Credit
Alan Wilson from Peterborough, Cambs, UK · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
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BTrainer aircraft
Maritime patrol aircraft (CP-140) MPA trainer aircraft (CP-140A)
At a glance
Measured figures
1976 150M Commuter II · Length
Single source23 ft 11 in (7.29 m)[source]
CP-140 Aurora · Length
Configuration
| Specification | Cessna 150 | Lockheed CP-140 Aurora |
|---|---|---|
| Crew | one[source] | Mission minimum 8, typically 12 to 15[source] |
| Type | Light utility aircraft, basic trainer[source] | Maritime patrol aircraft (CP-140) MPA trainer aircraft (CP-140A)[source] |
| Manufacturer | Cessna[source] | Lockheed Corporation[source] |
| Status | In service[source] | Active (CP-140M only) |
CP-140 · Length
Single sourceEmpty; 1976 150M Commuter II · Empty weight
Single sourceMaximum take-off; 1976 150M Commuter II · Max takeoff weight
Single source1,122 lb (509 kg)[source]
1,600 lb (726 kg)[source]
Gross; CP-140 Aurora · Gross weight · Maximum gross weight
Single sourceGross; CP-140 · Gross weight
Single sourceCruise; 1976 150M Commuter II · at 10,000 ft (3,050 m) (econ cruise)
Single sourceMaximum; 1976 150M Commuter II · at sea level
Single source109 kn (125 mph, 202 km/h) at sea level[source]
82 kn (94 mph, 152 km/h) at 10,000 ft (3,050 m) (econ cruise)[source]
Maximum; CP-140 Aurora · Maximum speed · Maximum speed
Single sourceMaximum; CP-140 · below cruise ceiling
Single source1976 150M Commuter II · econ cruise, standard fuel
Single source420 nmi (480 mi, 780 km) (econ cruise, standard fuel)[source]
1976 150M Commuter II · 1 × Continental O-200-A air-cooled horizontally-opposed engine
Single source1 × Continental O-200-A air-cooled horizontally-opposed engine, 100 hp (75 kW)[source]
CP-140 · 4 × Allison T56-A-14-LFE turboprop engines each
Single source4 × Allison T56-A-14-LFE turboprop engines, 4,909 hp (3,661 kW) each[source]
1976 150M Commuter II · 670 ft/min (
Single source670 ft/min (3.4 m/s)[source]
CP-140 · on station at 1,000 nmi (1,151 mi; 1,852 km) radius
Single source8 hours 12 minutes on station at 1,000 nmi (1,151 mi; 1,852 km) radius[source]
CP-140 · Hardpoints: 8 in weapons bay; 10 under-wing from capacity with a capacity of
Single sourceCP-140 · total in weapons bay, with provisions to carry combinations of
Single sourceHardpoints: 8 in weapons bay; 10 under-wing from 611 to 2,450 lb (277 to 1,111 kg) capacity with a capacity of 4,800 lb (2,177 kg) total in weapons bay, with provisions to carry combinations of:[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Number built | 23,839[source] | 21 (18 CP-140M + 3 CP-140A)[source] |
|---|
| Manufactured | 1958–1977[source] | — |
|---|
| First flight | September 12, 1957[source] | 22 March 1979 (CP-140)[source] |
|---|
| Variant | Cessna 152[source] | — |
|---|
| Capacity | one passenger (plus two children not exceeding 120 lb (54 kg) on optional bench seat in baggage space)[source] | — |
|---|
| Fuel capacity | 22.5 US gal (18.7 imp gal; 85 L) usable internal fuel[source] | 7,661 imp gal (9,200 US gal; 34,828 L) usable fuel in one fuselage tank and four wing integral tanks[source] |
|---|
| Aspect ratio | 6.7:1[source] | 7.5[source] |
|---|
| Airfoil | NACA 2412[source] | root: NACA 0014 (modified) ; tip: NACA 0012 (modified)[source] |
|---|
| Propellers | 2-bladed McCauley 1A102/OCM metal fixed-pitch propeller, 5 ft 9 in (1.75 m) diameter[source] | 4-bladed Hamilton Standard 54H60, 13 ft 6 in (4.11 m) diameter constant-speed fully-feathering reversible-pitch propellers[source] |
|---|
| Stall speed | 42 kn (48 mph, 78 km/h) (flaps down, power off)[source] | — |
|---|
| Never exceed speed | 140 kn (160 mph, 260 km/h)[source] | — |
|---|
| Take-off run to 50 ft (15 m) | 1,385 ft (422 m)[source] | — |
|---|
| Landing run from 50 ft (15 m) | 1,075 ft (328 m)[source] | — |
|---|
| Country of origin | United States[source] | United States[source] United States[source] |
|---|
| Primary user | — | Royal Canadian Air Force[source] |
|---|
| Introduction date | — | 1980[source] |
|---|
| Retired | — | 2011 (CP-140A only)[source] |
|---|
| Developed from | — | Lockheed P-3 Orion[source] |
|---|
| Hardpoints | — | 8 in weapons bay; 10 under-wing from 611 to 2,450 lb (277 to 1,111 kg) capacity with a capacity of 4,800 lb (2,177 kg) total in weapons bay, with provisions to carry combinations of: Other: signal chargers, smoke markers , illumination flares[source] |
|---|
| Maximum transit speed | — | 395 kn (455 mph; 732 km/h) at optimum altitude[source] |
|---|
| FAR balanced field length | — | 7,900 ft (2,408 m)[source] |
|---|
| Take-off distance to 50 ft (15 m) | — | 6,000 ft (1,829 m)[source] |
|---|
| Landing distance from 50 ft (15 m) | — | 3,200 ft (975 m) at 114,000 lb (51,710 kg) landing weight[source] |
|---|
| Other | — | signal chargers, smoke markers , illumination flares[source] |
|---|
| Rockets | — | air-to-surface rockets can be fitted after a minor retrofit.[source] |
|---|
| Bombs | — | Mk 46 Mod V torpedoes, conventional bombs[source] |
|---|