History Construction List

PZL-130 Orlik, engine Walter.

Kraków 2008-09-05

276b Section 1989-01-12


PZL-130 Orlik Turbo, engine Walter.

Poland

Construction

Walter turboprop aircraft.

PZL-130 TM nb 005. 2017. Photo by Karol Placha Hetman
PZL-130 TM nb 005. 2017. Photo by Karol Placha Hetman

PZL-130 TC-I nb 013. 2017. Photo by Karol Placha Hetman
PZL-130 TC-I nb 013. 2017. Photo by Karol Placha Hetman

The PZL-130 TC-I Orlik aircraft is a training aircraft of all-metal construction.

Self-supporting wing with a trapezoidal contour and a positive lift of 5 degrees, one-piece and single-girder structure, fastened with two fittings, two rockers and four connectors. Welded flow structure. The cover is made of duralumin sheet metal, 1.2 to 2 mm thick, riveted with countersunk rivets. Inside the wings are integral fuel tanks with a capacity of 640 liters and a compartment for the wheels of the main chassis. In addition, on the lower surface of the wings there are 4 (TC-I) or 6 (TC-II) catches for attaching armaments. Slotted ailerons, pivoting with a pusher system and electrically driven double-gap Fowler flaps.

The hull of a half-shell structure, with a rectangular cross-section, oval vaulted. Riveted and welded, divided into two parts, front and back. The cab cover is opening to the right, made of organic glass and epoxy-glass frame. Behind the cab, an electrical equipment compartment.

Classic steer with rudder, single-girder with reinforced coverage. Vertical trapezoidal metal half-crust ballast, with rudder with mass balance and aerodynamic compensation, with unloading and balancing flap. Composite rudder. Metal, half-shell horizontal ballast. Rectangular, two-segment, half-shell metal rudder. At the rear of the fuselage, an aerodynamic steering wheel compensates for the propeller torque.

Front wheel on fork swingarm main wheels with telescopic shin. The chassis is equipped with oil-gas shock absorbers and hydraulic brakes, retracted into a recess with covers. Multi-disc brakes, hydraulically controlled, with three systems - basic, parking and emergency. Front landing gear with landing light.

The drive unit is the Czech turboprop engine Walter M-601 E, 490 kW, with a five-blade Avia V510 / 7 propeller, with a diameter of 2.30 m.

Data T-T PZL-130 TM Orlik.

Span 8.00 m

Length 8.73 m

Height 3.53 m

Bearing area 12.28 m2

Lengthening of the lobe 5.21

Curb weight 1,350 - 1,400 kg

Total weight 1,700 kg

Maximum weight 1 977 kg

Load weight 600 kg

Fuel weight 420 liters

Surface load 160

Power load 4.03

Top speed 507 km / h

Climbing speed 16.2 m / s

Cruise speed 438 km / h

Landing speed 149 km / h

Range of 1,000 km

Ceiling 10,000 m

Engine Walter M 601 E, 490 kW

Data T-T PZL-130 TC-I Orlik.

Span of 9.00 m

Length 9.00 m

Height 3.53 m

Bearing area 13.00 m2

Lengthening of the lobe 5.21

Curb weight 1,700 - 1,750 kg

Total weight 2 153 kg

Maximum weight: 2,700 kg

Load weight 600 kg

Fuel weight 560 liters

Surface load 166

Power load 3.84

Top speed 501 km / h

Climbing speed 13.3 m / s

Cruise speed 480 km / h

Landing speed 145 km / h

Range 1 062 - 1 905 km

Ceiling 10,000 m

Engine Walter M 601 T, 551 kW



Written by Karol Placha Hetman