PZL-130 Orlik, piston engine. 1984. - Construction

Published on: 2020-02-01
Updated on: 2020-02-01
Category: Airplanes
History Construction Tally

Kraków 2008-09-05

271c Section 1984-10-12

PZL-130 Orlik with a piston engine



PZL-130 nb 003 in Chinese camouflage. 2011. Photo by Karol Placha Hetman
PZL-130 nb 003 in Chinese camouflage. 2011. Photo by Karol Placha Hetman

Construction PZL-130

Single-engine, two-seater training and training aircraft, made of metal. A piston engine in a star system.
 NACA 642215 wing modified to obtain a constant chord of the ailerons and flaps. Rise +5 degrees, wedge angle at the hull 0 degrees, geometric degree of rotation 3 degrees. Metal construction, non-split, caisson, multi-longitudinal, riveted caisson and welded flow part. Frize darts tilted 20 degrees up and 12 degrees down. Slotted flaps swing out to take off 10 degrees for take-off and 40 degrees for landing. Glass-epoxy composite tips.

Fuselage. Flat from below. Elliptically vaulted from above. Metal half-shell construction, riveted from welded components. Cabin glazing made of plexiglass glued to glass-epoxy composite frames. The cab cover opens to the right side. The cab cover may be rejected in an emergency. To facilitate boarding, a fixed footrest attached to the fuselage was used to stand on the left wing. Two-seater cabin in tandem arrangement. Rear seat with slight elevation. The seats are electrically adjustable and are adapted to use both back and seat parachutes.

Classical formation, well ahead vertical horizontal. Metal construction partially welded. Rudder tilts 30 degrees in both directions. The horizontal tail span is 3.50 m.

Three-support chassis with front wheel, retractable in flight. All wheels single. Front telescopic chassis with half-fork wheel and lateral vibration damper. Main landing gear wheels on rocker arms with hydraulic disc brakes. Oil and gas shock absorbers. Low-pressure tubeless tires. A parking brake. The chassis base is 2.22 m. The main chassis spacing is 3.10 m.

Control. Pusher ailerons with torsion tube at the starboard side of the hull. The elevator is moved pusher-rope. Rudder moved by cable. Flaps, balancing flaps and curtains for the engine cooling air intake. Electric control. The drive unit is controlled by double-acting flexible tendons (arens). Steering lever sectors.

The instrument panel contains; magnetic compass, speedometer, altimeter, artificial horizon, gyrocopter, gyrometer with bendmeter, variometer, clock, manovacometer, engine control indicator which shows fuel pressure, oil pressure, oil temperature. Other instruments are; tachometer, engine head temperature thermometer, carburetor thermometer, two fuel gauges, carburetor thermometer, stall indicator, accelerometer, fault signaling system, flap position indicator, chassis position indicator, rocket indicator, pneumatic system main pressure gauge, pneumatic emergency circuit pressure gauge, brake pressure gauge .

Engine PZL-130.

9-cylinder star engine of the Viennese type M-14 Pm with 243 kW. Pneumatic engine starting. Adjustable three-blade metal propeller. The propeller diameter is 1.95 m. Ultimately, the PZL-Kalisz K-8 AA engine was to be used, which was a modernized M-14 Pm engine.

Aircraft installations PZL-130

Fuel - 4 integral tanks in the caisson box with a capacity of 2 x 100 liters and 2 x 110 liters. Expenditure tank with a capacity of 9 liters in the fuselage.

Pneumatic. The pneumatic system is two-circuit. Basic and emergency circuit. Working pressure 4.9 Mpa.

Electric. Electrical installation with a voltage of 24/28 V. A 3 kW generator. 24 V / 18 Ah battery.

Plumbing system. Equipped with a 26-liter oil tank, cooler with thermostat.


The aircraft is equipped with a set of pilot-navigation instruments and engine control. Installation control instruments set. Failure signaling system. UHF radio station, radiocompass, on-board telephone, rocket launcher, fire extinguisher, first aid kit. The aircraft has the option of installing a radio altimeter.


The plane was equipped with two catches of suspended light armament, which were placed under the wings. They can be containers with non-guided missiles or light bombs of various types.

Data T-T PZL-130. 1984.

  • Span 8.00 m
  • Length 8.45 m
  • High 4.00 m
  • Bearing area 12.28 m2
  • Lengthening of the lobe 5.21
  • Curb weight 950 - 1,110 kg
  • Total weight 1 500 kg
  • Maximum weight 1,600 kg
  • Load weight 250 kg
  • Fuel weight 420 kg
  • Load capacity of 130.1 kg / m2
  • Engine power load up to 6.04
  • Maximum speed 340 - 380 km / h
  • Climbing speed 7.0 - 7.4 m / s
  • Landing speed 116 km / h
  • Cruise speed 316 km / h
  • Maximum range 1,415 - 1,460 km
  • Ceiling 4,200 - 7,000 m
  • Run up to 300 m
  • Run to stop 240 m
  • M-14 Pm engine with 243 kW

Data T-T PZL-130. 1986.

  • Span of 9.00 m
  • Length 8.45 m
  • High 4.00 m
  • Bearing area 12.80 m2
  • Lobe extension 6.33
  • Curb weight 1 112 - 1 147 kg
  • Total weight 1 520 kg
  • Maximum weight 1,600 kg
  • Load weight 300 kg
  • Fuel weight 420 kg
  • Load capacity of the bearing surface 125 kg / m2
  • Engine power load up to 6.04
  • Maximum speed 340 km / h
  • Climbing speed 7.1 m / s
  • Landing speed 115 km / h
  • Cruising speed 310 km / h
  • Maximum range 1,430 km Ceiling 4,300 m
  • Run up to 300 m
  • Run to stop 240 m
  • M-14 Pm engine with 243 kW

Written by Karol Placha Hetman