History Construction List

Antonow An-26 1972.

Kraków 2008-10-26

232b Section 1972-09-13

Antonow An-26

Poland

Construction

Transport plane.

See An-24.

An-26 nb 1508. Czyżyny 2017. Photo by Karol Placha Hetman
An-26 nb 1508. Czyżyny 2017. Photo by Karol Placha Hetman

An-26 nb 1508. Czyżyny 2009. Photo by Karol Placha Hetman
An-26 nb 1508. Czyżyny 2009. Photo by Karol Placha Hetman

An-26 nb 1406. Mińsk Mazowiecki 2008. Photo by Karol Placha Hetman
An-26 nb 1406. Mińsk Mazowiecki 2008. Photo by Karol Placha Hetman

An-26 nb 44. Radom 2018. Photo by Karol Placha Hetman
An-26 nb 44. Radom 2018. Photo by Karol Placha Hetman

An-26 nb 1508. Czyżyny 2019. Photo by Karol Placha Hetman
An-26 nb 1508. Czyżyny 2019. Photo by Karol Placha Hetman

An-26 nb 1508. Czyżyny 2019. Photo by Karol Placha Hetman
An-26 nb 1508. Czyżyny 2019. Photo by Karol Placha Hetman

An-26. Radom 2009. Photo by Karol Placha Hetman
An-26. Radom 2009. Photo by Karol Placha Hetman

An-26. Radom 2009. Photo by Karol Placha Hetman
An-26. Radom 2009. Photo by Karol Placha Hetman



Construction

The An-26 aircraft is a medium and short range transport machine. It is also used for landing parachutists and cargo as well as transporting the sick and injured. The crew consists of 3-5 people.

As a standard, the crew consists of two pilots, a navigator, radiotelegraphist and deck mechanic. You can take 41 skydivers, 40 passengers or 24 injured on stretchers. Three-engine high wing, semi-shell structure. The aircraft is adapted for use with ground surfaces. Five-part, double-girder wing. The wedge angle is 3 degrees. The outer parts of the wings have a negative rise of 2 degrees.

The wings are equipped with flaps and ailerons. Shuttlecocks are made of glass laminate. They were balanced massively and equipped with balancing flaps. Fowler graying flaps are hydraulically driven. The internal flaps are single-slot, the external are double-slot. Engine wings are attached to the wings connecting the chambers of the main chassis. The leading edges are made as channels through which hot air flows for de-icing the wings.

The fuselage is technologically divided into three main parts. The front part begins with a honeycomb laminate cover under which the equipment is placed. The crew cabin is intended for 5 crew people; two pilots, a navigator, radio operator and on-board mechanic. The left, rear position is occupied by a navigator, which has a window in the form of a semi-circular dome in which the sighting device is placed. In the upper part of the crew cabin there is a hatch for emergency crew leaving the aircraft. Between the crew's cabin and the hold, a wall was opened with doors opening to the hold. The hold has dimensions; length 15.68 m, width 2.17 m, height 1.77. It holds a load of 55 cubic meters. There are 41 folding seats along the sides. A chain conveyor was placed in the floor for loading, unloading and ejecting loads in flight, which will fall on parachutes. The transporter has a load capacity of 4,550 kg. A winch with a lifting capacity of 1 500 kg moving on the rail was placed under the ceiling. A door was placed in the right wall of the fuselage and another emergency hatch was leaving the bottom of the fuselage. The hold is equipped with only 8 windows, 4 on each side. The first window in port and the last in port are at the same time emergency manholes. The rear cargo door has dimensions; 3.40 m long and 2.40 m wide. It is closed by a 3.40 mx 2.60 m ramp ladder. The crew and cargo cabins are hermetic and air-conditioned. The rear part of the hull, to which the tail is attached, is also hermetic and provides a room for aggregates for pilot-navigation and radio-electronic equipment. Access to this part is possible through the sight glass.


Classic setup divided into rudders and ballasts. The horizontal is mounted with a large positive rise. Vertical with high inflow. The edges of the tail are de-iced with warm air.

Three-support chassis with front wheels. All wheels are double. The front assembly is retracted to the hull backwards. Left-right control. Main chassis with long shins, retractable forward to the chambers located in the engine nacelles. The main undercarriage covers have large ribs to use as large tires as possible. The covers are still closed, and they only open to extend or retract the chassis. This protects the chambers against dirt. Oil-gas (nitrogen) shock absorbers placed in the shins. The hydraulic system retracts and extends the landing gear, turns the front assembly, brakes with the main landing gear wheels. Emergency opening of the chassis under its own weight.

Engines An-26.


Two AI-24 WT turboprop engines with 2 x 2 076 kW - 2 x 2 103 kW (2 x 2 820 HP) with 4-blade AW-72 T propellers.

Additional turbojet engine RU-19 A-300 with 1 x 8.80 kN (1 x 900 kG) thrust. His work provides;

Extra string during take-off and climb.

Necessary thrust when one of the engines is damaged in major. Then you can easily continue to the planned airport.

Starts AI-24 WT engines from on-board power sources.

It supplies the plane with electricity when the main engines are not running.

Works as a generator in the event of failure of the main generators.



An-26 fuel installation.

The aircraft was equipped with three fuel pumps. Each of them supports one motor, but thanks to the cross system, one pump can power two motors simultaneously. As fuel is depleted from the tanks, the free space is filled with carbon dioxide or nitrogen. Depending on the system used. This limits any explosion of fuel vapors.

Fire protection installation.

Automatically detects fire sources and extinguishes them with CFC. Especially engines, fuel tanks, generators and others.

Anti-icing system.

They are de-iced; wing edges, vertical and horizontal tail edges, engine inlets, propeller blades, and crew cab windows.



Data T-T An-26 1972.


Span 29.20 m

Length 23.80 m

Bearing area 74.98 m2

Curb weight 15 020 - 16 914 kg

Total weight 23,000 - 24,000 kg

Load weight 5 500 kg

Top speed 540 km / h

Climbing speed 3.3 m / s

Cruising speed 420 - 450 km / h

Landing speed 175 - 190 km / h

Maximum range 2 250 - 2 400 km

Range with a load of 900 - 1,400 km

Flight ceiling 7,600 - 8,100 m

Take-off run Dobieg 680-870 / 650-1 500 m

Engines Type AI-24 WT + RU-19 with 2 x 2 076 kW + APU 1 x 8.80 kN

Crew 5

Number of items in Poland 12

Written by Karol Placha Hetman