Mil Mi-38

The Mi-38's development was carried out by Kazan Helicopters since early 1980s[3] and a mockup was first shown during the 1989 Paris Air Show.[8] After the dissolution of the Soviet Union in 1991, Kazan Helicopters went into collaboration with Eurocopter that was to adapt the Mi-38 for international market.[8] In September 1994, Euromil JSC was established and funding of the programme began a month later.[8] Sextant and Pratt & Whitney Canada were also to participate in the programme as suppliers of Mi-38's avionics and powerplant equipment.[8] Initially, the helicopter was to be first flight tested in 1999, but only on 18 August 1999 a contract was signed for completion of the first demonstrator. In 2001, testing of Mi-38's rotor blades was carried out on a Mi-17 helicopter. The first Mi-38 demonstrator (PT-1) performed its maiden flight above the Kazan Helicopters plant on 22 December 2003.[8][1]

The second prototype (OP-2), powered by Pratt & Whitney Canada PW127/TS engines, made its first flight on 2 December 2010. The prototype is also equipped with the IBKO-38 or IBKV-38 aviation complex, developed by Transas Aviation, which implements a concept of a glass cockpit for the Mi-38.[9] The same month, OP-2 performed its first long-haul flight from Kazan to Moscow, which covers more than 800 km.[10]

In March 2013, the Fédération Aéronautique Internationale has confirmed the Mi-38 prototypes have already set five records in the E1h class. The second prototype aircraft set an altitude record by reaching 8,620 meters (28,280 feet) without a payload. The second and third records were for climbing speed; the Mi-38 reached a height of 3,000 meters (9,843 feet) in six minutes, then followed this to reach 6,000 meters (19,685 feet) in 10 minutes and 52 seconds. Two further records were altitude records: the first was set at 7,895 meters (25,902 feet) with a 1,000-kg (2,205-lb) payload, the second at 7,020 meters (23,031 feet) with a 2,000-kg (4,409-lb) payload.[11]

The third prototype (OP-3), began its flight tests on 17 December 2013. The helicopter is equipped with a pair of Russian Klimov TV7-117V turboshaft engines,[12] which produce about 2800 shp as opposite to 2500 shp for the Pratt & Whitney Canada PW127/TS.[13]

The fourth and final prototype (OP-4), first took off on 16 October 2014. Same as the OP-3, it is powered by Klimov TV7-117V engines but differs from the third prototype by its impact-resistant fuel system and enlarged portholes.[14]

On 30 December 2015, Rosaviatsiya certified the Mi-38, completing the testing and certification program and allowing for the delivery of the first production model. Certification was based on the third and fourth flight-test prototypes with 2,500 shp Klimov TV7-117V engines.[15]

In July 2017, a contract for delivery of first two serial Mi-38s to the Russian Defence Ministry was signed.[4] The Kazan Helicopters plant launched the serial production of the helicopter on 10 January 2018. In total, the Russian Defence Ministry planned to purchase about 15 helicopters until 2020.[16]

On 23 November 2018, military variant, Mi-38T, performed its maiden flight.[17][18] The new variant was developed to meet the Russian MoD's new requirements for the helicopter and due to international sanctions imposed on Russia, all of its components, including engines and avionics, are Russian-made.[13] Deputy Managing Director at Kazan Helicopters Vadim Ligai stated that the Mi-38 can now carry up to 40 passengers.[19] The Russian Defence Ministry took delivery of the first two serial Mi-38s in December 2019.[2][4] In January 2020, Russian Helicopters announced that it had received orders from an unspecified export customer (reported by Russian media sources to be in the Middle East) for Mi-38Ts in "transport and in increased comfort cabin configurations", with delivery from 2021 to 2022.[20] The RF Defense Ministry ordered 2 more Mi-38s in increased comfort cabin configuration in August 2020.[21]

 Russia

Data from Jane's all the World's Aircraft 2000–01[22]

General characteristics

• Crew: 2
• Capacity: 30 max / 5,000 kg (11,023 lb) internal payload / 6,000 kg (13,228 lb) external payload
• Length: 19.95 m (65 ft 5 in) excluding rotors
• Height: 5.2 m (17 ft 1 in) to top of rotor head
• Gross weight: 14,200 kg (31,306 lb)
• Max takeoff weight: 15,600 kg (34,392 lb)
• Powerplant: 2 × Klimov TVA-3000 turboshaft engines, 1,838 kW (2,465 hp) each
• Main rotor diameter: 21.1 m (69 ft 3 in)
• Main rotor area: 349.67 m² (3,763.8 sq ft)

Performance

• Maximum speed: 275 km/h (171 mph, 148 kn)
• Cruise speed: 250 km/h (160 mph, 130 kn)
• Range: 325 km (202 mi, 175 nmi) - 5,000 kg (11,023 lb) payload with 30 minutes reserve

530 km (330 mi; 290 nmi) - 4,500 kg (9,921 lb) payload (30 pax weith baggage) with 30 minutes reserve

1,300 km (810 mi; 700 nmi) - 1,800 kg (3,968 lb) payload with 30 minutes reserve and auxiliary fuel

• Service ceiling: 6,500 m (21,300 ft)
  
• Hover ceiling OGE: 2,500 m (8,202 ft)
• Disk loading: 44.6 kg/m² (9.1 lb/sq ft) max
• Power/mass: 0.1675 kW/kg (0.1019 hp/lb)

Aircraft of comparable role, configuration, and era

• AgustaWestland AW101
• Sikorsky S-92
• Changhe Z-18
• HAL Medium Lift Helicopter

The initial version of this article was based on material from aviation.ru. It has been released under the GFDL by the copyright holder.

Wikimedia Commons has media related to Mil Mi-38.

• Official website