Mil Mi-24

.

NATO reporting name: 'Hind'

TYPE:

Twin-turbine gunship helicopter, with transport capability.

PROGRAMME:

"Development began second half of 1960s, as first fire support helicopter in former USSR, with accommodation for eight armed troops; 12 prototypes built; first flight 19 September 1969; first reported in West 1972; photographs became available 1974, when two units of approximately squadron strength based in East Germany; reconfiguration of front fuselage changed primary role to gunship; new version first observed 1977; used operationally in Chad, Nicaragua, Ceylon (Sri Lanka), Angola, Afghanistan, Chechnya and Iran/Iraq war, when at least one Iranian F-4 Phantom II destroyed by 9M114 (AT-6 `Spiral') anti-tank missile from Mi-24; low-rate production continues.

VARIANTS:

Mi-24A (`Hind-A, B and C'): Early versions with pilot and co-pilot/gunner in tandem under large-area continuous glazing; large flight deck; about 250 built, including Mi-24U unarmed dual-control trainers (first flight 1972); last described in 1989-90 Jane's.

Mi-24D (Type 24-6; `Hind-D'): Interim gunship version; design began 1971; entered production at Arsenyev and Rostov plants 1973; about 350 built 1973-77. Basically as late model `Hind-A' with TV3-117 engines and port-side tail rotor, but entire front fuselage redesigned above floor forward of engine air intakes; separate armored cockpits for weapon operator and pilot in tandem; flight mechanic optional, in main cabin; transport capability retained; USUP-24 gun system, with rangefinding; undernose JakB-12.7 four-barrel 12.7 mm machine gun in turret, slaved to adjacent KPS-53A electro-optical sighting pod, for air-to-air and air-to-surface use; Falanga P (Phalanx) anti-tank missile system; nosewheel leg extended to increase ground clearance of sensor pods; nosewheels semi-exposed when retracted. Mi-24DU dual-control training version has no gun turret. (See also Mi-25.) Detailed description applies to Mi-24D, except where indicated.

Mi-24V (Types 20-1and 24-2; `Hind-E'): As Mi-24D, but modified wingtip launchers and four underwing pylons; weapons include up to eight 9M114 (AT-6 `Spiral') radio guided tube-launched anti-tank missiles in pairs in Shturm V (Attack) missile system; ASP-17V enlarged undernose automatic missile guidance pod on port side, with fixed searchlight to rear; R-60 (K-60; AA-8 `Aphid') air-to-air missiles optional on underwing pylons; pilot's HUD replaces former reflector gunsight. Deliveries to Soviet Air Force began 29 March 1976; about 1,000 built at Arsenyev and Rostov 1976-86. (See also Mi-35.)

Mi-24VM: Proposed upgraded Mi-24V first shown in model form at Moscow Air Show '95. Mi-28 main and tail rotors and nose turret for twin 23 mm cannon; large IR suppressors scabbed to fuselage sides.

Mi-24VP: Variant of Mi-24V with twin-barrel 23 mm gun, with 450 rounds, in place of four-barrel 12.7 mm gun in nose; photographed 1992; small production series built at Rostov.

Mi-24P (Type 24-3; `Hind-F'): Development started 1974; about 620 built 1981-90; first shown in service in 1982 photographs; P of designation refers to pushka = cannon; as Mi-24V, but nose gun turret replaced by GSh-30-2 twin-barrel 30 mm gun (with 750 rounds) in semi-cylindrical pack on starboard side of nose; bottom of nose smoothly faired above and forward of sensors.

Mi-24R (Type 46-2; `Hind-G1'): Identified at Chernobyl after April 1986 accident at nuclear power station; no undernose electro-optical and RF missile guidance pods; instead of wingtip weapon mounts, has `clutching hand' mechanisms on lengthened pylons, to obtain six soil samples per sortie, for NBC (nuclear/biological/chemical) warfare analysis; air samples sucked in via pipe on port side, aft of doors; datalink to pass findings to ground; lozenge shape housing with exhaust pipe of air filtering system under port side of cabin; bubble window on starboard side of main cabin; small rearward-firing marker flare pack on tailskid; crew of four wear NBC suits; deployed six per helicopter regiment throughout CIS ground forces. Designation (also appearing as Mi-24RCh) indicates Razvedchik: reconnaissance/chemical. About 150 built 1983-89.

Mi-24K (korrektirovchik: corrector) (`Hind-G2'): As Mi-24R, but with large camera in cabin, f8/1,300 mm lens on starboard side; six per helicopter regiment for reconnaissance and artillery fire correction; gun and B-8V-20 rocket pods retained. No target designator pod under nose; upward hinging cover for IR sensor. About 150 built 1983-1989.

Mi-24BMT: A few modified 1973 for minesweeping.

Mi-24PS: Special version for Russian Ministry of Internal Affairs; prototype displayed at Moscow Air Show '95. Equipment includes undernose FLIR ball; searchlight pod outboard of this on port side, loudspeaker pack on starboard side; hoist; climbdown ropes; stations for radio operators.

Mi-24 Ecological Survey Version: Modification by Polyot industrial research organisation, to assess oil pollution on water and seasonal changes of water level. First seen 1991 with large flat sensor `tongue' projecting from nose in place of gun turret; large rectangular sensor pod on outer starboard underwing pylon; unidentified modification replaces rear cabin window on starboard side.

Mi-25: Export Mi-24D, including those for Afghanistan, Cuba and India.

Mi-35: Export Mi-24V. Unarmed, dual control trainer version also produced for India.

Mi-35P: Export Mi-24P.

Mi-35M: Upgraded night-capable version of Mi-24/35 designed to meet the latest air mobility requirements of the Russian Army. Features include Mi-28 main and tail rotors and transmission; 1,636 kW (2,194 shp) Klimov TV3-117VMA engines; new avionics; a reduced empty weight resulting from new titanium main rotor head, composites rotor blades, shortened stub-wings and non-retractable landing gear; a 23 mm GSh-23-2 twin-barrel gun in nose turret, with 470 rounds; up to 16 radio-guided 9M114 (AT-6 `Spiral'), or laser-guided 9M-120 anti-tank, 9M-120F blast fragmentation or 9A-220 air-to-air versions of Ataka (AT-12) missile; or a range of armament options including GUV gun/grenade pods; UPK-23-250 gun pods; B-8V-20 and B-13L rocket pods; S-24B rockets; and KMGU pods of anti-armor and anti-personnel mines. Night Operation Capable Avionics System (NOCAS) by Sextant Avionique and Thomson-TTD Optronic integrates Chlio FLIR ball with a TMM-1410 display, providing night vision for target acquisition and identification, missile guidance and gun aiming. Other equipment includes a VH-100 HUD, NVGs, liquid-crystal MFD, Nadir 10 mission management and navigation system, laser-gyro INS and GPS. The FLIR ball is mounted outboard of the standard missile guidance pod. Ability to carry Igla V air-to-air missiles is optional. Non-flying demonstrator first displayed at 1995 Paris Air Show.

DESIGN FEATURES:

Typical helicopter gunship configuration, with stepped tandem seating for two crew and heavy weapon load on stub-wings; fuselage unusually wide for role, due to requirement for carrying eight troops; dynamic components and power plant originally as Mi-8, but soon upgraded to Mi-17-type power plant and port-side tail rotor. Main rotor blade section NACA 230, thickness/chord ratio 11 to 12 per cent; tail rotor blade section NACA 230M; stub-wing anhedral 12°, incidence 19°; wings contribute approximately 25 per cent of lift in cruising flight; fin offset 3°.

STRUCTURE:

Five-blade constant-chord main rotor; forged and machined steel head, with conventional flapping, drag and pitch change articulation; each blade has aluminum alloy spar, skin and honeycomb core; spars nitrogen pressurized for crack detection; hydraulic lead/lag dampers; balance tab on each blade; aluminum alloy three-blade tail rotor; main rotor brake; all-metal semi-monocoque fuselage pod and boom; 5 mm hardened steel integral side armor on front fuselage; all-metal shoulder wings with no movable surfaces; swept fin/tail rotor mounting; variable incidence horizontal stabilizer.

LANDING GEAR:

Tricycle type; rearward-retracting steerable twin-wheel nose unit; single-wheel main units with oleo-pneumatic shock-absorbers and low-pressure tires, size 720 x 320 mm on mainwheels, 480 x 200 mm on nosewheels. Main units retract rearward and inward into aft end of fuselage pod, turning through 90° to stow almost vertically, discwise to longitudinal axis of fuselage, under prominent blister fairings. Tubular tripod skid assembly, with shock-strut, protects tail rotor in tail-down take-off or landing.

POWER PLANT:

Two Klimov TV3-117MT turboshafts, each with T-O rating of 1,434 kW (1,923 shp), side by side above cabin, with output shafts driving rearward to main rotor shaft through combining gearbox. There is 5 mm hardened steel armor protection for engines. Main fuel tank in fuselage to rear of cabin, with bag tanks behind main gearbox. Internal fuel capacity 1,500 kg (3,307 lb); can be supplemented by 1,000 kg (2,205 lb) auxiliary tank in cabin (Mi-24D); provision for carrying (instead of auxiliary tank) up to four external tanks, each 500 liters (132 US gallons; 110 Imp gallons), on two inner pylons under each wing. Optional deflectors and separators for foreign objects and dust in air intakes; and infra-red suppression exhaust mixer boxes over exhaust ducts.

ACCOMMODATION:

Pilot (at rear) and weapon operator on armored seats in tandem cockpits under individual canopies; dual flying controls, with retractable pedals in front cockpit; if required, flight mechanic on jump-seat in cabin, with narrow passage between flight deck and cabin. Front canopy hinged to open sideways to starboard; footstep under starboard side of fuselage for access to pilot's rearward-hinged door; rear seat raised to give pilot unobstructed forward view; anti-fragment shield between cockpits. Main cabin can accommodate eight persons on folding seats, or four stretchers; at front of cabin on each side is a door, divided horizontally into two sections hinged to open upward and downward respectively, with integral step on lower portion. Optically flat bulletproof glass windscreen, with wiper, for each crew member.

SYSTEMS:

Cockpits and cabin heated and ventilated. Dual electrical system, with three generators, giving 36, 115 and 208 V AC at 400 Hz, and 27 V DC. Retractable landing/taxiing light under nose; navigation lights; anti-collision light above tailboom. Stability augmentation system. Electrothermal de-icing system for main and tail rotor blades. AI-9 V APU mounted transversely inside fairing aft of rotor head for engine starting and ground services.

AVIONICS:

Comms: Include VHF and UHF radio.

Flight: Autopilot, ARK-15M radio compass, ARK-U2 radio compass, RV-5 radio altimeter.

Instrumentation: Blind-flying instrumentation, and ADF navigation system with Doppler-fed mechanical map display. Air data sensor boom forward of top starboard corner of bulletproof windscreen at extreme nose.

Mission: Undernose pods for electro-optics (starboard) and Raduga-F semi-automatic missile guidance (port). Many small antennae and blisters, including SRO-2 Khrom (`Odd Rods') IFF transponder.

Self-defence: Sirena-3M radar warning antennae on each side of front fuselage and on trailing-edge of tail rotor pylon. Infra-red jammer (L-166V-11E Jspanka microwave pulse lamp: `Hot Brick') in `flower pot' container above forward end of tailboom. ASO-2V flare dispensers under tailboom forward of tailskid assembly initially; later triple racks (total of 192 flares) on sides of center-fuselage.

EQUIPMENT:

Gun camera on port wingtip. Color-coded identification flare system.

ARMAMENT:

One remotely controlled YakB-12.7 four-barrel Gatling type 12.7 mm machine gun, with 1,470 rounds, in VSPU-24 undernose turret with field of fire 60° to each side, 20° up, 60° down; gun slaved to KPS-53AV undernose sighting system with reflector sight in front cockpit; four 9M17P Skorpion (AT-2 `Swatter') anti-tank missiles on 2P32M twin rails under endplate pylons at wingtips; four underwing pylons for UB-32 rocket pods (each 32 S-5 type 57 mm rockets), B-8V-20 pods each containing twenty 80 mm S-8 rockets, B-13L pods each containing five 130 mm S-13 rockets, 240 mm S-24B rockets, UPK-23-250 pods each containing a GSh-23L twin-barrel 23 mm gun, GUV pods each containing either one four-barrel

12.7 mm YakB-12.7 machine gun with 750 rounds and two four-barrel 7.62 mm 9-A-622 machine guns with total 1,100 rds or an AGS-17 Plamia 30 mm grenade launcher with 300 grenades, up to 1,500 kg (3,300 lb) of conventional bombs, mine dispensers, night flares or other stores. R-60 (AA-8 `Aphid'), R-73 (AA-11 `Archer') and Igla air-to-air missiles fitted experimentally. Helicopter can be landed to install reload weapons carried in cabin. PKV reflector gunsight for pilot.

Provisions for firing AKMS guns from cabin windows."

LENGTH (m) 21.35

HEIGHT (m) 3.97

WING SPAN (m) 6.54

MAX T-O WEIGHT (kg) 12000

MAX LEVEL SPEED (knots) 180

MAX RANGE (nm) 540

SERVICE CEILING (m) 4500

HOVERING CEILING (m) 1500

MAX RATE CLIMB (m/min) 750

(source: Jane's)

"Mil Mi-24, Mi-25 & Mi-35 Country of origin. Russia

Type: Armed assault/attack helicopter Powerplants: Mi-24P - Two 1635kW (2190shp) Klimov TV3-117 turboshafts driving a five blade main rotor and three blade tail rotor. Performance. Mi-24P - Max speed 335km/h (180kt), cruising speed 270km/h (145kt), economical cruising speed 217km/h (117kt). Max initial rate of climb 2460ft/min. Service ceiling 14,75oft. Hovering ceiling out of ground effect 4920ft. Range with auxiliary fuel 11000km (540nm), range with standard internal fuel 500km (270nm). Combat radius with max military load 160km (85nm), radius with two external fuel tanks 225krn (11 20nm), radius with four tanks 288km (11 55nm). Weights: Mi-241? - Empty 8200kg (18,078lb), max takeoff 12,000kg (26,455lb). Dimensions: Mi-24P - Main rotor diameter 17.30m (56ft 9in), length overall rotors turning 21.35m (70ft 1 in), fuselage length exc gun 17.51m (57ft 5in), height to top of rotor head 3.97m (13ft 1 in). Main rotor disc area 235.1 m^2 (2530.2sq ft). Accommodation: Weapons operator and pilot in tandem stepped cockpit. Main cabin can accommodate eight troops or four stretchers.

Armament One 12.7mm four barrel YakB machine gun in undernose turret or twin 23mm or 30mm cannon. Two anti armor missiles on each stub wing endplate. Four underwing hardpoints for rockets and guns. Operators. Afghanistan, Algeria, Angola, Armenia, Azerbaijan, Bulgaria, Croatia, Cuba, Czech Republic, Hungary, India, Iraq, Libya, Mozambique, Peru, Poland, Russia, Rwanda, Slovakia, Syria, Ukraine, USA, Yemen. History. Mil's feared 'Devil's Chariot' is unique in that it is a combined armed assault/attack helicopter, although the latter is its primary role.

The Mi-24 is based on the dynamic systems of the Mi-8 transport helicopter, although almost all production aircraft featured the uprated TV3 turboshafts and port side tail rotor of the upgraded Mi- 17. Design considerations were speed and firepower. First flight of the V-24 prototype was in 1973, while production Mi-24 'Hind-As' entered service in 1973. Early production 'Hind-A's, 'Hind-B's and 'Hind-C's feature a glasshouse style cockpit for the pilot and weapons operator which offered poor visibility and protection. The Mi-24D 'Hind-D' and export Mi-25 introduced the definitive stepped and armored cockpits, plus the four barrel 12.7mm machine gun in an undernose turret plus undernose missile guidance and electro optical pods. The similar Mi-24V'Hind-E' (or Mi-35 for export) introduced the stubwing endplates for 9M1 14 (AT-6 'Spiral') anti armor missiles and a HUD for the pilot. The Mi-24VP introduced a twin barrel GSh-23L cannon on the starboard fuselage side as operational experience in Afghanistan found the original gun ineffective against some targets, while the Mi-24P 'Hind-F' (and export Mi-35P) has a twin 30mm cannon. The Mi-24RKR and Mi-24K NBC reconnaissance platforms. Finally Mil is developing the Mi-35M, an upgraded Mi-24 featuring the Mi-28's rotors and transmission, a 23mm cannon and 91K114-9 Ataka advanced anti armor missiles, Sextant Avionique of France avionics and displays and Thomson-TTD Chlio FLIR ball." (source: International Directory of Military Aircraft 1998-1999)

MOSKOVSKY VERTOLETNY ZAVOD IMIENI M L MILYA AOOT (Moscow Helicopter Plant named for M L Mil JSC)

ARSENYEV - ARSENYEVSKOYE AVIATSIONNOYE PROIZVODSTVENNOYE PREDPRIYATIE IMENI N I SAZYKINA (Arsenyev Aviation Production Enterprise `Progress' named for N I Sazykin)

MANUFACTURER DETAILS

prospekt Lenina 5, 692335 Arsenyev, Primovsky Kray Tel: (+7 423) 612 48 97 Fax: (+7 423) 612 61 30

General Director: Vladimir Pechyonkin

Arsenyev plant previously built the Mil Mi-24/25/35 series of combat helicopters, in parallel with Rostvertol, and was also manufacturer of the Yak-55 aerobatic lightplane; a modified version of the last-mentioned, the Technoavia SP-55, was returned to production in 1999, in an initial batch of five, two of which delivered to Technoavia by October 2000. Arsenyev is responsible currently for the Kamov Ka-50 (including, if ordered, the Ka-50-2 export version) and Mil Mi-34 helicopters, as well as Moskit missiles. It has been assigned the new Kamov Ka-60. Russian government shareholding is 51 per cent. A government decree of 31 December 1997 authorised the Arsenyev plant to offer the Ka-50 for export and supply spares and support for existing Mi-24/25/35 helicopters. Overseas delivery of P-15U, P-20, P-21 and P-22 cruise missiles is also covered.

ROSTVERTOL - ROSTOVSKY VERTOLETNYI PROIZVODSTVENNYI KOMPLEKS OAO `ROSTVERTOL' (`Rostvertol' Rostov Helicopter Production Complex JSC)

MANUFACTURER DETAILS

ulitsa Novatorov 5, 344038 Rostov-na-Donu Tel: (+7 8632) 31 74 93 Fax: (+7 8632) 45 05 35 e-mail: rostvertol@rost.ru

Director General: Boris N Slyusar Deputy Director General: Yuri Zaikin Deputy Director-General, Marketing and Sales: V Dyatlov Chief Engineer: I Semyonov

The company now known as Rostvertol was founded on 1 July 1939, and began by manufacturing wooden propellers. It progressed to aircraft production during the Second World War and to helicopter work in the mid-1950s. Past products at Rostov-on-Don included the UT-2M (1944), Po-2, Yak-14 glider, Il-10M, Il-40, Mi-1, Mi-6, Mi-10 and Mi-10K. Rostvertol is wholly privately owned. Government decree of 19 February 1996 authorises Rostvertol to export spares and auxiliary equipment for Mil Mi-24 and Mi-25; and to export new Mi-26, Mi-28 and Mi-35 helicopters, as described in the Mil Moscow

Helicopter Plant entry. Production in 1999 included one Mi-26 delivered to the Moscow fire brigade for water-bombing and rescue duties. Mi-26 supplied to Mexican Air Force in January 2000 and second ordered in following April. Rostvertol also active in helicopter overhaul and upgrading. However, independent export sales authorisation rescinded 23 July 1999, and Rostvertol exports now made through official Russian agencies. Company has exported 650 aircraft.

MIL Mi-24, Mi-25 and Mi-35 NATO reporting name: Hind

Type Attack helicopter.

Programme Development began second half of 1960s, as first fire support helicopter in former USSR, with accommodation for eight armed troops. Complete redesign after construction of 1966 Bell UH-1-sized mockup with skid-type landing gear and side-by-side cockpit. Mil issued with directive to submit new plans in 1967, building three new mockups with five alternative forward fuselage arrangements. All featured replacement of fixed GSh-23 twin-barrelled cannon with faster-firing machine gun in powered turret, and provision for 9M114 Shturm V (AT-6 `Spiral') ATMs; 10.5 tonne aircraft, with two JV3-117A engines, chosen over lighter single-engined alternative. This aircraft (Izdelie 240) based on Mi-14 dynamic system, with streamlined new fuselage. Two V-24 prototypes built by MVZ 329 (the Mil workshops) at Panki; first flight 19 September 1969; 10 preseries Mi-24s followed, five built by MVZ 329, five by Progress (MVZ 116) at Arsenyev. State acceptance trials June 1970 to December 1971. All with TV3-117A engines, not TV2-117 as sometimes reported. First reported in West and production started 1972; photographs became available 1974, when two units of approximately squadron strength based in East Germany; reconfiguration of front fuselage changed primary role to gunship; new version first observed 1977; used operationally in Afghanistan, Angola, Chad, Chechnya, Iran/Iraq war, Nicaragua and Sri Lanka, when at least one Iranian F-4 Phantom II destroyed by 9M114 (AT-6 `Spiral') anti-tank missile from Mi-24; peak production rate at Progress plant, Arsenyev, was 165 a year but tooling there dismantled, 1989. Late models continue to be available from Rostvertol at Rostov-on-Don, where production continues at low rate for export and for Interior Ministry.

Current Versions Mi-24 (Izdelie 240 `Hind-B'): Prototypes and pre-series aircraft with simple tapered wing with no anhedral and simple underslung BD3-57Kr-V racks. Pilot (offset to port) and WSO (forward) in tandem under heavily glazed cockpit. One modified in 1975 as `A-10' for successful speed record attempts with wings removed and faired over and with inertia-type dampers on the main rotor head. TV3-117A engines. One later used to test Fenestron tail rotor. Mi-24A (Izdelie 245 `Hind-A'): Initial production version; similar heavily glazed angular cockpit to prototypes and preseries aircraft, but with extended forward fuselage, giving more pointed nose in plan view and with less steeply pitched `roof' glazing. Single-barrel Afanasyev A-12.7 (TKB-481) 12.7 mm machine gun in NUV-1 flexible mounting in tip of nose underside. Aimed using simple PKV collimator gunsight. Pilot's door (on port side) replaced by large sliding bubble window. WSO still entered through upward-opening side window. Fuselage stretched to accommodate Raduga-F (Rainbow-F) semi-automatic command to line-of-sight missile guidance system, presence of which was indicated by small teardrop fairing in front of nose landing gear. Armed with manually guided 9M17M (AT-2 `Swatter') ATGMs. Anhedral added to stub wings to improve lateral stability and cure high-speed Dutch roll. ATM launch rails relocated from fuselage sides to new endplate pylons at wingtips. Two Mi-24A prototypes produced by grafting new nose on to pre-series Mi-24s; entered production at Arsenyev in 1970. Mi-24U (Izdelie 244 `Hind-C'): Unarmed pilot conversion trainer based on Mi-24A, but lacking nose-mounted gun, wingtip missile launch rails and undernose Raduga antenna. Instructor in former WSO position, with full dual controls and instruments. Built at Arsenyev in small numbers, with others possibly produced by conversion of redundant Mi-24/Mi-24As. Mi-24F? (Izdelie 245M `Hind-A'): Inadequate tail rotor authority led to replacement of starboard pusher tail rotor by tractor tail rotor on port side from 1972. Seven reinforcing ribs added to port fuselage aft of wing, SRO-2M Khrom (`Odd Rods') IFF antenna relocated from canopy to oil cooler; APU exhaust extended and angled downwards. Total production of Mi-24, Mi-24A, Mi-24U and Mi-24F about 240, ending in 1974. Mi-24B (Izdelie 241 `Hind-A'): Up-gunned and improved model with new 12.7 mm Yakoushev/Borzov YakB (TKB-063 or 9A624) 12.7 mm four-barrel machine gun in USPU-24 powered chin turret, traversable through 120є in azimuth and from +20 to -40є in elevation/depression, and slaved to KPS-53AV sighting system. Manually controlled ATGMs replaced by 9M17P Falanga-P and Falanga-PV with SACLOS guidance. Traversing radio command link antenna moved from centreline to below port side of nose, with gyrostabilised collimated LLTV/FLIR under starboard side in fixed fairing. Passed company trials 1971-72 but overtaken by Izdelie 246 (`Hind-D') and abandoned. Full-scale mockup produced from pre-series Mi-24 with undrooped wing, prototype from early Mi-24A with normal anhedral wing. Retained fully retractable landing gear like all previous Mi-24 variants.

Mi-24D (Izdelie 246; `Hind-D'): Interim gunship version combining `old' weapon system of Mi-24B with new airframe designed for planned Mi-24V due to delays with that aircraft's Shturm-V ATGMs with SPS-24V fire-control system, consisting of KPS-53AV weapons control unit and KS-53 gunsight; design began 1971; two prototypes converted from Mi-24A, with starboard-side tail rotor; entered production at Arsenyev and Rostov plants 1973; about 350 built 1973-77. Basically as late model `Hind-A' with TV3-117 engines and port-side tail rotor, but entire front fuselage redesigned above floor forward of engine air intakes; separate armoured cockpits for weapon operator and pilot in tandem; flight mechanic optional, in main cabin; transport capability retained; USPU-24 gun system, with range-finding; undernose YakB-12.7 four-barrel 12.7 mm machine gun in turret, slaved to adjacent KPS-53A electro-optical sighting pod, for air-to-air and air-to-surface use; long air data boom with DUAS-V pitch and yaw vanes; Falanga P anti-tank missile system; nosewheel leg extended to increase ground clearance of sensor pods; wing pylons plumbed for 500 litre (132 US gallon; 110 Imp gallon) drop tanks; nosewheels semi-exposed when retracted; S-13 camera moved from port wingroot to port wingtip/endplate junction. Mi-24DU (Izdelie 249) dual-control training version has no gun turret. (See also Mi-25.) Mi-24PTRK was testbed for Shturm V missile system of Mi-24V. Detailed description applies to Mi-24D, except where indicated. Mi-24V (Izdelie 242; `Hind-E'): Up-engined, improved version powered by TV3-117V engines (V = vysotnii `high-altitude') rated at 1,633 kW (2,190 eshp). Airframe as Mi-24D, but modified wingtip launchers and four underwing pylons; empty weight 8,620 kg (19,004 lb); weapons include up to eight 9M114 (AT-6 `Spiral') radio-guided tube-launched anti-tank missiles in pairs in Shturm V (Attack) missile system; fixed enlarged undernose automatic missile guidance pod on port side (antenna inside was articulated), with fixed searchlight to rear; ASP-17V gunsight for pilot; R-60 (K-60; AA-8 `Aphid') air-to-air missiles optional on underwing pylons; pilot's HUD replaces former reflector gunsight. Deliveries to Soviet Air Force began 29 March 1976; about 1,000 built at Arsenyev and Rostov 1976-86. From 1981 usually with PZU filters over engine intakes, and, from 1984, with provision for triple-lobe IR filter boxes over downward-pointing exhausts and an L-166V-11E Ispanka (Spaniard) or SOEP-V1A `Lipa' IR jammer on `Wendy House' fairing. R-863 VHF, R-828 army radio, SRO-2M IFF replaced by SRO-1P Parol L-006LM Beryoza RHAWS on late aircraft. (See also Mi-35.) Mi-24V (Mi-24VD; D = Dorabotanni: Terminator): High proportion of combat losses in Afghanistan inflicted from the rear hemisphere. Mi-24VD produced in 1985 as testbed for rearward-firing defensive armament. Bulged gondola installed in place of rear avionics bay, accessed via narrow crawlway. Equipped with 12.7 mm NSVT-12.7 Utyos machine gun. Gunner entered turret in flight, legs dangling into the slipstream, encased in built-in rubberised fabric `trouser' bag. Project abandoned 1986. Mi-24VM/Mi-24PM/Mi-35M: (`Hind-E'): Mil Design Bureau three-stage, five-block MLU configuration for estimated 200 surviving RFAS Mi-24V/Mi-24P. (Stages 1, 2 and 3 equate to Blocks 2, 3 and 4). Will extend retirement dates from 2004 (Mi-24D) and 2010 (Mi-24V/P). Exact content of RFAS upgrade (and correct designation) confused by appearance of static demonstrators at Paris and MAKS air shows. These had mix of features from different stages of planned RFAS upgrade, and some aspects designed primarily to attract export customers (and later incorporated in Stage 3), including Sextant/Thomson-CSF Nadir 10 navigation system and NOCAS (Night Operation Capable Avionics System). Some sources suggest Mi-24VM designation will apply to Mi-24V or Mi-24VP after upgrade, and Mi-24PM to upgraded Mi-24Ps. Others maintain that the PM suffix applies only to aircraft which retain fixed 30 mm cannon associated with Mi-24P. Three Mi-24VM prototypes flying by late 1999: one with TV3-117VMA-SB3 engines; second for trials of GOES-342 sighting unit; third with new main and tail rotors. Designation Mi-24VK-1 assigned to night trials prototype with unspecified equipment, flying by late 2000; an Mi-24VK-2 was due to have joined the programme in December 2000. Actual Mi-24VM upgrade consists of: Block 1: Life extension to 4,000 flying hours/40 years. May be carried out in parallel with Stage 1/Block 2. Stage 1: Aircraft brought to Mi-24VM-1/Mi-35M1 standard with Geofizika NVG-compatible cockpit (LCD MFDs, embedded GPS/INS). Glass fibre main rotor blades (with greater thrust) and Mi-28-type Delta-H tail rotor, 1,636 kW (2,194 shp) TV3-117VMA or 1,839 kW (2,466 shp) TV3-117VMA-SB3 engines, extra oil cooler and more powerful KAU-115 control system actuators. Existing machine gun or 30 mm cannon armament replaced by Mi-24VP's NPPU-24 turret with GSh-23l cannon. Outer part of wing, endplate fins and existing missile launchers removed, with APU-8/4U launchers (eight 9M114 ATMs each) on remaining four (BD3-UV) underwing pylons, which have built-in hoists. S-13 attack camera replaced by SSh-45 (monitored in pilot or WSO sight). Strengthened, non-retracting landing gear. (Wing and landing gear, modifications incorporated in prototype, but believed planned as part of second stage). Reduced empty operating weight (8,350 kg/18,409 lb), compared to Mi-24V. Prototype converted from Mi-24VP (`51' of Berkuty formation team) first flew on 8 and 11 February, before official maiden flight on 4 March 1999. Six production conversions to be delivered during 2000. Stage 2: Aircraft brought to Mi-24VM-2/Mi-35M2 standard with Mi-28N main rotor; GSh-23L replaced by liquid-cooled GSh-23V (vodyanoye okhlazhdniye: water cooling), with 450 rounds. Communications system improvements include lightweight tactical datalink and R-999 VHF radio. New or revised ATM guidance compatible with passive IR-homing 9M39 (SA-18 `Grouse') Igla AAM in place of the 9M36 (AT-14 `Gremlin'). Stage 3: Aircraft brought to Mi-24VM/Mi-35M3 standard with new digital PNK-24 avionics suite, closely based on PrNK-28 of Mi-28N. Zenit Tor-24 weapon control system replaces Raduga-F. Shturm V ATM replaced at Ataka V (9M120 AT-12 `Swinger'). L-166V-1E deleted and replaced by Mak-UFM IR- and Otklik laser-MAWS. Beryoza RWR replaced by Pastel RHAWS controlling UV-26 chaff/flare dispensers. Empty operating weight further reduced to 8,200 kg (18,078 lb), with

commensurate improvement in hover, speed and range performance. Block 5: Incorporates NVG-compatible cockpit and FLIR, laser range-finder, helmet-mounted displays and new navigation/display system software to optimise low-level/short duration mission capability. Originally planned to have Sextant/Thomson NOCAS with Chlio FLIR in turret mounted on port side of forward fuselage, TMM-1410 LCD MFD in WSO cockpit and SMD-45H and TMM-1410 in pilot's cockpit, together with VH 100 HUD. French Chlio FLIR replaced by UOMP GOES-342 (OPS-24N) TV/FLIR sighting unit (similar to Shamshit of Ka-50Sh) with Swedish AGEMA FLIR. French MFDs probably replaced by indigenous MFI-10 or MFI-68 152 Ч203 mm (6 Ч 8 in) MFDs. GOES-342 also offered as heart of upgrade proposed to Poland in late 1997. Arsenal Mi-24V upgrade: Ukrainian upgrade configuration centred around French (Elno) developed Sura HMTDS (helmet-mounted target designation system) for pilot and WSO. NVG-compatible cockpit, new ASP-17VM gunsight computer and INS with embedded GPS. Improved weapon-aiming algorithms. Single aircraft converted as demonstrator by Arsenal, Kiev. Mi-24VP (Izdelie 258): Final basic Army Aviation production version, based on Mi-24V with twin-barrel GSh-23L 23 mm gun in NPPU-24 flexible mount with 450 rounds, in place of four-barrel 12.7 mm gun in nose; photographed 1992; small production series of 25 built at Rostov, entering service in 1989. Production curtailed by ammunition feed problems. One VP flew with Mi-28-type Delta H tail rotor. `Mi-24VU' (`Hind-E'): No dedicated trainer version of Mi-24V produced by OKB or factories for Russian or former Soviet Army. India uses small number of these trainer versions (possibly locally converted) with gun turret removed and faired over, and with dual controls and instruments for instructor in front cockpit. Mi-24VU, Mi-25VU and Mi-35U designations may be unofficial, even in India. Mi-24P (Izdelie 243; `Hind-F'): Development started 1974; about 620 built 1981-89; first shown in service in 1982 photographs; P of designation refers to pushka: cannon; as Mi-24V, but nose gun turret replaced by GSh-30K twin-barrel 30 mm gun (with 750 rounds) in semi-cylindrical pack on starboard side of nose; bottom of nose smoothly faired above and forward of sensors. Alternative Mi-24G has gun on starboard side. Mi-24RKhR or Mi-24R (Izdelie 2462 `Hind-G1'): Dedicated NBC reconnaissance aircraft to replace Mi-8VD. RKhR = dlya Radiatseeonno-Khimeccheskoi Razvedki (NBC reconnaissance). Identified at Chernobyl after April 1986 accident at nuclear power station; no undernose electro-optical and RF missile guidance pods, strike camera deleted, but pylons for underwing stores retained; instead of wingtip weapon mounts, has `clutching hand' excavator mechanisms on lengthened pylons, to obtain six soil samples per sortie, for NBC (nuclear/biological/chemical) warfare analysis; air samples sucked in via pipe on port side, forward of doors exhausting through horizontal slit above; datalink to pass findings to ground; lozenge-shape housing with exhaust pipe of air filtering system under port side of cabin; bubble window on starboard side of main cabin; small rearward-firing marker flag/flare pack on tailskid; crew of four wear NBC suits; deployed six per helicopter regiment throughout Russian Federation and Associated States (CIS) ground forces. About 152 built 1983-89. Mi-24RA (Izdelie 2462 [or 2463?] `Hind-G1 Mod'): New series of conversions from Mi-24V. Retained strike camera in wingroot and lacked wingtip excavators; sometimes seen with pod on port station. Crew reduced to three with improved (presumably automated) processing and data transfer. Probably had slightly different and more specialised role - only one known in Group of Soviet Forces in Germany, for example. Mi-24K (korrektirovchik: corrector) (Izdelie 201 `Hind-G2'): Dedicated artillery spotter/fire correction aircraft to replace Mi-8TARK. As Mi-24R, but with large A87P or AFA-100 camera in cabin, f8/1,300 mm lens on starboard side; six per helicopter regiment for reconnaissance and artillery fire correction; gun and B-8V-20 rocket pods retained. No target designator pod under nose; upward-hinging cover for IRIS wide-angle IR and optical sensor system. Rita reconnaissance and spotting system with optical target identification, computer and data processor. About 163 built 1983-1989. Mi-24BMT (Izdelie 248): A few modified 1973 for minesweeping. Mi-24VN (Mi-35O `Hind-E'): Interim night-attack version based on conversion of Mi-24V in Mi-24VM Stage 1 configuration. Cockpit and external lights compatible with Geo-ONV-1 NVGs and with new RPKB navigation/fire-control system. May also feature GOES-320 gyrostabilised sensor turret containing Sony EVI331 TV and Agema THV1000 FLIR sensors (for navigation/surveillance, not targeting) or a similar GOES-342 turret with a targeting function for the 9M120 (AT-12) ATMs. Some reports suggest that Mi-24VNs were to be used by Experimental Combat Group in Chechnya. A similar upgrade configuration, with A737 GPS and using two MFI-68 cockpit displays for the pilot (one replacing the S-17V gunsight, one functioning as a colour LCD terrain map), and an MFPU console for the gunner, has been prepared for an unnamed customer. Performance generally as for Mi-24V/Mi-24P. Mi-24PN: Preliminary tests reportedly under way in mid-2000. Presumed to be a 30 mm cannon-armed `Hind-F' upgraded with Geofizika FLIR, new laser range-finder, mission computer and NVG-compatible cockpit. Possibly equivalent to Mi-24VN. Mi-24PS (Patrul'nospasatelny: patrol/rescue): Transport/law enforcement/SAR variant for Russian Ministry of the Interior. Production or series conversion status unknown. First prototype converted from Mi-24P, retaining 30 mm cannon and wing endplate pylons. Undernose LLTV/FLIR replaced by downward-pointing loudspeaker group, ATGM guidance antenna by FPP-7 searchlight. Nose cut away to allow installation of weather radar and EO turret. LPG-4 winch (120 kg; 264 lb capacity) installed aft of starboard cabin door, grab rails, foot rests and rappel attachment points around sides of doors. Four of six-man squad carried can rappel from the aircraft simultaneously. Satellite communications, secure encrypted

voice radios and special police-band radios. Second prototype similar (albeit painted white, with blue cheatlines and Militia titles) but converted from Mi-24V, with USPU-24 turret replaced by FLIR ball. Marketed as Mi-35PS for export. Mi-24 Ecological Survey Version: Modification by Polyot industrial research organisation, to assess oil pollution on water and seasonal changes of water level. First seen 1991 with large flat sensor `tongue' projecting from nose in place of gun turret; large rectangular sensor pod on outer starboard underwing pylon; unidentified modification replaces rear cabin window on starboard side. Mi-25: Export Mi-24D, including those for Afghanistan, Angola, Cuba, India and Peru. Also Mi-35D. Mi-35: Export Mi-24V also known as Mi-25V. Mi-35D: Upgrade configurations for export. Sub-variants designated Mi-35D, Mi-35D1 and Mi-35D2, using various weapons and systems from the Kamov Ka-50. Proposed by Rostvertol but not supported by Mil OKB. Borrowed equipment to include Shkval fire-control unit, Saturn FLIR and Vikhr ATMs. Probably abandoned and replaced by joint Mil/Rostvertol upgrade configuration with 1,839 kW (2,466 shp) TV3-117VMA-SB3 engines which give 10 per cent greater power output, and increase engine TBO to 3,000 hours, and life to 7,500 hours. This new upgrade configuration could include redesigned main and tail rotors, together with avionics developed by Ramenskoye and Krasnogorsk. Mi-35P: Export Mi-24P. Mi-35M: Upgraded night-capable version of Mi-24/35; export counterpart of Mi-24M; designed to meet the latest air mobility requirements of the Russian Army. Features include Mi-28 main and tail rotors and transmission; 1,636 kW (2,194 shp) Klimov TV3-117VMA engines; new avionics; a reduced empty weight resulting from new titanium main rotor head, composites rotor blades, shortened stub-wings and non-retractable landing gear; a 23 mm GSh-23-2 twin-barrel gun in nose turret, with 470 rounds; up to 16 radio-guided 9M114 (AT-6 `Spiral'), or laser-guided 9M-120 anti-tank, 9M-120F blast fragmentation or 9A-220 air-to-air versions of Ataka (AT-12) missile; or a range of armament options including GUV gun/grenade pods; UPK-23-250 gun pods; B-8V-20A and B-13L rocket pods; S-24B rockets; and KMGU pods of anti-armour and anti-personnel mines. Night Operation Capable Avionics System (NOCAS) by Sextant Avionique and Thomson-TTD Optronic integrates Chlio FLIR ball with a TMM-1410 display, providing night vision for target acquisition and identification, missile guidance and gun aiming. Other equipment includes a VH-100 HUD, NVGs, liquid-crystal MFD, Nadir 10 mission management and navigation system, laser-gyro INS and GPS. The FLIR ball is mounted outboard of the standard missile guidance pod. Ability to carry Igla V air-to-air missiles is optional. Non-flying demonstrator first displayed at 1995 Paris Air Show. ATE `Super Hind': Upgrade configuration proposed by South Africa's Advanced Technologies and Engineering. Derived from Denel/Kentron PZL Swidnik W-3WB upgrade. Extended nose in front of cockpit with undernose IST Dynamics turret, Kentron IR/EO sight and Denel Vektor G12 20 mm chain gun (as used by Rooivalk), cheek fairings both sides for ammunition feed, designator, improved displays, new night vision systems and provision for Denel/Kentron Ingwe or Mokopa ATMs. Prototype Mi-24V ZU-BOI delivered for modifications 26 June 1998; rolled out at Grand Central Airport, Midrand, by 15 February 1999. Customer believed to be Algeria. Tamam Mi-24 HMOSP (`Mission 24'): Israeli upgrade configuration. US$20 million contract placed for upgrade of 25 (probably Indian) Mi-24s based on existing Helicopter Multimission Optronic Stabilised Payload system, with MLM mission computer, TV, FLIR and automatic target tracker, NVG-compatible cockpit integrated with monocular helmet sight, digital moving map, integrated DASS, embedded GPS, and a new mission planning system. FLIR FoV variable from 2є 24' to 29є 12' and with built-in automatic tracking. Cannon can be slaved to pilot or WSO's line of sight. Compatible with Rafael Spike ATM and to be fitted with IMI chaff/flare dispensers. Cockpits have new LCD MFDs and can be reorganised to put pilot in front, weapon operator in rear.

Customers Reported 5,200 produced at Arsenyev and Rostov, including 1,000 exported to over 30 countries; about 700 in Russian Army service, most with helicopter attack regiments of Mi-8/17s and Mi-24s; one supplied to Russian army aviation in 1994 and seven in 1995.

`HIND' OPERATORS

Customer Variant Delivered/Remaining Date

Afghanistan Mi-24A, U, 25, 35 36 plus top-ups/0 1979

Algeria Mi-24A, 24D 38/c 33-35 1978

Angola Mi-25, 35, 35P 36+/20-28 1983

Armenia Mi-24P, K, RKhR 7 P, 3 K, 2 RKR/12 1991

Azerbaijan Unknown C 15 1991

Belarus Mi-24D, V, K, RKhR Unknown/61 1991

Bosnia Mi-35 Five reportedly ordered

Bulgaria Mi-24D, 24V 38 D, 6 V/35 and 5 1979

Cambodia Unknown ex-Vietnamese c 1985

Congo Unknown Unknown 1997

Croatia Mi-24V 15 + 5/15 1993

Cuba Mi-24D 20/c 15 1982

Czechoslovakia Mi-24D, DU, V 28 D, 2 DU, 32 V/0 1978

Czech Republic Mi-24D, DU, V 16 D, 1 DU, 20 V/361 1993

Ethiopia Mi-24D, Mi-35 40 +?/30 1980

France Mi-25D, ex-Libyan 3/0 1987

Georgia Unknown 4/3 1991

East Germany Mi-24D, Mi-24P 42 D, 12 P/0 1978

Germany Mi-24D, Mi-24P 39 D, 12 P/0 1990

Hungary Mi-24D, Mi-24V 30 D, 11 V/29 + 102 1978

India Mi-25 Akbar, Mi-35 12 D, 20 35/32 1984

Iraq Mi-25 Unknown/c 30 c 1979

Kazakhstan Mi-24D, V 42 1991

Kyrgizia Unknown 50/most stored 1991

Libya Mi-24A, 25, 35 Unknown/c 65 c 1978

Mongolia Mi-24V 12/survivors stored c 1990

Mozambique Mi-25 15/4 1984

Nicaragua Mi-25 12-18/0 1983

Nigeria Mi-35P 6/6 2000

North Korea Unknown/c 20 1985

Peru Mi-25 12 + 73/10 + 5 c 1982

Poland Mi-24D, V 16 + 22D4, 23 V/41 1978

Russia Mi-24D, V, P, VP, K, RKhR c 700* 1972

Rwanda Unknown 2 1997

Sierra Leone Mi-24V 3/2 serviceable

Slovakia Mi-24D, DU, V 8 D, 1 DU, 10 V/19 1993

Sri Lanka Mi-24V 13/7 1995

Sudan Mi-24V ex-Belarus 6/5 1996

Syria Mi-24D, Mi-25 50/36 1980

Tajikistan Unknown c 5 1991

Turkmenistan Unknown 10 1991

Uganda Unknown 2 ex-Belarus5

Ukraine Mi-24D, V, P, K RKhR 278/more than 50 stored 1991

UK Mi-25 1 ex-Libyan briefly evaluated c 1989

USA Mi-24D, Mi-24P 2 ex-German + captured Iraqi6

Uzbekistan Mi-24D, V c 45 1991

Vietnam Mi-24, 24A, 24D, 25 30/? c 1984

Yemen Mi-24D/25 15/12?

Zimbabwe Mi-35 5/5 1999

Notes: Several Mi-24s were acquired for Papua New Guinea, but none entered service. Massoud guerilla forces in Afghanistan have six operating from Kulob (Tajikistan) (1997). `Serbian Police' Mi-24s have been reported. Rostvertol notes `Mi-35' to be in service with 26 air arms by late 2000. 1 25 in use, four Ds and eight Vs stored

2 16 ex-German Mi-24s (11 24D, five P) acquired for third squadron, but not put into service

3 ex-Nicaraguan aircraft (possibly only five purchased)

4 22 ex-German Mi-24D, 12 of which were in service by late 1997

5 Returned to CSC in dispute, 1999. Allegedly not overhauled before 1998 delivery

6 ex-Iraqi aircraft not flown

* some sources

Design Features Typical helicopter gunship configuration, with stepped tandem seating for two crew and heavy weapon load on stub-wings; fuselage unusually wide for role, due to requirement for carrying eight troops; dynamic components and power plant originally as Mi-8, but soon upgraded to Mi-17-type power plant and port-side tail rotor; VR-24 main gearbox. Main rotor blade section NACA 230, thickness/chord ratio 11 to 12 per cent; tail rotor blade section NACA 230M; stub-wing anhedral 12є, incidence 19є; wings contribute approximately 25 per cent of lift in cruising flight; fin offset 3є.

Structure Five-blade constant chord main rotor; forged and machined steel head, with conventional flapping, drag and pitch change articulation; each blade has aluminium alloy spar, skin and honeycomb core; spars nitrogen pressurised for crack detection; hydraulic lead/lag dampers; balance tab on each blade; aluminium alloy three-blade tail rotor; main rotor brake; all-metal semi-monocoque fuselage pod and boom; 5 mm hardened steel integral side armour on front fuselage; all-metal shoulder wings with no movable surfaces; swept fin/tail rotor mounting; variable incidence horizontal stabiliser.

Landing Gear Tricycle type; rearward-retracting steerable twin-wheel nose unit; single-wheel main units with oleo-pneumatic shock-absorbers and low-pressure tyres, size 720Ч320 on mainwheels, 480Ч200 on nosewheels. Main units retract rearward and inward into aft end of fuselage pod, turning through 90є to stow almost vertically, discwise to longitudinal axis of fuselage, under prominent blister fairings. Tubular tripod skid assembly, with shock-strut, protects tail rotor in tail-down take-off or landing.

Power Plant Two Klimov TV3-117MT turboshafts, each with T-O rating of 1,434 kW (1,923 shp), side by side above cabin, with output shafts driving rearward to main rotor shaft through combining gearbox. There is 5 mm hardened steel armour protection for engines. Main fuel tank in fuselage to rear of cabin, with two bag tanks behind main gearbox and two under floor. Internal fuel capacity 2,130 litres (563 US gallons; 469 Imp gallons), of which 2,050 litres (542 US gallons; 451 Imp gallons) are usable; can be supplemented by two 850 litre (225 US gallon; 187 Imp gallon) auxiliary tanks in cabin (Mi-24D); provision for carrying (instead of auxiliary tank) up to four external tanks, each 500 litres (132 US gallons; 110 Imp gallons), on two inner pylons under each wing. Optional deflectors and separators for foreign objects and dust in air intakes; and IR suppression exhaust mixer boxes over exhaust ducts.

Accommodation Pilot (at rear) and weapon operator on armoured seats in tandem cockpits under individual canopies; dual flying controls, with retractable pedals in front cockpit; if required, flight mechanic on jump-seat in cabin, with narrow passage between flight deck and cabin. Front canopy hinged to open sideways to starboard; footstep under starboard side of fuselage for access to pilot's rearward-hinged door; rear seat raised to give pilot unobstructed forward view; anti-fragment shield between cockpits. Main cabin can accommodate eight persons on folding seats, or two stretchers, two seated casualties and a medical attendant; seats often not fitted, allowing larger numbers to be carried; at front of cabin on each side is a door, divided horizontally into two sections hinged to open upward and downward respectively, with integral step on lower portion. Optically flat bulletproof glass windscreen, with wiper, for each crew member.

Systems Cockpits and cabin heated and ventilated. Dual electrical system, with three generators, giving 36, 115 and 208 V AC at 400 Hz, and 27 V DC. Retractable landing/taxying light under nose; navigation lights; anti-collision light above tailboom. Stability augmentation system. Electrothermal de-icing system for main and tail rotor blades. AI-9V APU mounted transversely inside fairing aft of rotor head for engine starting and ground services.

Avionics Comms: R-860/863 and Karat M24 com; SPU-8 intercom. Flight: VUAP-1 autopilot, ARK-15M radio compass, ARK-U2 radio compass, RV-5 radio altimeter. Instrumentation: Blind-flying instrumentation, and ADF navigation system with DISS-15D Doppler-fed mechanical map display. Air data sensor boom forward of top starboard corner of bulletproof windscreen at extreme nose. Mission: Undernose pods for electro-optics (starboard) and Raduga-F semi-automatic missile guidance (port). Many small antennas and blisters, including SRO-2 Khrom (`Odd Rods') IFF transponder. Self-defence: SPO-15 Beryoza RWR. IR jammer (L-166V-1E Ispanka microwave pulse lamp: `Hot Brick') in `flower pot' container above forward end of tailboom. ASO-2V flare dispensers under tailboom forward of tailskid assembly initially; triple racks (total of 192 flares) on sides of centre-fuselage from 1987, due to combat experience in Afghanistan.

Equipment Gun camera on port wingtip. Colour-coded identification flare system.

Armament One remotely controlled YakB-12.7 four-barrel Gatling-type 12.7 mm machine gun, with 1,470 rounds, in VSPU-24 undernose turret with field of fire 60є to each side, 20є up, 60є down; gun slaved to KPS-53AV undernose sighting system with reflector sight in front cockpit; four 9M17P Skorpion (AT-2 `Swatter') anti-tank missiles on 2P32M twin rails under endplate pylons at wingtips; four underwing pylons for UB-32 rocket pods (each 32 S-5 type 57 mm rockets), B-8V-20 pods each containing twenty 80 mm S-8 rockets, B-13L pods each containing five 130 mm S-13 rockets, 240 mm S-24B rockets, UPK-23-250 pods each containing a GSh-23L twin-barrel 23 mm gun, GUV pods each containing either one four-barrel 12.7 mm YakB-12.7 machine gun with 750 rounds and two four-barrel 7.62 mm 9-A-622 machine guns with total 1,100 rounds or an AGS-17 Plamia 30 mm grenade launcher with 300 grenades, up to 1,500 kg (3,300 lb) of conventional bombs, mine dispensers, night flares or other stores. R-60 (AA-8 `Aphid'), R-73 (AA-11 `Archer') and Igla AAMs fitted experimentally. Helicopter can be landed to install reload weapons carried in cabin. PKV reflector gunsight for pilot. Provisions for firing AKMS guns from cabin windows and PK or PKT machine gun from door mounts.

Dimensions, External (A: Mi-24P, B: Mi-35M, C: Mi-24V/-35 alternative official figures)

Main rotor diameter: A 17.30 m (56 ft 9ј in)

B 17.20 m (56 ft 5ј in)

Main rotor blade chord: A 0.58 m (1 ft 10Ѕ in)

Tail rotor diameter: A 3.91 m (12 ft 10 in)

B 3.84 m (12 ft 7ј in)

Wing span: A 6.66 m (21 ft 10ј in)

B 5.06 m (16 ft 7ј in)

Width of fuselage: A, B 1.70 m (5 ft 7 in)

Length:

excl rotors and gun: A, B 17.51 m (57 ft 5ј in)

rotors turning: A 21.35 m (70 ft 0Ѕ in)

B 21.27 m (69 ft 9Ѕ in)

Height: to main rotor tip, turning:

A, B 3.97 m (13 ft 0Ѕ in)

overall: rotors turning: B approx 5.00 m (16 ft 4Ѕ in)

Span of horizontal stabiliser: A 3.27 m (10 ft 9 in)

Wheel track: A, B 3.03 m (9 ft 11Ѕ in)

Wheelbase: A, B 4.39 m (14 ft 5 in)

Dimensions, Internal

Main cabin: Length: A 2.825 m (9 ft 3ј in)

B 2.60 m (8 ft 6ј in)

Width: A 1.46 m (4 ft 9Ѕ in)

B 1.18 m (3 ft 10Ѕ in)

Height: A, B 1.20 m (3 ft 11ј in)

Areas

Main rotor disc: A 235.06 m2 (2,530.2 sq ft)

B 232.35 m2 (2,501.0 sq ft)

Tail rotor disc: A 11.99 m2 (129.06 sq ft)

B 11.58 m2 (124.66 sq ft)

Weights and Loadings

Weight empty: A 8,570 kg (18,894 lb)

B 8,090 kg (17,835 lb)

Normal internal load: B 1,500 kg (3,307 lb)

Max external stores: A 2,400 kg (5,291 lb)

B 2,860 kg (6,305 lb)

Max slung cargo: A, B 2,400 kg (5,291 lb)

Max combat payload: B 2,860 kg (6,305 lb)

Normal T-O weight: A 11,200 kg (24,690 lb)

B 10,800 kg (23,809 lb)

C 10,900 kg (24,030 lb)

Max T-O weight: A, B 12,000 kg (26,455 lb)

attack configuration 11,500 kg (25,353 lb)

ferry, four external tanks 12,000 kg (26,455 lb)

Max disc loading: A 51.1 kg/m2 (10.46 lb/sq ft)

B 51.7 kg/m2 (10.58 lb/sq ft)

Performance

Max level speed: A 172 kt (320 km/h; 198 mph)

B 167 kt (310 km/h; 193 mph)

C 168 kt (312 km/h; 194 mph)

Cruising speed: A 145 kt (270 km/h; 168 mph)

B 140 kt (260 km/h; 161 mph)

C 151 kt (280 km/h; 174 mph)

Econ cruising speed: A 117 kt (217 km/h; 135 mph)

Max rate of climb at S/L: A 750 m (2,460 ft)/min

B 744 m (2,440 ft)/min

Service ceiling: A 4,500 m (14,750 ft)

B 5,700 m (18,700 ft)

C 5,750 m (18,860 ft)

Hovering ceiling OGE: A, ISA 1,500 m (4,920 ft)

C 1,750 m (5,740 ft)

B, ISA 3,100 m (10,180 ft)

C 3,000 m (9,840 ft)

B, ISA + 10єC 2,150 m (7,060 ft)

Combat radius: A, with max military load 86 n miles (160 km; 99 miles)

A, with two external fuel tanks 121 n miles (224 km; 139 miles)

A, with four external fuel tanks 155 n miles (288 km; 179 miles)

Range: A, standard internal fuel 243 n miles (450 km; 279 miles)

B, standard internal fuel, 5% reserves 270 n miles (500 km; 450 miles)

A, B, with four external tanks 540 n miles (1,000 km; 620 miles)

Max endurance: A 4 h

(source: Jane's All the World's Aircraft 2001-2002)