ATrainer aircraft
Lockheed CP-140 Aurora
Maritime patrol aircraft (CP-140) MPA trainer aircraft (CP-140A)
Credit
Ken Mist · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
Loading the evidence…
Preparing your view.
Preparing your view.
ATrainer aircraft
Maritime patrol aircraft (CP-140) MPA trainer aircraft (CP-140A)
At a glance
Measured figures
CP-140 Aurora · Length
Single sourceCP-140 · Length
Single sourceConfiguration
| Specification | Lockheed CP-140 Aurora | SIAI-Marchetti SF.260 |
|---|---|---|
| Type | Maritime patrol aircraft (CP-140) MPA trainer aircraft (CP-140A)[source] | Trainer /Light attack[source] |
| Manufacturer | Lockheed Corporation[source] | SIAI-Marchetti Aermacchi Alenia Aermacchi Leonardo S.p.A.[source] |
| Status | Active (CP-140M only)[source] | In service[source] |
| Primary user | Royal Canadian Air Force[source] |
SF-260M · Length
Single source7.10 m (23 ft 4 in)[source]
Gross; CP-140 Aurora · Gross weight · Maximum gross weight
Single sourceGross; CP-140 · Gross weight
Single source61,362 lb (27,833 kg)[source]
64,410 kg[source]CP-140 Aurora · Maximum gross weight
Empty; SF-260M · Empty weight
Single sourceGross; SF-260M · Gross weight
Single sourceMaximum; CP-140 Aurora · Maximum speed · Maximum speed
Single sourceMaximum; CP-140 · below cruise ceiling
Single source375 kn (432 mph, 694 km/h) below cruise ceiling[source]
750 km/h[source]CP-140 Aurora · Maximum speed
Cruise; SF-260M · at 75% power at 1,500 m (4,900 ft)
Single sourceMaximum; SF-260M · at sea level
Single sourceCP-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]
SF-260M · 1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine
Single source1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine, 190 kW (260 hp)[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]
SF-260M · 1,500 ft/min
Single source7.6 m/s (1,500 ft/min)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Number built | 21 (18 CP-140M + 3 CP-140A)[source] | 900 (2012)[source] |
|---|
| Introduction date | 1980[source] | April 1966 (FAA certification)[source] |
|---|
| First flight | 22 March 1979 (CP-140)[source] | 15 July 1964[source] |
|---|
| Retired | 2011 (CP-140A only)[source] | — |
|---|
| Developed from | Lockheed P-3 Orion[source] | — |
|---|
| Fuel capacity | 7,661 imp gal (9,200 US gal; 34,828 L) usable fuel in one fuselage tank and four wing integral tanks[source] | internal: 235 L (62 US gal; 52 imp gal) usable[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] | — |
|---|
| Aspect ratio | 7.5[source] | 6.3:1 excluding tip-tanks[source] |
|---|
| Airfoil | root: NACA 0014 (modified) ; tip: NACA 0012 (modified)[source] | root: NACA 641 1 -212 (modified); tip: NACA 641 1 -210 (modified)[source] |
|---|
| Propellers | 4-bladed Hamilton Standard 54H60, 13 ft 6 in (4.11 m) diameter constant-speed fully-feathering reversible-pitch propellers[source] | 2-bladed Hartzell HC-C2YK-1BF/8477-8R constant-speed propeller , 1.93 m (6 ft 4 in) diameter[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] | — |
|---|
| Country of origin | United States[source] United States[source] | — |
|---|
| Designer | — | Stelio Frati[source] |
|---|
| Primary users | — | Italian Air Force Libyan Air Force Philippine Air Force Belgian Air Force[source] |
|---|
| Manufactured | — | 1964–2017[source] |
|---|
| Capacity | — | 1 passenger[source] |
|---|
| Stall speed | — | 126 km/h (78 mph, 68 kn) flaps and landing gear down[source] |
|---|
| Never exceed speed | — | 436 km/h (271 mph, 235 kn)[source] |
|---|
| g limits | — | +6 -3 at max aerobatic T-O weight[source] |
|---|
| Take-off run | — | 384 m (1,260 ft)[source] |
|---|
| Landing run | — | 345 m (1,132 ft)[source] |
|---|
| Take-off run to 15 m (50 ft) | — | 606 m (1,988 ft)[source] |
|---|
| Landing run from 15 m (50 ft) | — | 606 m (1,988 ft)[source] |
|---|
| National origin | — | Italy[source] |
|---|
| Time to altitude | — | 1,500 m (4,900 ft) in 4 minutes 2,300 m (7,500 ft) in 6 minutes 50 seconds 3,000 m (9,800 ft) in 10 minutes[source] |
|---|
Maximum take-off; SF-260M · Max takeoff weight
Single source