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Antonov An-124 Ruslan
The Antonov An-124 Ruslan is a large, strategic airlift, four engine aircraft that was designed in the 1980s by the Antonov design bureau in the Ukrainian SSR, then part of the Soviet Union (USSR).
Externally, the An-124 is similar to the American Lockheed C-5 Galaxy, having a double fuselage to allow for a rear cargo door that can open in flight without affecting structural integrity.
It is slightly shorter, with a slightly greater wingspan, and a 17% larger payload.
Instead of the Galaxy’s T-tail, the An-124 uses a conventional empennage, similar in design to that of the Boeing 747.
The An-124’s main engine is the Lotarev D-18 (238–250 kN).
The aircraft uses oleo strut suspension for its 24 wheels.
The suspension has been calibrated to allow landing on rough terrain and is able to kneel to allow easier front loading.
The plane has an onboard overhead crane capable of lifting up to 30 tonnes of cargo, and items up to 120 tonnes can be winched on board.
Up to 150 tonnes of cargo can be carried in a military An-124, it can also carry 88 passengers in an upper deck behind the wing centre section.
The cargo compartment of An-124 is 36×6.4×4.4 m (118×21×14 ft), ca. 20% larger than the main cargo compartment of the C-5 Galaxy, which is 36.91×5.79×4.09 m (121.1×19.0×13.4 ft).
Due to limited pressurization in the main cargo compartment (24.6 kPa, 3.57 psi), it seldom carries paratroopers.
Pilots have stated that the An-124 is light on the controls and easy to handle for an aircraft of its size.
Some airports require pavement protection from the heat and blast effects of the An-124’s 2 TA18-200-124 auxiliary power units.
88 passengers in upper aft fuselage,
The hold can take an additional 350 max on a palletised seating system / 150,000 kg (330,693 lb)
69.1 m (226 ft 8 in)
73.3 m (240 ft 6 in)
21.08 m (69 ft 2 in)
628 m2 (6,760 sq ft)
181,000 kg (399,037 lb)
214,000 kg (471,789 lb) maximum fuel weight
Max take-off weight
402,000 kg (886,258 lb)
Maximum landing weight
330,000 kg (727,525 lb)
348,740 l (92,130 US gal; 76,710 imp gal)
4 × Progress D-18T high-bypass turbofan engines, 229 kN (51,000 lbf) thrust each
865 km/h (537 mph, 467 kn) max
800–850 km/h (500–530 mph; 430–460 kn) at FL 328-394
(32,800–39,400 ft (9,997–12,009 m) at regional pressure setting)
230–260 km/h (140–160 mph; 120–140 kn)
3,700 km (2,300 mi, 2,000 nmi) with max payload
8,400 km (5,200 mi; 4,500 nmi) with 80,000 kg (176,370 lb) payload
11,500 km (7,100 mi; 6,200 nmi) with 40,000 kg (88,185 lb) payload
14,000 km (8,700 mi, 7,600 nmi) with max fuel and minimum payload
12,000 m (39,000 ft) max certified altitude
640.1 kg/m2 (131.1 lb/sq ft)
(Maximum take-off weight)
3,000 m (9,800 ft)
(Maximum landing weight)
900 m (3,000 ft).
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