Main Menu

Mil Mi-26 / Mi-27


Designed to provide Aeroflot with a heavylift helicopter to assist in the exploitation of undeveloped regions, this aircraft began life in the early 1970s (initially as Mi-6M), as soon as it became clear that the V-12 was not going to fulfil this role. It required the design and development of a completely new rotor and transmission system, plus the need to meet an official requirement that the aircraft's empty weight should be only half that of its maximum take-off weight, meant that it was not until 14 December 1977 that the V-26 prototype achieved its first hovering flight. NATO name Halo.

Weight has been saved by in-house design of the main gearbox providing multiple torque paths, GFRP tail rotor blades, titanium main and tail rotor heads, main rotor blades of mixed metal and GFRP, and use of alumimum-lithium alloys in airframe.

Equipped with a rear-loading ramp/doors, the main rotor rpm is 132, and the main rotor spindle is inclined forwards 4 degrees. Flying controls are hydraulically powered cyclic and collective pitch controls actuated by small parallel jacks, with redundant autopilot and stability augmentation system inputs. A fly-by-wire system flight was tested in 1994.

An eight-blade constant-chord main rotor has flapping and drag hinges, droop stops and hydraulic drag dampers. No elastomeric bearings or hinges, each blade has a one-piece tubular steel spar and 26 GFRP aerofoil shape full-chord pockets, honeycomb filled, with ribs and stiffeners and non-removable titanium leading-edge abrasion strip. Blades have moderate twist, taper in thickness toward tip, and are attached to small forged titanium head of unconventional design. Each has ground-adjustable trailing-edge tab. A five-blade constant-chord tail rotor on the starboard side, has GFRP blades and forged titanium head. A conventional transmission, with tail rotor shaft inside cabin roof, all-metal riveted semi-monocoque fuselage with clamshell rear doors, and flattened tail boom undersurface. The engine bay is of titanium for fire protection. All-metal tail surfaces and swept vertical stabiliser/tail rotor support are profiled to produce sideways lift. There is a ground-adjustable variable incidence horizontal stabiliser.

Landing gear is a non-retractable tricycle type with twin wheels on each unit. The steerable nosewheels have tyre size 900x300, and mainwheel tyres size 1,120x450. A retractable tailskid is at the end of the tailboom to permit unrestricted approach to the rear cargo doors. The length of the main legs is adjusted hydraulically to facilitate loading through rear doors and to permit loading on varying surfaces. A device on main gear indicates takeoff weight to flight engineer at lift-off, on panel on shelf to rear of his seat.

Power if from two 8,500kW ZMKB Progress (Soloviev) D-136 free-turbine turboshafts, side by side above cabin, forward of main rotor driveshaft. Air intakes fitted with particle separators to prevent foreign object ingestion, and have both electrical and bleed air anti-icing systems. Above and behind is central oil cooler intake. VR-26 fan-cooled main transmission, rated at 14,914kW, with air intake above rear of engine cowlings. System for synchronising output of engines and maintaining constant rotor rpm; if one engine fails, output of other is increased to maximum power automatically. Independent fuel system for each engine; fuel in eight underfloor rubber tanks, feeding into two header tanks above engines, which permit gravity feed for a period in emergencies; maximum standard internal fuel capacity 12,000 litres; provision for four auxiliary tanks. Mi-26TS normal capacity is 13,020 litres. Two large panels on each side of main rotor mast fairing, aft of engine exhaust outlet, hinge downward as work platforms.

Crew of five on flight deck: pilot (on port side) and co-pilot side by side, tip-up seat between pilots for flight technician, and seats for flight engineer (port) and navigator (starboard) to rear; upgrade proposal revealed in early 2001 involves installation of new avionics and will result in reduction of flight deck crew to three. Four-seat passenger compartment aft of flight deck. Loads in hold include two airborne infantry combat vehicles and a standard 20,000kg ISO container; about 20 tip-up seats along each sidewall of hold; maximum military seating for 90 combat-equipped troops; alternative provisions for 60 stretcher patients and four/five attendants. Heated windscreen, with wipers; four large blistered side windows on flight deck; forward pair swing open slightly outward and rearward. Downward-hinged doors, with integral airstairs, at front of hold on port side, and each side of hold aft of main landing gear units. Hold loaded via downward-hinged lower door, with integral folding ramp, and two clamshell upper doors forming rear wall of hold when closed; doors opened and closed hydraulically, with back-up hand pump for emergency use. Two LG-1500 electric hoists on overhead rails, each with capacity of 2,500kg, enable loads to be transported along cabin; winch for hauling loads, capacity 500kg; roller conveyor in floor and load lashing points throughout hold. Flight deck fully air conditioned.

It has a cargo hold 3.20m wide, 3.15m/ 10.25 ft high and 15m/49 ft deep. The maximum payload is 5000kg or 70-100 passengers. The helicopter has a crew of four, with room for an additional handler, and has a full range of navigational electronics and an automatic hover system.

Two main and one emergency hydraulic systems, operating pressure 157 and 206 bar. Electrical system three-phase 200/115V 400Hz; single-phase 115V 400Hz; three-phase, 36V 400Hz; single-phase 36V 400Hz; DC 27V. TA-8V 119kW. APU under flight deck, with intake louvres (forming fuselage skin when closed) and exhaust on starboard side, for engine starting and to supply hydraulic, electrical and air conditioning systems on ground. Electrically heated leading-edge of main and tail rotor blades for anti-icing. Only flight deck pressurised.

Systems include: Radar: Groza 7A813 weather radar in hinged (to starboard) nosecone.
Flight: Integrated PKV-26-1 flight/nav system and automatic flight control system, Doppler, map display, HSI, and automatic hover system. Optional GPS. Self-defence: Military versions can have IR jammers and suppressors, IR decoy dispensers and colour-coded identification flare system.

A hatch for a load sling is in the bottom of the fuselage, in line with the main rotor shaft, the sling cable attached to internal winching gear. Closed-circuit TV cameras observe slung payloads. Specialised versions can utilise firefighting equipment.

The first production aircraft rolled out in October 1980 and one of several prototype or preproduction Mi-26s (SSSR-06141) was displayed at the 1981 Paris Air Show. In-field evaluation began early 1982 and the type was fully operational in 1983. The production model carries a crew of five, and up to 85 combat-equipped troops, or two airborne infantry combat vehicles. More than 50 were in service in 1987.

On 3 February 1982, as just one of a string of new records established by the Mi-26, a "standard production" Mi-26 lifted a total mass (helicopter plus payload) of 56768.8kg to a height of 2000m. Also in February, 1982, set several load-to-height records, in-cluding lifting 25,000 kg (55,115 lbs) to 4,100 metres (13,451 ft).

The Mi-26 is reported to have entered service with Aeroflot in either 1982 or 1983.

India is the only export customer to 1987, with an order for ten. The first two were delivered in June 1986.

Production continued at low rate, with manufacture and marketing by Rostvertol.

Nearly 300 were built by 2001. Reportedly sold to about 20 countries; operators include Belarus (15), Cambodia
(two), Congo Democratic Republic (one), India (10), Kazakhstan, North Korea (two), South Korea (one), Mexico (two second-hand) in 2000, Peru (three), Russian Army (35), Russian Ministry of Emergencies, Mil-Avia and Ukraine (20). Russian Army deliveries included four in 1994.

COSTS: US$8 million to US$10 million (Mi-26T) (2000).


Mi-26 (Izdelie 90)
Basic military transport.

Modified military Mi-26, tested in 1985, with PNK-90 integrated flight/nav systems for automatic approach and descent to critical decision point, and other tasks. Not adopted.

Basic civil transport (Izdelie 209), generally as military Mi-26. Production begun in 1985. Variants include Geological Survey Mi-26 towing seismic gear, with tractive force of 10,000kg or more, at 180 to 200km/h at 55 to 100m for up to 3 hours. The mockup of an Mi-26 two-crew flight deck was shown al the 1997 Moscow Air Show and was again displayed at Farnborough 2002, when Rostvertol said decision to install new avionics on helicopter dependent upon outcome of discussions undertaken at Farnborough; if go-ahead is given, new designation Mi-26T2 will apply. New avionics suite will include PNK-26M flight-navigation system, incorporating five colour MFDs, two data input panels and a digital computer, plus GPS receiver and digital map and weather radar; increased automation will eliminate need for navigator/communications operator and flight engineer, although loadmaster will be retained. Military version will be adapted for night operations, using OVN-1 Skosok NVGs and GOES-321 gyrostabilised observation turret, containing a FLIR sensor and a laser range-finder. No designation has been announced for military versions.

Mi-26TS (sertifitsywvannyi: certified)
Mi-26T (Izdelie 219), but prepared for certification and marketed (in West as Mi-26TC) from 1996. Preproduction version, with gondola (port, front), positioned a 16,000kg TV tower, 30m long, in Rostov-on-Don in 1996. One delivered to Samsung Aerospace Industries in South Korea on 13 Septernher 1997; supplied with Twin Bambi Bucket fire-suppressant system and fulfils dual transport/ firefighting roles. This version is subject of upgrade proposal involving installation of new avionics suite and other improvements that will reduce crew numbers from five to three and offer benefits in area of operational effectiveness; if implemented, is expected to result in improved helicopter becoming available in about 2006.

Medical evacuation version of Mi-26T, typically with intensive care section for four casualties and two medics, surgical section for one casualty and three medics, pre-operating section for two casualties and two medics, ambulance section for five stretcher patients, three seated casualties and two attendants; laboratory; and amenities section with lavatory, washing facilities, food storage and recreation unit. Civil version in use by MChS Rossii (Ministry of Emergency Situations). Alternative medical versions available, with modular box-laboratories or fully equipped medical centres that can be inserted into the hold for anything from ambulance to field hospital use. As field ambulance can accommodate up to 60 stretcher patients; or seven patients in intensive care, 32 patients on stretchers and seven attendants; or 47 patients and eight attendants in other configurations, which can include 12 bunks in four tiers forward, or patent Rostvertol box laboratory behind the first row of bunks, with 16 bunks behind.
The box includes an operating table, diagnostic equipment, anaesthetic and breathing equipment and other systems. Another configuration includes a larger theatre box by Heinkel Medizin Systeme and 12 stretchers behind, and the helicopter can be fitted with an X-ray laboratory or form the central element of a deployable air-portable field hospital.

ASW version with search radar in undernose faired radome, extra cabin heat exchangers and towed MAD housing mounted on ramp.

Transport for 63 passeugers, basically four abreast in airline-type seating, with centre aisle; lavatory, galley and cloakroom aft of flight deck.

Flying crane (kran) derivative of Mi-26P with operator's gondola on fuselage side, next to cabin door on port side. First produced in 1997.

Reported ECM version. First noted 1986; current status unknown.

Hastily developed version for disaster relief tasks following explosion at Chernobyl nuclear facility; equipped with deactivating liquid tank and underbelly spraying apparatus.

Flying crane, with gondola for pilot/sling supervisor under fuselage aft of nosewheels or under rear-loading ramp. First produced in 1992.

Firefighting (pozharnyi) version that appeared in 1994, with internal tanks able to dispense up to 15,000 litres fire retardant from one or two vents, or 17,260 litres of water from an underslung VSU-15 bucket, or from two linked EP-8000 containers. Can fill tanks on the ground using pumps with 3,000 litres/min throughput. Prototype RA-06183 operated by Rostvertol. One delivered to Moscow Fire Brigade on 19 August 1999.

Tanker version that emerged in 1998, with 14,040 litres of T2, TS1 or R2 aviation fuel or DL, DZ or DA diesel oil fuel and 1,040 litres lubricants (in 52 jerry cans), dispensed through four 60m hoses for aircraft, or 10 20m hoses for ground vehicles. Conversion to/from Mi-26T takes 1 hour 25 minutes for each operation.

Upgrade under development; all-GFRP main rotor blades of new aerodynamic configuration, new ZMKB Progress D-127 turboshafts (each 10,700kW), and modified integrated flight/nav system with EFIS. Transmission rating unchanged, but full payload capability maintained under 'hot and high' conditions, OEI safety improved, hovering and service ceilings increased, and greater maximum payload (22,000 kg) for crane operations.

Two prototypes of a command support version of the Mi-26 are reported to have been built in 1988, with designation Mi-27. These feature new antennas along lower 'corner' of fuselage, blade and box-type and with long folded masts which are horizontal in flight, vertical when deployed on ground. Orders for production helicopters do not appear to have been placed.


Engines: 2 x ZMKB Progress D-136
Instant pwr: 14,710 kW
Rotor dia: 32 m
MTOW: 56,000 kg
Payload: 20,000 kg
Max speed: 159 kts
Max range: 800 km
HOGE: 5900 ft
Service ceiling: 15,100 ft
Crew: 5
Pax: 85

Mi-26 Halo A
Engines: 2 x Lotarev D-136, 11,400 shp
Installed pwr: 17,000 kW
Rotor dia: 32 m
Fuselage length: 33.7 m
Height: 8.06m (26 ft 5.25 in)
Wheelbase: 8.95m (29ft 4.5in)
Tail rotor dia: 7.61m (24 ft 11.5in)
No. Blades: 8
Empty wt: 28,200 kg
MTOW: 56,000 kg
Internal payload: 5000 kg
External payload: 20,000 kg
Max speed: 295 kph
Cruise speed: 255 kph
Ceiling: 4500 m
HOGE: 1800 m
Range: 800 km
Crew: 5
Pax: 100

Engines: 2 x Progress D-126 turboshaft, 7355kW
Main rotor diameter: 32.0m
Length with rotors turning: 40.03m
Width: 8.15m
Max take-off weight: 56000kg
Empty weight: 28200kg
Fuel: 12000kg
Max speed: 295km/h
Cruising speed: 255km/h
Service ceiling: 4600m
Hovering ceiling, OGE: 1800m
Range with 18000kg payload: 670km
Payload: 20000kg
Crew: 4
Passengers: 70






Copyright © 2020 all-aero. All Rights Reserved.
Joomla! is Free Software released under the GNU General Public License.