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• Yak-40

Technical characteristics

 Performance specifications

Maximum take-off weight	17.2 tons
Maximum landing weight	17.2 tons
Maximum payload weight	2.72 tons
Equipped aircraft weight	9.85 tons
Maximum cruising speed	510 km/h
Operating ceiling	8100 m
Flying range
with maximum fuel reserve	1800 km
with maximum payload (fuel reserve)	1350 km
Required runway length (ISA conditions, at sea level)	1250 m
Crew	5 people

Airplane dimensions

Wingspan	25.0 m
Aircraft length	20.36 m
Aircraft height	6.5 m
Wing area	70.0 sq. m
Fuselage diameter	2.4 m
Passenger cabin:
Width	2.15 m
height	1.85 m
length	7.70 m
cubic capacity	43.00 m3

 

Aircraft power unit

  Yak-40 is equipped with three turbojet engines AI-25 manufactured by Ivchenko Engineering Design Bureau in Zaporozhye, Ukraine. Two engines are pylon-mounted in the fuselage tail section, and the third one is installed inside it.

  Turbojet double-flow engine AI-25 - 3 x 14.7 KN, 3 x 1,500 kgf

Take-off regime: (Í=0, Ì=0, ISA conditions)
Thrust 1500 kgf
Specific fuel consumption  0.555 kg/h
Nominal conditions:  
Thrust 1120 kgf
Cruising regime: (Í = 6000 m, 550 km/h)
Specific fuel consumption  0.83 kg/h
Aircraft fuel consumption  1150 kg/h

Flight control and navigation equipment

  Flight control and navigation equipment installed in Yak-40 allows to flight during the day and in nighttime under adverse weather conditions. Yak-40 is equipped with:
· Autopilot AP-40
· Heading system GM.K-1G
· Horizon indicator AGB-ZK
· Magnet compass KI-13
· Two automated radio compasses ARK-9
· Low-range radio altimeter RV-ZM

Noise level

  Conforms with ICAO, Chapter 2