised aircraft and the prototype flew for the first time on 12 September 1978. The aircraft combined the airframe of the Model 421 Golden Eagle with two Pratt & Whitney of Canada PT6A turboprop engines. Other features included the dihedral tailplane of the Model 404.
The new aircraft was introduced in 1980 as the Cessna Model 425 Corsair. Like the Model 421, the Corsair offered six/eight seats in varying. The Corsair was certified in mid-1980 and first deliveries made in November the same year.
Late in 1982 the aircraft was retrospectively designated and marketed as the Corsair I and 226 had been delivered when production terminated in 1986. The Garrett-engined Corsair II was built as the Model 441
A 400 lb gross weight increase is possible for the Corsair when owners fit the later standard stronger wheels and change tyres from 8 to 10 ply. On completing these changes they now have a Conquest I and the original big brother becomes Conquest II.
CE-425 Corsair
Engines: 2 x P&W PT6A-112, 450 shp, 335kW.
Props: McCauley 3-blade, 93-in.
Seats: 6/8.
Length: 10.93 m / 35 ft 10 in
Height: 3.84 m / 12 ft 7 in
Wingspan: 13.45 m / 44 ft 2 in
Wing area: 20.90 sq.m / 224.97 sq ft
Wing aspect ratio: 8.7.
Maximum ramp weight: 8275 lbs.
Maximum takeoff weight: 8200 lbs.
Standard empty weight: 4915 lbs.
Maximum useful load: 3360 lbs.
Zero-fuel weight: 6740 lbs.
Maximum landing weight: 8000 lbs.
Wing loading: 36.4 lbs/sq.ft.
Power loading: 9.1 lbs/hp.
Maximum usable fuel: 2452 lbs.
Best rate of climb: 2027 fpm.
Certificated ceiling: 30000 ft.
Max pressurisation differential: 5 psi.
8000 ft cabin alt @: 23500 ft.
Maximum single-engine rate of climb: 434 fpm @ 111 kts.
Single-engine climb gradient: 235 ft/nm.
Single-engine ceiling: 18500 ft.
Maximum speed: 264 kts.
Normal cruise @ 26,000ft: 257 kts.
Fuel flow @ normal cruise: 400 pph.
Endurance at normal cruise: 5.1 hrs:
Stalling speed clean: 88 kts.
Stalling speed gear/flaps down: 79 kts.
Turbulent-air penetration speed: 154 kts.
Cessna CE-421 Golden Eagle
A development of the CE 411A, designed in 1965 as the replacement for the model 411, the pressurised model 421 was not a great deal different in external appearance. The CE-421 first flew on 14 October 1965.
Derived from the Model 401/411, the Model 421 differed primarily in its original configuration by having a fail-safe pressurised fuselage structure and an AiResearch air-conditioning and pressurisation system. Deliveries of initial production aircraft began in May 1967, following certification of the type on the fist day of that month.
Two new versions of the Model 421 were introduced for 1970, the Model 421B Golden Eagle and Model 421B Executive Commuter. Both had a number of improvements including lengthening of the nose to provide more avionics and baggage capacity, an increase in wing span, strengthening of the landing gear for operation at higher gross weights, and many detail refinements. The Executive Commuter was basically the same as the Golden Eagle, but the interior was laid out with lightweight easily-removable seating to provide alternative passenger/cargo configurations which could accommodate a maximum of 10 passengers.
Production increased so that 1000 models had been built by 1975.
These two versions were replaced in 1976 by the Model 421C Golden Eagle, which introduced some important changes. These included a new wing that dispensed with the distinctive wingtip tanks, replaced by integral fuel tanks of the type introduced at a later date on the Model 414. Other changes provided increased area for the vertical tail surfaces and larger-capacity engine turbochargers. Four versions were available, the Model 421C Golden Eagle and Model 421C Executive Commuter, both produced in Model 421C II, versions with a factory-installed avionics/equipment package.
The Executive Commuter was discontinued for 1978, the Golden Eagle then being available in standard as well as Model 421C II and Model 421C III versions with differing avionics/equipment packages.
By late-1985 when production ceased, 1,909 Golden Eagles of all versions had been delivered, including three examples for the Royal New Zealand Air Force.
CE-421
Engines: 2 x Continental GTSIO-520-N, 280kW
Max Take-off weight: 3379 kg / 7449 lb
Empty weight: 2129 kg / 4694 lb
Wingspan: 12.53 m / 41 ft 1 in
Length: 11.09 m / 36 ft 5 in
Height: 3.49 m / 11 ft 5 in
Wing area: 19.97 sq.m / 214.96 sq ft
Max. speed: 478 km/h / 297 mph
Cruise speed: 356 km/h / 221 mph
Ceiling: 9205 m / 30200 ft
Range: 2752 km / 1710 miles
CE-421B Golden Eagle
Engine: Continental GTSIO 520H, 375 hp.
Prop: 3 blade, 90 in, full feathering.
Wing span: 41 ft. 10 in.
Length: 36 ft. 1 in.
Height: 11 ft. 7 in.
Wing area: 211.09 sq. ft.
Wing loading: 34.25 lb./sq. ft.
Seats: 6-8.
Empty weight, equipped: 5,000 lbs.
Useful load, equipped: 2,250 lbs.
Gross weight: 7,250 lbs.
Max landing weight: 7,200 lbs.
Power loading: 9.67 lb/hp.
Fuel cap (std): 170 USG.
Fuel cap (with res): 196 to 248 USG.
Baggage cap: 1,340 lb/ 73.3 cu.ft.
Takeoff dist: 1,838 ft.
Takeoff dist 50 ft: 2,325 ft.
SE takeoff dist 50 ft: 4,283 ft.
ROC: 1,950 fpm.
SE ROC: 345 fpm.
Service ceiling: 31,800 ft.
SE service ceiling: 15,000 ft.
Max speed: 283 mph/246 kts.
Cruise speed (75% power): 270 mph/234 kts.
Economical cruise: 224 mph/194 kts.
Range (at max cruise, std tanks): 1,067 sm/926 nm.
Range (at econ. cruise, std tanks): 1,194 sm/1,031 nm.
Stall speed (clean): 97 mph/84 kts.
Stall speed (gear & flaps down): 86 mph/75 kts.
Landing dist: 720 ft.
Landing distance 50 ft: 2,178 ft.
CE-421C Golden Eagle
Engines: Continental GTSIO-520-L, 375 hp each.
TBO: 1600 hrs.
Props: McCauley 3-blade, 90-in.
Seats: 8.
Length: 36.4 ft.
Height: 11.5 ft.
Wingspan: 41.1 ft.
Wing area: 215 sq.ft.
Wing aspect ratio: 7.9.
Maximum ramp weight: 7500 lbs.
Maximum takeoff weight: 7450 lbs.
Standard empty weight: 4640 lbs.
Maximum useful load: 2860 lbs.
Zero-fuel weight: 6733 lbs.
Maximum landing weight: 7200 lbs.
Wing loading: 34.7 lbs/sq.ft.
Power loading: 9.9 lbs/hp.
Maximum usable fuel: 1572 lbs/262 USG.
Best rate of climb: 1940 fpm @ 111 kts.
Climb gradient: 1049 ft/nm.
Rate of climb @ 8,000 ft: 1640 fpm.
Certificated ceiling: 30,000 ft.
8000ft cabin alt @: 21,700 ft.
Maximum single-engine rate of climb: 350 fpm @ 111 kts.
Single-engine climb gradient: 189 ft/nm.
Single-engine service ceiling: 14900 ft.
Maximum speed: 258 kts.
Max cruise speed: 241 kts.
Range max fuel/75% pwr: 1310nm/5.3hr.
Range max fuel / 55%: 1457nm/7.3hr.
75% cruise: 242 kt.
55% cruise: 201 kt.
Cruise @ 65% pwr @ 8,000ft: 190 kts.
Cruise @ 65% power @ 18,000ft: 208 kts.
Fuel flow @ 65% pwr @ 18,000 ft: 230 pph.
Endurance at 65 % pwr @ 18,000 ft: 6.7 hrs.
Max range: 1,487 nm.
Stalling speed clean: 83 kts.
Stalling speed gear/flaps down: 74 kts.
Turbulent-air penetration speed: 150 kts.
Takeoff Dist 50 ft obstacle: 2,323 ft.
Landing Dist 50 ft obstacle: 2,293 ft.
Cessna CE-414 Chancellor
To provide the pressurised 414 twin-engined transport, Cessna married the basic fuselage of the Model 421 with the wing developed for the Model 401. The resulting aircraft was flown for the first time on 1 November 1968 and certificated during the following August. New features introduced on the aircraft included engine cowlings with flush intakes to improve engine cooling and an accurate fuel monitoring system developed by Cessna to provide better fuel management.
From the time of its introduction until 1976, improvements introduced for the Model 402 were reflected in the Model 414, and in that year the name Chancellor was adopted. It was available for 1976 in standard and Model 414 II versions, the latter incorporating a package of factory-installed avionics and equipment.
After 513 of the original Model 414s had been built, Cessna combined the air¬frame that was developed for the Golden Eagle in 1978 with the 310 hp engines of the 414 to produce the 414A Chancellor. The engines are direct drive Continental TSIO 520s. The gross weight and useful load of the new airplane both are substantially greater than those of the old 414, which gives it much better payload and endurance numbers and makes it a more viable corporate transport. The pressure differential five pounds per square inch is greater so that the airplane can cruise at higher altitudes. Major changes included a redesigned and increased-span wing incorporating integral fuel tanks and more baggage capacity in an extended nose.
Versions available between 1978 and 1986, were the standard Model 414A Chancellor, the Chancellor II and later the Chancellor III, all with differing factory installed avionic/equipment packages. When Model 414/414A production ended in 1986 a total of 1,067 variants had been built.
The old 414’s service ceiling was 11,350 feet, and with the same engines and gross weight 400 pounds greater, the new airplane does 19,850 feet. The new airplane has four and a half feet more span as well as 30 more square feet of wing area, and these two factors do wonders for single engine ceiling.
On the old 414, fuel was carried in as many as six tanks, only two of which were standard equipment. Fuel management included the operation of transfer pumps, the monitoring of fuel return and the bother of tank selection. The new air¬plane carries a standard 103 gallons in each wing, virtually no management is required and the total capacity is greater than was available with all six tanks on the 414.
Scenic Air Lines, in 1977, acquired from American Jet Industries engineering and manufacturing rights for turboprop conversions of Cessna Models 402 and 414, now known as Turbo Star 402 and Turbo Star Pressurised 414.
Variations:
Riley Super 414
CE-414
Engine: 2 x Continental TSIO-520-N, 310 hp.
Seats: 7.
Wing loading: 32.4 lb/sq.ft.
Pwr loading: 10.2 lb/hp.
Gross wt: 6350 lb.
Empty wt: 4126 lb.
Equipped useful load: 1889 lb.
Payload max fuel: 671 lb.
Range max fuel/75% pwr: 1168nm/5.1hr.
Range max fuel / 55%: 1309nm/7.2hr.
Ceiling: 30,100 ft.
75% cruise: 225 kt.
55% cruise: 183 kt.
Vmc: 84 kt.
Stall: 74-86 kt.
1.3 Vso: 96 kt.
ROC: 1580 fpm.
SE ROC: 240 fpm @ 105 kt.
SE ceiling: 11,350 ft.
Min field length: 2350 ft.
Fuel cap: 600/1218 lb.
Cabin pressure: 4.2 psi.
CE-414A Chancellor
Engines: Continental TSIO-520-NB, 310 hp, 231kW.
TBO: 1400 hrs.
Props: McCauley 3-blade, 76.5-in.
Seats: 6/8.
Length: 11.09 m / 36 ft 5 in.
Height: 3.49 m / 11 ft 5 in.
Wingspan: 13.45 m / 44 ft 2 in.
Wing area: 20.98 sq.m / 225.83 sq ft.
Wing aspect ratio: 8.6.
Wing loading: 29.7 lb/sq.ft.
Power loading: 10.8 lb/hp.
Maximum ramp weight: 6785 lbs.
Maximum takeoff weight: 3062 kg / 6750 lbs.
Standard empty weight: 4368 lbs.
Maximum useful load: 2417 lbs.
Zero-fuel weight: 6515 lbs.
Maximum landing weight: 6750 lbs.
Wing loading: 29.9 lbs/sq.ft.
Power loading: 10.9lbs/hp.
Maximum usable fuel: 1236 lbs/204 USG.
Best rate of climb: 1520 fpm @ 108 kts.
Climb gradient: 853 ft/nm.
Rate of climb @ 8,000 ft: 1400 fpm.
Certificated ceiling with oxygen equipment: 30,000 ft.
Certificated ceiling without oxygen equipment: 25,000 ft.
8000ft cabin alt @: 21700 ft.
10,000ft cabin alt at: 26,500 ft.
Maximum single-engine rate of climb: 290 fpm @ 108 kts.
Single-engine climb gradient: 161 ft/nm.
Single-engine service ceiling: 19850 ft.
Maximum speed: 235 kts.
Max cruise, 77.5 % power at 24,500 ft: 225 kts.
Duration at max cruise: 5.67 hrs.
Cruise @ 65% pwr @ 8,000ft: 177 kts.
Cruise @ 65% power @ 18,000ft: 190 kts.
Fuel flow @ 65% pwr @ 18,000 ft: 180 pph.
Endurance at 65% pwr @ 18,000 ft: 6.5 hrs:
Econ cruise, 60.8% power at 20,000 ft: 187 kts.
Duration at econ cruise: 7.14 hrs.
Stalling speed clean: 82 kts.
Stalling speed gear/flaps down: 72 kts.
Turbulent-air penetration speed: 144 kts.
Takeoff Dist 50 ft obstacle: 2,595 ft.
Landing dist 50 ft obstacle: 2,393 ft.
Pressurization differential: 5.0 psi.
1980 Cessna 414A
Engines: RAM Overhauled TSIO-520-B, 335 hp
TBO: 1600 hour
Propellers: McCauley Series Saber Tip C500, Model 3AF32CC515, 3 Bladed
Prop TBO: 2000
Gross Ramp Weight: 7140 lb
Max Gross Takeoff Weight: 7105 lb
Empty Weight: 5120.72 lb
Useful Load: 1979.28 lb
Useful load W/full main tanks (206USG): 743.28 lb
Nose Baggage capacity: 332 lb
Fuel burn: 35.8GPH @ 185-195K @ 16000 – 17000 Ft.
Range with 206USG: 800 miles w/ 1 hr reserve.
Seats: 7 / 8
CIDC Turbo Star 414 / Cessna 414
Engines: 2 x Allison 250-B17B, 420 hp.
Seats: 6/8.
Wing loading: 33.5 lb/sq.ft.
Pwr loading: 7.7 lb/hp.
Max TO wt: 6525 lb.
Empty wt: 3705 lb.
Equipped useful load: 2492 lb.
Payload max fuel: 534 lb.
Range max fuel/cruise: 996 nm/4.4 hr.
Range max fuel /range: 1390 nm/ 6.7 hr.
Service ceiling: 25,000 ft.
Max cruise: 226 kt.
Max range cruise: 209 kt.
Vmc: 81 kt.
Stall: 70-85 kt.
1.3 Vso: 91 kt.
ROC: 2180 fpm.
SE ROC: 510 fpm @ 86 kt.
SE ceiling: 13,800 ft.
Min field length: 1290 ft.
Fuel cap: 1512/1958 lb.
Cessna CE-411
When flown for the first time on 18 July 1962, the Cessna Model 411 then represented the company’s largest business aircraft. Generally similar in configuration to the Model 310, it differed by having slightly increased wing span and area, a lengthened fuselage, more powerful 254kW Continental GTSIO-520-C flat-six turbocharged engines and accommodation for a crew of two and four to six passengers. Priced at $120,000, the 6-7 place was indicating 240mph optimum cruise at 22,000 ft with a range over 1000 mi with standard fuel, in tests.
Deliveries begin of the Model 411 in 1965, but production of the Model 411 was discontinued in June 1978, after the production of 400 examples, a small number of which were supplied to the French air force.
Engines: 2 x 254kW Continental GTSIO-520-C
Gross weight: 6500 lb
Top speed: 265 mph
Cruise: 230 mph at 16,000 ft
Wingspan: 39.86 ft
Length: 33 ft
Height: 11.1 ft
Price: $120,000
