Iliuszyn Ił-14. 1955. - Construction
125b Section 1955-06-01
Transport plane. Successor to the Il-12 aircraft.
Passenger, transport and landing aircraft, used to transport people, transport cargo, drop skydivers, transport wounded, aerophotogrammetry and others. Planes used in Poland took 18-32 soldiers or 3,500 kg of cargo on board.
Iliuszyn Ił-14 is a twin-engine low-wing aircraft with a three-chassis retractable in flight. Full metal half-shell construction.
Three-folded wings with working cover. The center wing has a box-type girder and forms a whole with engine nacelles. The center wing was equipped with crocodile flaps. The external parts are easily attached and have a three-girder structure. Shuttlecocks covered with canvas, there is a trimmer on the right shuttlecock. The outer wings have a slight rise. The all-metal slotted flaps are swiveled to take off at an angle of 20 degrees and landing by 45 degrees. The leading edges are de-iced with warm air flowing in the internal channels. The bottom surface has retractable landing, taxiing and take-off lights, 700 W each. The fuselage of the half-shell structure houses in the front part a crew cabin consisting of; two pilots, on-board mechanic and radiotelegraph navigator. The deck mechanic sits between the pilots in a folding chair. The navigator sits on the right behind the second pilot. The front windows of the crew cabin are de-iced with warm air. Landing reflectors were also placed in the nose. Behind the crew cab there is an equipment compartment with communication and navigation devices as well as central hydraulics and a fire extinguisher system. Further on the left side of the passenger version there is a front trunk with a hatch on the left side. On the right side there is a small place to prepare meals. The original passenger cabin had 18 seats in a 2 + 1 arrangement in 6 rows. By changing all the seats to double the number of seats increased to 24, and the liquidation of the front trunk was added row of seats by this number of seats increased to 28. The next change consisting in reducing the spacing between rows led to the eighth row, which gave 32 seats. Seats did not have individual headboards and were rather rail-type couches. The CCCP even used a seating arrangement for up to 40 people. At the back, behind the entrance behind the curtain, there is room for passengers' covers. Toilet on the right, small luggage compartment on the left. Behind the trunk is the passage to the tail of the fuselage housing the altimeter radio equipment and signal flare launchers. In the transport version of the aircraft, in the central part there is a cargo compartment with metal benches folded under the walls. In the rear, an additional small loading compartment for light loads. The fuselage cross-section is circular, and in the thickest sections the diameter is 2.8 m. Non-encapsulated cabins.
Classic, self-supporting. Ballasts covered with sheet metal, rudders made of canvas. Trimmers (balancing tabs) are mounted on all rudders. The leading edge of the horizontal tail is defrosted with warm air.
Three-support, single-gen chassis with oil-air cushioning. Front with one wheel. Main double. The chassis chamber hatches are only open when the chassis is extended and retracted. In the chassis position, the open-flaps remain closed. This protects the chambers against dirt and improves aerodynamics. The average operating ceiling does not exceed 4,000 m above sea level, and results from the use of a non-hermetic cabin. However, when using oxygen masks for the crew, the aircraft was able to operate at a ceiling of 6,500 m. The airframe's service life was 20,000 hours with repair intervals of 4,200 hours. On average, Polish airplanes spent about 1,200 hours / year in the air.
Two 14-cylinder piston engines in the ASz-82 T double star system with 2 x 1 398.4 kW (2 x 1 900 HP) starting power. Nominal power 2 x 1 199 kW (2 x 1 630 HP). The tailpipes are placed in a jet pattern, which reduces the risk of fire and improves aerodynamics. There are two exhaust pipes, and between them a third pipe is placed, which is the outlet of the engine cooling system and exhaust manifolds. Air heat exchangers are located directly on the exhaust manifolds. Air at a temperature of about 90 degrees C was directed to the channels de-icing the leading edges of the wings and for heating the cabin. 4-blade self-aligning propellers AW-50 with a diameter of 3.8 m.
Fuel tanks with a total capacity of 3 520 liters are located in the outer parts of the wings. Fuel consumption is about 450 kg / h of flight. Oil tanks 2 x 142 liters were placed in engine nacelles.
Avionics equipment Ił-14.
Three on-board radio stations of the KF and VHF range. ILS / VOR system for flight without ground visibility. Automatic remote control AP-45.
Data T-T Ił-14.
Span 31.70 m, length 22.31 m, height 7.80 m, load surface 100 m2, curb weight 12 700 kg, total weight 17 500 kg, load weight 3 300 - 3 500 kg, fuel 3 520 liters, speed maximum 430 km / h, cruising speed 280-350 km / h, climb speed 5.0 m / s, landing speed 135 km / h, maximum range 2 250 km, range with a maximum load of 600 km, maximum ceiling 7 400 m, run-up 485 m, reach 443 m.
Written by Karol Placha Hetman