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
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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 | UTVA 75 |
|---|---|---|
| Type | Maritime patrol aircraft (CP-140) MPA trainer aircraft (CP-140A)[source] | Military and civilian trainer aircraft[source] |
| Manufacturer | Lockheed Corporation[source] | UTVA[source] |
| Status | Active (CP-140M only)[source] | Active[source] |
| Primary user | Royal Canadian Air Force[source] | Serbia Air Force |
UTVA 75A21 · Length
Single source7.11 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; UTVA 75A21 · equipped
Single sourceMaximum take-off; UTVA 75A21 · Max takeoff 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; UTVA 75A21 · Cruise speed
Single sourceMaximum; UTVA 75A21 · Maximum speed
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]
UTVA 75A21 · 1 × Lycoming IO-360-B1F 4-cyl. air-cooled horizontally-opposed piston engine
Single source1 × Lycoming IO-360-B1F 4-cyl. air-cooled horizontally-opposed piston engine, 134 kW (180 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]
UTVA 75A21 · 890 ft/min
Single source4.5 m/s (890 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] | — |
|---|
| Introduction date | 1980[source] | 1978[source] |
|---|
| First flight | 22 March 1979 (CP-140)[source] | 19 May 1976[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] | standard:160 L (42 US gal; 35 imp gal): with drop tanks 360 L (95 US gal; 79 imp gal)[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] | 2 with a capacity of 150 kg (330 lb) each, with provisions to carry combinations of:[source] |
|---|
| Aspect ratio | 7.5[source] | 6.5[source] |
|---|
| Airfoil | root: NACA 0014 (modified) ; tip: NACA 0012 (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/F7666A variable-pitch metal propeller[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] | 450 m grass at Sea Level[source] |
|---|
| Other | signal chargers, smoke markers , illumination flares[source] | 2 × MAC-AA-52 container with 7.62 mm , or 2 × cargo container 100 kg capacity, or 2 × drop tanks[source] |
|---|
| Rockets | air-to-surface rockets can be fitted after a minor retrofit.[source] | 2 × RL 128-02 128 mm (HVAR-5), or 2 × 57 millimetres (2.2 in) rocket launchers with 12 rockets[source] |
|---|
| Bombs | Mk 46 Mod V torpedoes, conventional bombs[source] | 2 × 120 kg bombs, or 4 × 50 kg bombs[source] |
|---|
| Country of origin | United States[source] United States[source] | — |
|---|
| National origin | — | Yugoslavia[source] |
|---|
| Capacity | — | 210 kg (460 lb) max[source] |
|---|
| Stall speed | — | 95 km/h (59 mph, 51 kn) flaps up at idle[source] |
|---|
| Never exceed speed | — | 270 km/h (168 mph, 146 kn)[source] |
|---|
| g limits | — | +4.4 -2.2[source] |
|---|
| Takeoff distance to 50 ft (15 m) | — | 501 m grass at Sea Level[source] |
|---|
| standard | — | (model 75) KING KR85 ADF and KING KY 195B[source] |
|---|
| optional | — | (model 75A catalog only) KING KR87 ADF, RNAV KING KNS81 VOR/LOC: KING KN 53, KING KY 197 Indicators: HSI KING KI 525A, and RMI KING KI 229, DME:KING KN 62A, Transponder: KING KT 79, Audio panel: KING KMA 24[source] |
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