Main Menu

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.



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.




Copyright © 2021 all-aero. All Rights Reserved.
Joomla! is Free Software released under the GNU General Public License.