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
M.L.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 57mm 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 23mm NS-23KM cannon on
port side of fuselage, two 7.62mm gun pods on each side pylon, and
two other 7.62mm 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/enginerpm 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 longerones and
frames. Main load bearing joints are of steel alloy.
TAIL UNIT : Variable incidence horizontal stabilizer
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. Main tires size 600x
180, pressure 4.41 bars (64 lb/sq in). Nosewheel tires size 400x
125, pressure 3.45 bars (50 lb/sq in). Pneumatic brakes on
main. 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.
Refueling 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 700kg (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 main 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 750kg; 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 40-45m (130-150 ft). As a
search and rescue aircraft, an electric hoist, capacity 120kg (264
lb), is fitted. In the freight role an underfuselage hook can be
fitted for suspended loads of up to 800kg (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
M.L.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 23mm
and two 7.62mm guns, plus two pylon mounted pods of sixteen 57mm
unguided rockets on each side of the fuselage; a seven-gun variant
(one fixed 23mm on port side, four pylon mounted and two cabin
mounted 7.62mm) 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.....................14.50m (47ft 6{7/8} in)
  Main rotor blade chord (constant, each)...0.40m (1ft 3{3/4} in)
  Tail rotor diameter......................2.70m (8ft 10{1/4} in)
  Length overall, rotors turning..............17.42m (57ft 2 in)
    fuselage..............................11.40m (37ft 4{3/4} in)
  Height to top of rotor head..............3.75m (12ft 3{1/2} in)
  Stabilizer span...........................1.85m (6ft 0{3/4} in)
  Wheel track...................................3.05m (10ft 0 in)
  Wheelbase................................2.71m (8ft 10{3/4} in)
  Tail rotor ground clearance...............1.59m (5ft 2{3/4} in)
  Cabin door (port, rear): Height..........1.065m (3ft 5{3/4} in)
    Width.......................................1.115m (3ft 8 in)
  Cabin door (stbd, front): Height..........1.11m (3ft 7{3/4} in)
    Width...................................0.75m (2ft 5{1/2} in)
  Cabin door (port, front): Height..........1.11m (3ft 7{3/4} in)
    Width...................................0.78m (2ft 6{3/4} in)
DIMENSIONS, INTERNAL:
  Cabin:
    Length incl flight deck...............4.07m (13ft 4{1/4} in)
      excl flight deck......................2.27m (7ft 5{1/2} in)
    Mean width.............................1.20m (3ft 11{1/4} in)
    Mean height..................................1.40m (4ft 7 in)
AREAS:
  Main rotor blades (each)..................2.40 m2 (25.83 sq ft)
  Tail rotor blades (each)...................0.22 m2 (2.37 sq ft)
  Main rotor disc........................166.4 m2 (1791.11 sq ft)
  Tail rotor disc...........................5.73 m2 (61.68 sq ft)
  Horizontal stabilizer......................0.70 m2 (7.53 sq ft)
WEIGHTS AND LOADINGS:
  Weight empty, equipped:
    passenger version.............................2402kg (5295 lb)
    cargo version.................................2372kg (5229 lb)
    ambulance version.............................2410kg (5313 lb)
    agricultural version..........................2372kg (5229 lb)
  Basic operating weight empty:
    single-pilot versions.........................2365kg (5213 lb)
    dual control version..........................2424kg (5344 lb)
  Max payload, excl pilot, oil and fuel............800kg (1763 lb)
  Normal T-O weight (and max T-O weight of agricultural
version)..........................................3550kg (7826 lb)
  Max T-O weight (special versions)...............3700kg (8157 lb)
  Max disc loading......................22.4kg/m2 (4.6 lb/sq ft)
PERFORMANCE (at 3550kg; 7826 lb T-O weight):
  Never-exceed speed (VNE) at 500m (1640 ft):
    agricultural version................84 knots (155km/h; 96mph)
    other versions....................113 knots (210km/h; 130mph)
  Max cruising speed at 500m (1640 ft):
    agricultural version (without agricultural equipment).....
                                 .....102 knots (190km/h; 118mph)
    other versions....................108 knots (200km/h; 124mph)
  Max level speed with agricultural equipment.....
                                   .....84 knots (155km/h; 96mph)
  Econ cruising speed at 500m (1640 ft):
    for max range.....................102 knots (190km/h; 118mph)
    for max endurance...................54 knots (100km/h; 62mph)
  Max rate of climb at S/L.......................270m (885 ft)/min
  Time to 1000m (3280 ft)...............................5 min 30 s
  Time to 4000m (13125 ft)..................................26 min
  Service ceiling.................................4000m (13125 ft)
  Hovering ceiling: IGE.....................approx 2000m (6560 ft)
    OGE.....................................approx 1000m (3280 ft)
  Min landing area.........................30x30m (100x100 ft)
  Range at 500m (1640 ft):
    max payload, 5% fuel reserves.........91 nm (170km; 105miles)
    max internal fuel, no reserves.......237 nm (440km; 273 miles)
    max internal and auxiliary fuel, 30 min reserves.....
                                    .....313 nm (580km; 360miles)
    max internal and auxiliary fuel, no reserves.....
                                    .....430 nm (797km; 495miles)
  Endurance at 500m (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
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Modified January 25, 1996 by Alexandre Savine;
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