PRODUCT TITLE: JANE'S ALL THE WORLDS AIRCRAFT 
EDITION: 1991-92 
EQUIPMENT TYPE: AIRCRAFT 
COUNTRY: POLAND 
MANUFACTURER: WSK-PZL SWIDNIK 
PAGE : 194 
MODEL: 
PZL SWIDNIK (MIL) Mi-2 
COMMENT : 
NATO reporting name: Hoplite 
  The Mil Mi-2, first flown in September 1961, was designed in the 
USSR by the Mikhail L. Mil bureau. Development of the two 
prototypes continued in the USSR until the helicopter had completed 
its initial State trials programme. Then, in accordance with an 
agreement signed in January 1964, further development, production 
and marketing of the Mi-2 were assigned exclusively to the Polish 
aircraft industry, which flew its own first example of the Mi-2 on 
4 November 1965. 
  Series production began in 1965, and Swidnik has since built 
more than 5250 for various civil and military operators; the 
majority of these have been exported. Among the operators of the 
Mi-2 are the air forces of Bulgaria, Czechoslovakia, Germany, 
Hungary, Iraq, North Korea, Libya, Poland (Mi-2CH, Mi-2T, Mi-2URN, 
Mi-2URP and Mi-2US and other variants), Syria and the USSR, and 
civil operators in European and various developing countries. 
Production of the Mi-2B (see separate entry) accounts for ``a few 
per cent'' of the overall total. 
  During the course of production the Mi-2 has undergone 
continuous improvement and upgrading, with versions for new 
applications being developed to meet specific customers' 
requirements. A full list of these can be found in the 1984-85 and 
earlier Jane's; the principal civil versions being produced 
recently were as follows: 
  (a) Convertible passenger/cargo transport; 
  (b) Ambulance and rescue versions (Mi-2R); 
  (c) Agricultural version, for dusting or conventional 
and ultra-low-volume spraying. In service in Bulgaria, 
Czechoslovakia, Egypt, Iraq, Poland and USSR; 
  (d) Freighter version, 
with external cargo sling and electric hoist; 
  (e) Training version; 
  (f) Aerial photography versions, able to carry 
photographic, photogrammetric, thermal imaging or TV cameras for 
oblique or vertical pictures. 
The following armed military variants have been produced: 
  Mi-2URN: As Mi-2US, but with four Mars 2 launchers (each with 16 
S-5 57 mm unguided rockets) instead of pylon mounted gun pods. PKV 
gunsight in cockpit for aiming of all weapons. In service since 
1973. 
  Mi-2URP: Anti-tank version, with cabin-side outriggers for four 
9M14M Malyutka (AT-3 `Sagger') wire-guided missiles. Four 
additional missiles carried in cargo compartment. In service since 
1976; later version can carry four 9M32 Strela 2 missiles. 
  Mi-2US: Gunship version, equipped with 23 mm NS-23KM cannon on 
port side of fuselage, two 7.62 mm gun pods on each side pylon, and 
two other 7.62 mm PK type movable machine guns in rear cabin. 
  The following details apply specifically to the basic Mi-2, 
except where indicated: 
TYPE : Twin-turbine general purpose light helicopter. 
ROTOR SYSTEM Three-blade main rotor fitted with hydraulic 
blade vibration dampers. All-metal blades, of NACA 230-12M section. 
Flapping, drag and pitch hinges on each blade. Main rotor blades 
and those of two-blade tail rotor each consist of an extruded 
duralumin spar with bonded honeycomb trailing-edge pockets. 
Anti-flutter weights on leading-edges, balancing plates on 
trailing-edges. Hydraulic boosters for longitudinal, lateral and 
collective pitch controls. Coil spring counterbalance mechanism in 
main and tail rotor systems. Pitch change centrifugal loads on tail 
rotor carried by ribbon type steel torsion elements. Rotors do not 
fold. Electric blade de-icing system for main and tail rotors. 
Rotor brake fitted. 
    Main rotor shaft driven via gearbox on each engine; 
three-stage WR-2 main gearbox, intermediate gearbox and tail rotor 
gearbox. Main rotor/engine rpm ratio 1 : 24.6; tail rotor/engine 
rpm ratio 1 : 4.16. Main gearbox provides drive for auxiliary 
systems and take-off for rotor brake. Freewheel units permit 
disengagement of a failed engine and also autorotation. 
FUSELAGE : Conventional semi-monocoque structure of pod and 
boom type, made up of three main assemblies: the nose (including 
cockpit), central section, and tailboom. Construction is of sheet 
duralumin, bonded and spot welded or riveted to longerons and 
frames. Main load bearing joints are of steel alloy. 
TAIL UNIT : Variable incidence horizontal stabiliser 
controlled by collective pitch lever. 
LANDING GEAR : Non-retractable tricycle type, plus 
tailskid. Twin-wheel nose unit. Single wheel on each main unit. 
Oleo-pneumatic shock absorbers in all units, including tailskid. 
Main shock absorbers designed to cope with both normal operating 
loads and possible ground resonance. Mainwheel tyres size 600 x 
180, pressure 4.41 bars (64 lb/sq in). Nosewheel tyres size 400 x 
125, pressure 3.45 bars (50 lb/sq in). Pneumatic brakes on 
mainwheels. Metal ski landing gear optional. 
POWER PLANT : Two 298 kW (400 shp) Polish built Isotov 
GTD-350 turboshafts, mounted side by side above cabin. Fuel in 
single rubber tank, capacity 600 litres (158.5 US gallons; 131 Imp 
gallons), under cabin floor. Provision for carrying a 238 litre (63 
US gallon; 52.4 Imp gallon) external tank on each side of cabin. 
Refuelling point in starboard side of fuselage. Oil capacity 25 
litres (6.6 US gallons; 5.4 Imp gallons). Engine air intake 
de-icing by engine bleed air. 
ACCOMMODATION : Normal accommodation for one pilot on 
flight deck (port side). Seats for up to eight passengers in 
air-conditioned cabin, comprising back to back bench seats for 
three persons each, with two optional extra starboard side seats at 
the rear, one behind the other. All passenger seats are removable 
for carrying up to 700 kg (1543 lb) of internal freight. Access to 
cabin via forward hinged doors on each side at front of cabin and 
aft on port side. Pilot's sliding window jettisonable in emergency. 
Ambulance version has accommodation for four stretchers and a 
medical attendant, or two stretchers and two sitting casualties. 
Side by side seats and dual controls in pilot training version. 
Cabin heating, ventilation and air-conditioning standard. Electric 
de-icing of windscreen. 
SYSTEMS: Cabin heating, by engine bleed air, and 
ventilation; heat exchangers warm atmospheric air for ventilation 
system during cold weather. Hydraulic system, pressure 65 bars (940 
lb/sq in), for cyclic and collective pitch control boosters. 
Hydraulic fluid flow rate 7.5 litres (1.98 US gallons; 1.65 Imp 
gallons)/min. Vented reservoir, with gravity feed. Pneumatic 
system, pressure 49 bars (710 lb/sq in), for mainwheel brakes. AC 
electrical system, with two STG-3 3kW engine driven 
starter/generators and 208V 16kVA three-phase alternator. 24V DC 
system, with two 28Ah lead-acid batteries. 
AVIONICS : Standard items include two transceivers (MF/HF), 
gyro compass, radio compass, radio altimeter, intercom system and 
blind-flying panel. Nose and tail warning radar fitted to some 
military versions. 
EQUIPMENT: Agricultural version carries a hopper on each 
side of the fuselage (total capacity 1000 litres; 264 US gallons; 
220 Imp gallons of liquid or 750 kg; 1650 lb of dry chemical) and 
either a spraybar to the rear of the cabin on each side or a 
distributor for dry chemicals under each hopper. Swath width 
covered by the spraying version is 40-45 m (130-150 ft). As a 
search and rescue aircraft, an electric hoist, capacity 120 kg (264 
lb), is fitted. In the freight role an underfuselage hook can be 
fitted for suspended loads of up to 800 kg (1763 lb). Illustrations 
in the Polish press have shown a version equipped for laying 
smokescreens. Diesel oil from external tanks on each side of the 
cabin is injected into large-diameter pipes extending backward and 
downward from the upper part of the rotor pylon. These pipes do not 
touch the engine exhausts but are warmed sufficiently to convert 
the diesel oil into dense white smoke. Electrically operated wiper 
for pilot's windscreen. Fire extinguishing system, for engine bays 
and main gearbox compartment, is generally similar to, but simpler 
than, the Freon system fitted to the Soviet Mil Mi-8, and can be 
actuated automatically or manually. 
ARMAMENT : Mi-2URN combat support and armed reconnaissance 
version of the Polish Air Force (see model listings) has a 23 mm 
and two 7.62 mm guns, plus two pylon mounted pods of sixteen 57 mm 
unguided rockets on each side of the fuselage; a seven-gun variant 
(one fixed 23 mm on port side, four pylon mounted and two cabin 
mounted 7.62 mm) is designated Mi-2US. Polish Air Force Mi-2 URPs 
(see illustration in 1988-89 Jane's) can carry two `Sagger' 
anti-tank missiles mounted on pylons on each side of the cabin. 
DIMENSIONS, EXTERNAL: 
  Main rotor diameter.....................14.50 m (47 ft 6{7/8} in) 
  Main rotor blade chord (constant, each)...0.40 m (1 ft 3{3/4} in) 
  Tail rotor diameter......................2.70 m (8 ft 10{1/4} in) 
  Length overall, rotors turning..............17.42 m (57 ft 2 in) 
    fuselage..............................11.40 m (37 ft 4{3/4} in) 
  Height to top of rotor head..............3.75 m (12 ft 3{1/2} in) 
  Stabiliser span...........................1.85 m (6 ft 0{3/4} in) 
  Wheel track...................................3.05 m (10 ft 0 in) 
  Wheelbase................................2.71 m (8 ft 10{3/4} in) 
  Tail rotor ground clearance...............1.59 m (5 ft 2{3/4} in) 
  Cabin door (port, rear): Height..........1.065 m (3 ft 5{3/4} in) 
    Width.......................................1.115 m (3 ft 8 in) 
  Cabin door (stbd, front): Height..........1.11 m (3 ft 7{3/4} in) 
    Width...................................0.75 m (2 ft 5{1/2} in) 
  Cabin door (port, front): Height..........1.11 m (3 ft 7{3/4} in) 
    Width...................................0.78 m (2 ft 6{3/4} in) 
DIMENSIONS, INTERNAL: 
  Cabin: 
    Length incl flight deck...............4.07 m (13 ft 4{1/4} in) 
      excl flight deck......................2.27 m (7 ft 5{1/2} in) 
    Mean width.............................1.20 m (3 ft 11{1/4} in) 
    Mean height..................................1.40 m (4 ft 7 in) 
AREAS: 
  Main rotor blades (each)..................2.40 m{2} (25.83 sq ft) 
  Tail rotor blades (each)...................0.22 m{2} (2.37 sq ft) 
  Main rotor disc........................166.4 m{2} (1791.11 sq ft) 
  Tail rotor disc...........................5.73 m{2} (61.68 sq ft) 
  Horizontal stabiliser......................0.70 m{2} (7.53 sq ft) 
WEIGHTS AND LOADINGS: 
  Weight empty, equipped: 
    passenger version.............................2402 kg (5295 lb) 
    cargo version.................................2372 kg (5229 lb) 
    ambulance version.............................2410 kg (5313 lb) 
    agricultural version..........................2372 kg (5229 lb) 
  Basic operating weight empty: 
    single-pilot versions.........................2365 kg (5213 lb) 
    dual control version..........................2424 kg (5344 lb) 
  Max payload, excl pilot, oil and fuel............800 kg (1763 lb) 
  Normal T-O weight (and max T-O weight of agricultural 
version)..........................................3550 kg (7826 lb) 
  Max T-O weight (special versions)...............3700 kg (8157 lb) 
  Max disc loading......................22.4 kg/m{2} (4.6 lb/sq ft) 
PERFORMANCE (at 3550 kg; 7826 lb T-O weight): 
  Never-exceed speed (VNE) at 500 m (1640 ft): 
    agricultural version................84 knots (155 km/h; 96 mph) 
    other versions....................113 knots (210 km/h; 130 mph) 
  Max cruising speed at 500 m (1640 ft): 
    agricultural version (without agricultural equipment)..... 
                                 .....102 knots (190 km/h; 118 mph) 
    other versions....................108 knots (200 km/h; 124 mph) 
  Max level speed with agricultural equipment..... 
                                   .....84 knots (155 km/h; 96 mph) 
  Econ cruising speed at 500 m (1640 ft): 
    for max range.....................102 knots (190 km/h; 118 mph) 
    for max endurance...................54 knots (100 km/h; 62 mph) 
  Max rate of climb at S/L.......................270 m (885 ft)/min 
  Time to 1000 m (3280 ft)...............................5 min 30 s 
  Time to 4000 m (13125 ft)..................................26 min 
  Service ceiling.................................4000 m (13125 ft) 
  Hovering ceiling: IGE.....................approx 2000 m (6560 ft) 
    OGE.....................................approx 1000 m (3280 ft) 
  Min landing area.........................30 x 30 m (100 x 100 ft) 
  Range at 500 m (1640 ft): 
    max payload, 5% fuel reserves.........91 nm (170 km; 105 miles) 
    max internal fuel, no reserves.......237 nm (440 km; 273 miles) 
    max internal and auxiliary fuel, 30 min reserves..... 
                                    .....313 nm (580 km; 360 miles) 
    max internal and auxiliary fuel, no reserves..... 
                                    .....430 nm (797 km; 495 miles) 
  Endurance at 500 m (1640 ft), no reserves: 
    max internal fuel....................................2 h 45 min 
    max internal and auxiliary fuel.............................5 h 
  Endurance (agricultural version), 5% reserves: 
    spraying.................................................40 min 
    dusting..................................................50 min