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.
Riley Super 414
Engine: 2 x Continental TSIO-520-N, 310 hp.
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.
Engines: Continental TSIO-520-NB, 310 hp, 231kW.
TBO: 1400 hrs.
Props: McCauley 3-blade, 76.5-in.
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.
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.