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Michal šenki · Public domain · Resized · Public domain · Source ↗ · Modified
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BSupport aircraft
American four- to six-seat twin-engined general aviation light aircraft ,
At a glance
Measured figures
L-59E · Length
Single source12.20 m (40 ft 0 in)[source]
PA-23-250F, normally aspirated · Length
Configuration
| Specification | Aero L-59 Super Albatros | Piper PA-23 |
|---|---|---|
| Type | Military trainer aircraft COIN[source] | Twin-engined light piston utility[source] |
| Manufacturer | Aero Vodochody[source] | Piper Aircraft[source] |
| Status | Out of production, in service[source] | — |
| Primary users | Czech Air Force Egyptian Air Force Tunisian Air Force[source] | — |
| Number built |
31 ft 2 + 3 ⁄ 4 in (9.519 m)[source]
Empty; L-59E · includes gun
Single sourceMaximum take-off; L-59E · Max takeoff weight
Single source4,030 kg (8,885 lb) (includes gun)[source]
7,000 kg (15,432 lb)[source]
Empty; PA-23-250F, normally aspirated · Empty weight
Single sourceMaximum take-off; PA-23-250F, normally aspirated · Max takeoff weight
Single sourceMaximum; L-59E · at 5,000 m (16,000 ft)
Single source865 km/h (537 mph, 467 kn) at 5,000 m (16,000 ft)[source]
L-59E · at 7,000 m (23,000 ft) (with maximum internal and external fuel)
Single source2,000 km (1,200 mi, 1,100 nmi) at 7,000 m (23,000 ft) (with maximum internal and external fuel)[source]
PA-23-250F, normally aspirated · at long-range cruise
Single source1,519 mi (2,445 km, 1,320 nmi) at long-range cruise[source]
PA-23-250F, normally aspirated · 2 × Lycoming IO-540 -C4B5 normally aspirated air-cooled flat-six piston engines each
Single source2 × Lycoming IO-540 -C4B5 normally aspirated air-cooled flat-six piston engines , 250 hp (190 kW) each[source]
L-59E · 1 × Lotarev DV-2 turbofan thrust
Single source1 × Lotarev DV-2 turbofan , 21.57 kN (4,850 lbf) thrust[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
80[source] |
6,976[source] |
| Manufactured | 1986–1996[source] | 1952–1981[source] |
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| First flight | 30 September 1986[source] | 2 March 1952[source] |
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| Developed from | Aero L-39 Albatros[source] | — |
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| Variant | Aero L-159 ALCA[source] | — |
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| Fuel capacity | 1,537 L (406 US gal; 338 imp gal) including tip tanks[source] | 140 US gal (120 imp gal; 530 L) usable fuel (normal), optional extra tanks with 40 US gal (33 imp gal; 150 L)[source] |
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| Stall speed | 185 km/h (115 mph, 100 kn) (flaps down)[source] | 68 mph (109 km/h, 59 kn) (flaps down)[source] |
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| Guns | one GSh-23L cannon in under-fuselage pod[source] | — |
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| Hardpoints | four underwing hardpoints with a capacity of inner hardpoints 500 kg (1,100 lb)capacity, outer hardpoints 250 kg (550 lb)[source] | — |
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| Country of origin | Czechoslovakia[source]Inventory Origin column; table 1, row 26, cell 2; revision 1374778711; retrieved 2026-10-01 | — |
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| Introduction date | — | 1954[source] |
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| Capacity | — | 5 passengers[source] |
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| Aspect ratio | — | 6.8:1[source] |
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| Airfoil | — | USA 35B (modified)[source] |
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| Propellers | — | 2-bladed Hartzell HC-E2YK-2RB constant-speed propellers[source] |
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| Never exceed speed | — | 277 mph (446 km/h, 241 kn)[source] |
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| Takeoff distance to 50 ft (15 m) | — | 1,695 ft (517 m)[source] |
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| Landing distance from 50 ft (15 m) | — | 1,695 ft (517 m)[source] |
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| Role | — | American four- to six-seat twin-engined general aviation light aircraft ,[source] |
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| National origin | — | United States[source] |
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| Source measurement | — | The PA-23 was the first twin-engined Piper aircraft, and was developed from a proposed "Twin Stinson" design, inherited when Piper bought the Stinson Division of the Consolidated Vultee Aircraft Corporation . The prototype PA-23 was a four-seat, low-wing, all-metal monoplane with a twin tail , powered by two 125 hp Lycoming O-290 -D piston engines; it first flew on March 2, 1952. The aircraft performed poorly, so it was redesigned with a single vertical stabilizer and an all-metal rear fuselage and more powerful 150 hp Lycoming O-320 -A engines.[source]Piper PA-23 · Design and development; only the objects and conditions stated in this passage Two new prototypes of the redesigned aircraft, named Apache , were built in 1953 and entered production in 1954; 1,231 Apaches were built. In 1958, the Apache 160 was produced with upgraded 160 hp (119 kW) engines; 816 were built. The Apache 160 was superseded in 1962 by the Aztec-derived 235 hp (175 kW) Apache 235 . With a 1962 price of $45,000, the Apache 235 featured the Aztec's engines and swept tail surfaces (119 built).[source]Piper PA-23 · Design and development / Apache; only the objects and conditions stated in this passage In 1959, Piper produced an upgraded version with 250 hp (186 kW) Lycoming O-540 engines and a swept vertical tail as the PA-23-250, and named it Aztec . The first models came in a five-seat configuration. In 1961, a longer-nosed variant, the Aztec B, entered production. Later Aztecs were equipped with Lycoming IO-540 fuel-injected engines and six-seat capacity, and remained in production until 1982. Turbocharged versions of the later models could fly at higher altitudes.[source]Piper PA-23 · Design and development / Aztec; only the objects and conditions stated in this passage PA-23 powered by two 160 hp O-320-B engines[source]Piper PA-23 · Variants / Apache; only the objects and conditions stated in this passage Apache with five seats and 235 hp O-540 engines, 118 built[source]Piper PA-23 · Variants / Apache; only the objects and conditions stated in this passage Apache G with modified rear fuselage, new fin and rudder and 250hp Lycoming O-540-A1D engines, 4811 built (including subvariants)[source]Piper PA-23 · Variants / Aztec; only the objects and conditions stated in this passage Aztec variant with gross weight reduced from 5,200 lb (2,400 kg) to 4,995 lb (2,266 kg). Produced in the late 1960s and early 1970s exclusively for the United Kingdom market.[source]Piper PA-23 · Variants / Aztec; only the objects and conditions stated in this passage On 18 April 1974, Aztec G-AYDE collided with Court Line Flight 95 , a BAC One-Eleven , at London Luton Airport after the pilot of the Aztec entered the active runway without clearance. He was killed and his passenger was injured. All 91 people on board the One-Eleven successfully evacuated after the takeoff was aborted.[source]Piper PA-23 · Accidents and incidents; only the objects and conditions stated in this passage Capacity: 5 passengers[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Length: 31 ft 2 + 3 ⁄ 4 in (9.519 m)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Wingspan: 37 ft 2 + 1 ⁄ 2 in (11.341 m)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Height: 10 ft 4 in (3.15 m)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Wing area: 207.56 sq ft (19.283 m 2 )[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Empty weight: 3,180 lb (1,442 kg)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Max takeoff weight: 5,200 lb (2,359 kg)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Powerplant: 2 × Lycoming IO-540 -C4B5 normally aspirated air-cooled flat-six piston engines , 250 hp (190 kW) each[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Maximum speed: 215 mph (346 km/h, 187 kn)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Cruise speed: 172 mph (277 km/h, 149 kn) at 10,200 ft (3,100 m) (long-range cruise)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Stall speed: 68 mph (109 km/h, 59 kn) (flaps down)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Never exceed speed : 277 mph (446 km/h, 241 kn)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Range: 1,519 mi (2,445 km, 1,320 nmi) at long-range cruise[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Service ceiling: 18,950 ft (5,780 m) (absolute ceiling)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Rate of climb: 1,400 ft/min (7.1 m/s)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Takeoff distance to 50 ft (15 m): 1,695 ft (517 m)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage Landing distance from 50 ft (15 m): 1,695 ft (517 m)[source]Piper PA-23 · Specifications (PA-23-250F, normally aspirated); only the objects and conditions stated in this passage |
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