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Cessna CE-210 Centurion

 

cessna210
CE-210


Cessna engineers fitted a retractible undercarriage to a model 182B resulting in the 210. The first 210s were flown in 1959, and the airplane has always been a 160- knot cruiser that can go 175 knots. When its hydraulically activated landing gear is retracted, the gear doors seal it completely within the fuselage. (The 1979 model no longer has the all-covering doors; the main gear nestles up into open wheel wells. As a result, the gear extension speeds have been raised 25 knots, and a more simple design has been obtained without any loss in performance.) The first production aircraft flew in December 1959 powered by a 194kW Continental IO-470-E engine. The initial 210s carried four people; then in 1964, two seats were added. The four seat 210s were made from 1960 to 1963, with wing struts, two windows per side and no rear window. The early mod-els are powered by the 260-horsepower, fuel-injected Continental with a 1,200-hour TBO. Those 210s carried 65 USG of fuel, but in 1962, when the option was first offered, most buyers chose the 84-gallon long-range tanks. The early 210s gross at 2,900 pounds, with a standard useful load of about 1,165 pounds.
The 1961 model introduced two more cabin windows, additional headroom and an improved heating and ventilating system, and by 1963 an autopilot was offered as an option. In January 1965 the Model 210E Centurion had supplanted earlier versions and was powered by a 213kW Continental IO-520-A. The Model 210F followed in 1966.
The Centurion, a heavier, bigger, more-powerful 210, was introduced in 1964. The first Centurion had a 285-hp Continental, still fuel injected, still with a 1,200-hour TBO. The gross weight was increased to 3,100 pounds, which raised the useful load by 105 pounds. The cabin was expanded to seat six with the addition of two tiny rear seats that can be folded flush with the baggage compartment floor.


In 1966 the first turbocharged model became available in the form of the T210F Turbo-System Centurion with a 213kW Continental TSIO-520C; the extra power conferred a useful increase in performance, particularly in altitude. A new wing, first flown on a T210 in June 1965, was later introduced on production aircraft, and eliminated the need for external bracing struts. The turbocharged version eventually outsold the basic model two to one.


In 1967, the Centurion lost its wing struts, took on two standard 45-gallon fuel tanks and gained 100 pounds, for a gross of 3,400. With a 1,960-pound empty weight, the full-fuel payload went to about 905 pounds.


In 1969, the TBO on the engine went up to 1,500 hours. The following year, the cabin was enlarged and the rear seats expanded to make the airplane an honest six-seater. The gross weight went up again, this time to 3,800 pounds, and the useful load rose to 1,720, for a full-fuel payload of about 1,186 pounds. At the same time, the old, square passenger windows were replaced by a three-foot long window on each side, aft of the doors. The engine, still rated at 285 hp, was allowed to develop 300 hp for takeoff and five minutes of climb-out.


By 1970 Cessna had dropped its suffix letter system from model numbers and in that year introduced two new versions, the Centurion II and Turbo Centurion II which incorporated a factory-installed package of avionics and equipment as standard, these being produced alongside the Centurion and Turbo Centurion. By then the Centurions were of six-seat capacity and offered powerplant options of a 224kW Continental IO-520-L for the Centurion and a 213kW TSIO-520H for the Turbo Centurion.
In 1975, the three-blade prop became standard.


The 210L models featured larger picture windows which greatly im-proved the visibility for the rear seat passengers.


The Turbo Centurion was first built with strutted wings. That was remedied in 1967 with a center section to make the Turbo Centurion's wing full cantilever, eliminating the struts. A new airfoil was incorporated at the same time. Gone was the classic Cessna wing, swapped for a new laminar-flow section. The strutless-wing arrangement added 95 pounds to the empty weight, increased the stalling speed six knots, resulted in a 154 fpm decrease in rate of climb (largely from a 100-pound gross weight increase to preserve useful load) and improved the cruising speed but two knots. The first strutless Turbo Centurion almost had too much dihedral in the wings but that was quickly remedied.


The Centurion's performance has been greatly improved, too, through a series of small but important aerodynamic refinements. The 1975 Centurion is basically the same airframe as that used since 1970, when six full-size seats were first offered. It uses the same engine, also, but incorporates such features as a retractable cabin step which gives it 10 knots additional cruise at maximum power settings.


In November 1977 a new pressurised version of the Model 210, the Pressurized Centurion, was announced. Generally similar to the standard Centurion, it differed by having a pressure cabin and a 231kW Continental TSIO-520-P which incorporated a high-capacity turbocharger to support the pressurisation system, and like the earlier models was available in standard and Pressurized Centurion II versions.

 

Cess-P210-pit
Cessna P210N Pressurized Centurion II

 

The 210R model, with a longer span stabiliser and cambered wingtips, was produced for the 1986 sales year and only 112 were produced in the final year of production.
All six versions remained available until 1986 when sales slowed down and at the end of 1987 when production ceased, a total of 8,453 Model 210s and Centurions had rolled off the line together with 851 Pressurized Centurions.


Turbocharged Centurions established several world records in their class: including time-to-height records, a round the world speed record of 204km/h, and an altitude record of 12905m established on 13 May 1967.

1973 Cessna Centurion T210L
Base price: US$544,295
Engine: Continental TSIO-520H, 285 hp to 17,000 ft
TBO (hrs.): 1400
Fuel type: 100/100LL
Propeller type: McCauley CS/3-blade
Landing gear type: Tri./Retr.
Max ramp weight (lbs): 3800
Gross weight (lbs.): 3800
Landing weight (lbs.) 3800
Empty weight, std. (lbs.): 2195
Useful load, std. (lbs.): 1605
Useful fuel, std (gals.): 89
Payload, full std. fuel (lbs.): 1071
Wingspan: 36 ft. 9 in.
Overall length: 28 ft. 3 in.
Height: 9 ft. 7 in.
Wing area (sq. ft.): 175.1
Wing loading (lbs./sq.ft.): 21.7
Wheel size (in.): 6.00 x 6
Power loading (lbs./hp):12.3
Seating capacity: 6
Cabin doors: 2
Cabin width (in.): 45.5
Cabin height (in.): 48   
Cruise speed (kts.) 80% power: 198@20,000 ft.
Cruise speed (kts.) 70% power: 190@20,000 ft.     
Fuel consumption (USgph.) 80% power: 17.2
Fuel consumption (USgph.) 70% power: 15.5
Range (plus reserve, nm) 80% power: 830
Range (plus reserve, nm) 70% power: 880
Vso (kts.): 57
Best rate of climb, SL (fpm): 1115
Service ceiling (ft.): 28,500
Takeoff distance (ft.): 1170
Takeoff over 50 ft. obstacle (ft.): 2030
Landing distance (ft.): 765
Landing over 50 ft. obstacle (ft.): 1500  

1977 Cessna T210M
Engine: Continental TSIO-520H, 310 hp
TBO hr: 1400
Propeller type: Const. spd.
Landing gear type: Tri/Retr.
Gross weight (lbs.): 3800
Empty weight, std. (lbs.): 2324
Useful load, std. (lbs.): 1476
Fuel (USgals.): 89
Wingspan: 36 ft. 9 in.
Overall length: 28 ft. 2 in.
Height: 9 ft. 5 in.
Wing area (sq. ft.):175
Seating capacity: 6
Cabin width (in.): 42.5
Cabin height (in.): 48
Baggage capacity (lbs.): 240
Cruise speed (kt) 75% power @ 24,000 ft: 198
Cruise speed (kt) 65% power @ 6,500 ft.: 168   
Max range (w/ reserve) (nm) 75% power: 870
Max range (w/ reserve) (nm) 65% power: 880  
Fuel consumption (USgph) 70% power: 17.8
Fuel consumption (USgph) 65% power: 14.0   
Estimated endurance (65% power with 1-hr. reserve): 5 hrs. 30 mins.
Stall speed (gear, flaps down) (knots): 56
Best rate of climb (fpm): 1030
Service ceiling (ft.): 28,500
Takeoff ground roll (ft.): 1150
Landing ground roll (ft.): 765

CE-210N
Engine: 1 x Continental IO-520-L, 300 hp.
TBO: 1700 hrs.
Prop: McCauley 3 blade, constant speed 80 in.
Seats: 6.
Length: 28.2 ft.
Height: 9.7 ft.
Wingspan: 36.8 ft.
Wing area: 175 sq.ft.
Wing aspect ratio: 7.7.
Max ramp wt: 3812 lbs.
Max take off wt: 3800 lbs.
Standard empty wt: 2153 lbs.
Max useful load: 1659 lbs.
Max landing wt: 3800 lbs.
Wing loading: 21.7 lbs/sq.ft.
Power loading: 12.7 lbs/hp.
Max useable fuel: 522 lbs.
Climb rate: 950 fpm @ 96 kts.
Climb gradient: 597 ft/nm.
Rate of climb @ 8000 ft: 560 fpm.
Service ceiling: 17,300 ft.
Max speed: 175 kts.
Cruise @ 65% power @ 8,000ft: 160 kts.
Fuel flow @ 65% power @ 8,000ft: 82 pph.
Endurance @ 65% power @ 8,000ft: 6.2 hr.
Stalling speed clean: 65 kts.
Stall speed gear/flaps down: 56 kts.
Turbulent air penetration speed: 125 kts.
Retractable nose wheel undercarriage.

1983 Cessna Turbo 210N Centurion II

Engine: Continental TSIO-520-R
Takeoff power: 310 hp @2700 rpm / 36.5-in manifold pressure
Max continuous power: 285 hp @2600 rpm /  35-in. manifold pressure
TBO hrs.: 1600
Fuel Type:100/100LL
Propeller type/diameter: McCauley CS/80 in
Landing Gear type: Tri./Retr.
Max ramp weight (lbs.): 4016
Gross weight (lbs.): 4000
Landing weight (lbs.): 3800
Empty weight, std. (lbs.): 2303
Useful load, std. (lbs.): 1697
Payload (lbs.): 896 with 120-USgallon auxillary tanks
Usable fuel, std. (USgals.): 90
Oil capacity (qts.): 11
Wingspan: 39 ft. 9 in With Flint Tip Tanks
Overall length: 28 ft. 2 in.
Height: 9 ft. 8 in.
Wing area (sq. ft.):181
Wing loading (lbs./sq. ft.): 22.9
Power loading (lbs./hp.): 12.9
Wheel base (in.): 72
Seating capacity: 6
Cabin doors: 2
Cabin width (in.): 41.8
Cabin height (in.): 48
Baggage capacity (lbs.): 370
Cruise speed (kt) 75% power @ 2000/24,000 ft.: 157/192
Cruise speed (kt) 65% power @ 2000/24,000 ft.: 150/175
Cruise speed (kt) 45% power @ 2000/24,000 ft.: 135/154
Range (w/45-min. reserve) (nm) 75% power @ 2000/24,000 ft.: 1000/1075
Range (w/45-min. reserve) (nm) 65% power @ 2000/24,000 ft.: 1200/1125
Range (w/45-min. reserve) (nm) 45% power @ 2000/24,000 ft.: 1350/1200
Fuel consumption (est. @ .44 lbs./hp/hr. sfc gph) 75% power: 17
Fuel consumption (est. @ .44 lbs./hp/hr. sfc gph) 65% power: 15
Fuel consumption (est. @ .44 lbs./hp/hr. sfc gph) 45% power: 12
Estimated endurance (65%) (hrs): 8.0
Vso (kts.): 58
Best rate of climb (fpm): 930
Best rate of climb, 8,000 ft. (fpm): 850
Service ceiling (ft.): 27,000
Takeoff ground roll (ft.): 1300
Takeoff over 50-ft. obstacle (ft.): 2160
Landing ground roll (ft.): 765
Landing over 50-ft. obstacle (ft.): 1500

CE-P210N
Engine: 1 x Continental TSIO-520-AF, 310 hp.
TBO: 1600 hrs.
Prop: McCauley 3 blade, constant speed 80 in.
Seats: 6.
Length: 28.2 ft.
Height: 9.6 ft.
Wingspan: 36.8 ft.
Wing area: 175 sq.ft.
Wing aspect ratio: 7.7.
Max ramp wt: 4016 lbs.
Max take off wt: 4000 lbs.
Standard empty wt: 2426lbs.
Max useful load: 1590 lbs.
Max landing wt: 3800 lbs.
Wing loading: 22.9 lbs/sq.ft.
Power loading: 12.9 lbs/hp.
Max useable fuel: 522 lbs.
Climb rate: 945 fpm @ 100 kts.
Climb gradient: 567 ft/nm.
Rate of climb @ 8000 ft: 860 fpm.
Certificated ceiling: 23,000 ft.
8000ft cabin altitude at 17,350 ft.
Max speed: 201 kts.
Cruise @ 65% power @ 8,000ft: 154 kts.
Cruise @ 65% pwr @ 18,000 ft: 166 kts.
Fuel flow @ 65% power @ 18,000ft: 88 pph.
Endurance @ 65% power @ 18,000ft: 5.7 hr.
Stalling speed clean: 67 kts.
Stall speed gear/flaps down: 58 kts.
Turbulent air penetration speed: 130 kts.
Retractable nose wheel undercarriage and pressurised.

1985 Cessna P210R
Engine: Continental TSIO-520CF, 325
TBO hr: 1600
Propeller type: CS
Landing Gear type: Tri./Retr.
Gross weight (lbs.): 4100
Empty weight, std. (lbs.): 2471
Useful load, std. (lbs.): 1629
Fuel (lbs.): 115
Wingspan: 33 ft. 5 in.
Overall length: 28 ft. 4 in.
Height: 9 ft. 8 in.
Seating capacity: 6
Cabin width (in.): 42
Cabin height (in.): 48
Baggage capacity (lbs.):200
Cruise speed (kt) 75% power: 210
Cruise speed (kt) 65% power: 196   
Max range (w/ reserve) (nm) 75% power: 1045
Max range (w/ reserve) (nm) 65% power: 1137
Fuel consumption (USgph) 75% power: 18.2
Fuel consumption (USgph) 65% power: 15.8   
Estimated endurance (65% power with 1-hr. reserve) (hrs): 6 hrs.
Stall speed (gear, flaps down) (knots): 55
Best rate of climb (fpm): 1150
Service ceiling (ft.): 23,000
Takeoff ground roll (ft.): 1325
Landing ground roll (ft.): 840

CE-T210N
Engine: 1 x Continental TSIO-520-R, 310 hp. turbo charged
TBO: 1400-1500 hrs.
Fuel Type:100LL
Prop: McCauley 3 blade Q-Tip , constant speed 80 in.
Seats: 6.
Length: 28.2 ft.
Height: 9.8 ft.
Wingspan: 36.8 ft.
Wing area: 175 sq.ft.
Wingspan (ft.): 39.7, Flint wingtip tanks
Wing aspect ratio: 7.7.
Max ramp wt: 4016 lbs.
Max take off wt: 4000 lbs.
Standard empty wt: 2237 lbs.
Max useful load: 1779 lbs.
Payload, full std. fuel: 718lb
Max landing wt: 3800 lbs.
Wing loading: 22.9 lbs/sq.ft.
Power loading: 12.9 lbs/hp.
Usable fuel, std. (gals.): 88 main, 123 w/aux. tanks
Max useable fuel: 522 lbs.
Best rate of climb (SL fpm): 1035
Best rate of climb, 8,000 ft. (fpm): 840
Best climb speed: 100 kt
Climb gradient: 558 ft/nm.
Rate of climb @ 8000 ft: 845 fpm.
Service ceiling: 27,000 ft.
Max speed: 204 kts.
Cruise @ 65% power @ 8,000ft: 156 kts.
Cruise @ 65% pwr @ 18,000 ft: 167 kts.
Cruise speed (kts.) @ 10,000 ft 75% power: 174
Cruise speed (kts.) @ 10,000 ft 65% power: 164
Cruise speed (kts.) @ 10,000 ft 55% power: 157  
Fuel consumption (lb) 75% power: 94 pph
Fuel flow @ 65% power @ 18,000ft: 86 pph.
Fuel consumption (lb) 55% power: 73 pph
Endurance @ 65% power @ 18,000ft: 5.9 hr.
Max range (w/reserve, 75% power) (nm): 1235
Stalling speed clean: 67 kts.
Stall speed gear/flaps down: 58 kts.
Turbulent air penetration speed: 130 kts.
Undercarriage:  Retractable / nose wheel
Wheel track (ft.): 8.8
Cabin width (in.): 43
Cabin height (in.): 48
Baggage capacity (lbs.): 200
Takeoff ground roll (ft.): 1300
Takeoff over 50-ft. obstacle (ft.): 2160
Landing ground roll (ft.): 765
Landing over 50-ft. obstacle (ft.): 1500

1978 Pressurized Centurion
Engine: Continental TSIO-520-P, 310hp for takeoff, 285 maximum continuous.
TBO: 1,500 hrs.
Prop: three-blade, constant-speed, 80-in. diameter.
Length: 28 ft. 2 in.
Height: 9 ft. 5 in.
Wingspan: 36 ft. 9 in.
Wing area: 174.6 sq.ft.
Wing loading: 22.9 lb/sq.ft.
Power loading: 12.9 lb/hp.
Seats: 6.
Empty weight: 2588 lb.
Useful load: 1412 lb.
Payload with full fuel: 878 lb.
Gross wt: 4000 lb.
Useable fuel: 89 USG/534 lb.
Maximum landing weight 3,800 lbs.
Max ramp wt: 4,016 lbs.
Maximum rate of climb 930 fpm.
Certificated ceiling 23,000 ft.
Maximum speed 206 kts.
Max cruise, 79% power at 20,000 ft: 195kts.
Econ cruise, 55% power at 20,000 ft: 158 kts.
Duration at max cruise 4.7 hrs.
Duration at econ cruise (leaned to peak EGT) 7.3 hrs.
Stalling speed, clean, forward CG 73 kts.
Stalling speed, full flaps, forward CG 58 kts.
Pressurization differential 3.35 psi.
10,000-ft. cabin at 20,000 ft.
Max range: 926 nm.
ROC: 930 fpm.
Takeoff dist 50 ft obstacle: 2,160 ft.
Landing dist 50 ft obstacle: 1,500 ft.

O&N Aircraft Modifications Cessna 210 Silver Eagle
Engine: Allison 250-B17F/2, 450 shp
TBO hrs.: 3500
Fuel Type: Jet A, Jet A1, JP 8, limited avgas
Propeller make/type: 90-inch CS three-blade full-feather reversing
Landing Gear type: Tri./Retr.
Max ramp weight (lbs.): 4016
Gross weight (lbs.): 4000
Max landing weight (lbs.): 3800
Empty weight (lbs.): 2470
Useful load (lbs.): 1530
Payload, full fuel (lbs.): 1545
Usable fuel (USgals.): 114
Oil capacity (qts.): 12
Wingspan: 36 ft. 11 in.
Overall length: 29 ft. 6 in.
Height: 9 ft. 6 in.
Wing area (sq. ft.): 175
Wing loading (lbs./sq. ft.): 22.9
Power loading (lbs./hp.): 8.89
Wheel track (in.): 8 ft. 7 in.
Wheel size (in.): 6.00 x 6 main; 5.00 x 5 nose
Seating capacity: 6
Cabin doors: 1
Cabin width (in.): 41.75
Cabin height (in.): 57
Baggage capacity (lbs.): 181.5
Cruise speed (kts.): 215
Cruise speed (kt) @ 12,000 ft.: 200
Cruise speed (kt) @ 17,500 ft.: 215
Cruise speed (kt) @ 23,000 ft.: 208
Max range (w/ reserve) @ 12,000 ft: 570 nm
Max range (w/ reserve) @ 17,500 ft.: 860 nm
Max range (w/ reserve) @ 23,000 ft.: 910 nm
Fuel consumption (USgph): @ 12,000 ft.: 24.0
Fuel consumption (USgph): @ 17,500 ft.: 22.7
Fuel consumption (USgph): @ 23,000 ft.: 19.5
Estimated endurance (standard fuel)(hrs): 5.0
Stall speed (flaps up) (knots): 76
Stall speed (flaps down) (knots): 61
Best rate of climb (SL fpm): 2200
Service ceiling (ft.): 23,000
Takeoff ground roll (ft.): 600
Takeoff over 50 ft. obstacle (ft.): 900
Landing ground roll (ft.): 500
Landing over 50 ft obstacle (ft.): 1000

 


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