Credit
Michal šenki · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
L-59E · Length
Single source12.20 m (40 ft 0 in)[source]
P2002-LSA · Length
Single sourceConfiguration
| Specification | Aero L-59 Super Albatros | Tecnam P2002 Sierra |
|---|---|---|
| Type | Military trainer aircraft COIN[source] | Two-seat light single[source] |
| Manufacturer | Aero Vodochody[source] | Tecnam[source] |
| Status | Out of production, in service[source] | — |
| Primary users | Czech Air Force Egyptian Air Force Tunisian Air Force[source] | — |
| Number built | 80 |
P2002 Sierra MkII / Tecnam Means Flying with Style · Length
Single source6.61 m (21 ft 8 in)[source]
21.7 ft (6,63 m)[source]P2002 Sierra MkII / Tecnam Means Flying with Style
L-59E · including tip tanks
Single source9.54 m (31 ft 4 in) (including tip tanks)[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; P2002-LSA · Empty weight
Single sourceMaximum take-off; P2002-LSA · Max takeoff weight
Single sourceL-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]
P2002-LSA · 1 × Rotax 912 S2
Single source1 × Rotax 912 S2 , 73.5 kW (100 hp)[source]
L-59E · 1 × Lotarev DV-2 turbofan thrust
Single source1 × Lotarev DV-2 turbofan , 21.57 kN (4,850 lbf) thrust[source]
L-59E · Service ceiling
Single source11,800 m (38,700 ft)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Manufactured | 1986–1996[source] | — |
|---|
| First flight | 30 September 1986[source] | — |
|---|
| Developed from | Aero L-39 Albatros[source] | — |
|---|
| Variant | Aero L-159 ALCA[source] | — |
|---|
| Fuel capacity | 1,537 L (406 US gal; 338 imp gal) including tip tanks[source] | — |
|---|
| Stall speed | 185 km/h (115 mph, 100 kn) (flaps down)[source] | 71 km/h (44 mph, 38 kn) (flaps down)[source] |
|---|
| Guns | one GSh-23L cannon in under-fuselage pod[source] | — |
|---|
| Hardpoints | four underwing hardpoints with a capacity of inner hardpoints 500 kg (1,100 lb)capacity, outer hardpoints 250 kg (550 lb)[source] | — |
|---|
| Country of origin | Czechoslovakia[source]Inventory Origin column; table 1, row 26, cell 2; revision 1374778711; retrieved 2026-10-01 | — |
|---|
| National origin | — | Italy[source] |
|---|
| Capacity | — | 1 passenger[source] |
|---|
| Aspect ratio | — | 6.4:1[source] |
|---|
| Propellers | — | 2-bladed, fixed pitch propeller[source] |
|---|
| Never exceed speed | — | 250 km/h (160 mph, 130 kn)[source] |
|---|
| g limits | — | +6g, -3g[source] |
|---|
| Takeoff run | — | 232 m (761 ft)[source] |
|---|
| Landing run | — | 186 m (610 ft)[source] |
|---|