Официальный каталог МАКС 2005/Official Catalogue MAKS 2005

, V -

-2005

, - VII -- -2005. - -, - . , - - , - , , - . - , , , ., -2005 , -. , - .

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-2005

- VII -- 2005. - - -, , , , . - - . - - - - , - - . - -2005 , - .

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Austria

Australia

Belgium

Byelorussia

Bolgaria

Bahrain

Brasil

Canada

Chile

China

Columbia

Czech

Denmark

France

Finland

Germany

Gibraltar

Georgia

India

Italy

Ireland

Iran

Israel

Japan

Korea

Lithuania

Malaysia

Netherland

Poland

Russia

Slovakia

Sweden

Switzerland

Singapore

Turkey

UAE

UK

Ukrain

USA

Uzbekistan

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/ COUNTRIES PARTICIPATING

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, VII - - .

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- . - - - .

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-2005 -, , - -.

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-2005 , - .

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/ ORGANIZING COMITEE

CHAIRMAN OF THE ORGANIZING COMMITTEE

Viktor Khristenko Minister of Industry and Energy of the Russian Federation

ORGANIZER

Federal Agency on Industry of the Russian Federation

Boris Alyoshin - Head of Agency

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EXECUTIVE ORGANIZER

Aviasalon JSC

Igor Novikov - Director General

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LOCATION

Gromov Flight Research Institute

Zhukovsky, Moscow Region

Yuriy Klishin Head of the Institute

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STRATEGIC PARTNER Vneshtorgbank

GENERAL SPONSOR Savings Bank of the RF

GENERAL PARTNER Sukhoi Company (JSC)

GENERAL SPONSOR Rosoboronexport State Corporation

LEADING PARTNER -Almaz-Antei Concern JSC

OFFICIAL SPONSOR Konica Minolta

OFFICIAL SPONSOR Russian Insurance Traditions (JSC)

OFFICIAL SPONSOR Joint Stock State Insurance Company Yugoriya

OFFICIAL EVENT SPONSOR Vnesheconombank JSC

TECHNICAL EQUIPMENT PARTNERS AND SPONSORS

Mobilnye TeleSystemy (MTS) JSC

Nauservis Ltd

MB Energy Llc

-K-systems Llc

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/ CONTENTS

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.: +38 (044) 455 93 91

e-mail: [email protected]

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: , 125057, , / 77

.: (095) 926-5211, 950-5612

: (095) 151-61-50


www.airfleet.ru

Greetings from the President of Russian Federation Vladimir Putin . . . . . . . . . . . . . . . . . .3

. . . . . . . . . . . . . .

Greetings from the Russian Federation Government Chairman Mikhail Fradkov . . . . . . . .5

- -2005

List of Participating Countries . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6

Greetings from the His Holiness Alexy II

Patriarch of Moscow and all Russia . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7

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Greetings from the President of the Russian Chamber of Commerce and Industry

Evgeniy Primakov . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9

, -2005

Organizers, business partners and sponsors of MAKS`2005 . . . . . . . . . . . . . . . . . . . . . . .12

Transport map . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .16

-2005

Site plan . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20

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Business Chalets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22

-2005

MAKS`2005 Contra-agents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .24

-2005

Special programs of MAKS`2005 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .26

-2005

Information sponsors of MAKS`2005 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .30

Modern Russia and CIS` aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .32

-2005 ( )

MAKS`2005 Exhibitors List (Cyrillic alphabet) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .113

-2005 ( )

MAKS`2005Exhibitors List (English alphabet) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .118

Exhibitors layout in pavilions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .125

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-2005 ( ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .133

Index of MAKS`2005 Exhibiting Companies (Cyrillic alphabet)

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-2005 ( )

Index of MAKS`2005 Exhibiting Companies (English alphabet) . . . . . . . . . . . . . . . . . . . . .265

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/ TRANSPORT MAP

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, , : +7 095 363 62 62, : +7 095 787 60 26, : [email protected]

: www.airbp.com

77

... Air BP 1200 90 ,

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Air BP , : 2197 , 50 ; 2380

Air BP , ,, ,, ..

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2005 / SITE PLAN

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1 " " President Chalet

2-3 -2005 MAKS-2005 management

4 . ..FRI named after M.M.Gromov

5 . .. Ilushin Aviation Complex

6 ESA7

Rosoboronexport

8-9 Tupolev

10 - Russian Air Force

11 , Ramenskoye Design Company

12 Aviaexport

13 ""MiG Corporation

14-15 ""Irkut Research and ProductionCorporation

16 -

17-18 EADS19 SNECMA20 .

../Tikhomirov NIIP/SRIP

21-24 X ""AHK Sukhoi

25-26 Vneshtorgbank

27-28 , . . , Almaz Scientific Industrial Corporation named after Academician A.A. Raspletin

29 . Moscow City Administration

30 Sberbank

31 Rostvertol

32 . ..

Mil Moscow Helicopter Plant

33-34

Aviazapchast

35

Ufa Motor Building Plant

36

SPARK Saint-Petersburg Aviation

Repair Company

37

Moscow Region Administration

38 -

39 UTAir

40

Kamov

41

Lease Financing Company

42 C

43

Kharkov GAPP

44 USAFE

45

46-48 ""

NPO Saturn

49 -,

50 .

Scientific and Technical Complex of

Samara named after N.D. Kuznetsov

51 ,

52-53 .

Zhukovsky City Administration

62 " "

Russian Vitiazi Fund of assistance to

aviation Not-for-profit organization

63

TAPO named after V.P.Chkalov

64

65

66

Russian Aviation Co.

67 Exxon Mobil

68 UGS

69

AviaDelta

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Standbuilding

- ..AviaexposerviceI. Kravtsov, Director General Tel. +7 (095) 155 80 01Fax. +7 (095) 155 17 50, 125319, , ., 6666 Leningradsky pr., 125319, Moscow,Russia

- ..Sankt-Peterburg MesseV. Kuznetsov, Director GeneralTel. +7 (812), 277 25 75, 275 77 25Fax + (812) 277 17 89, 193024, -, ., 147-14147-14 Nevsky pr. Saint-Petersburg193204 Russia

Insurance

..Joint-stock Insurance CompanyRussian Insurance TraditionsI. Davidov, Director GeneralTel. +7 (095) 683 88 03, 683 87 07Fax +7 (095) 683 88 05, , ,.13, .213, Build.2, Raketny Boulevard, Moscow,Russia

..Joint-stock State InsuranceCompany YugoriyaV.Volkov, Director GeneralTel. +7 (34671) 57 222Fax +7 (34671) 57 224, 628012, -,., .5252, Sverdlov str. 628012, Khanty-Mansiysk, Russia

..Joint-stock Insurance CompanyRussian Insurance CenterD. Izvekov - President

Tel. +7 (095) 775 47 00Fax +7 (095) 232 58 74, 125315, , . 68/1, .2468/1 Build.24, Leningradsky pr., Moscow,Russia

/ Transportation / Customs clearance

..ExpoWestTrance Sole OfficialHandling and Forwarding AgentA.Levitsky, Director GeneralTel. +7 (095) 205 66 50Fax +7 (095) 253 96 84, 123100, , 1- , 1212, 1st Krasnogvardeisky passage,123100, Moscow, Russia

BTG Messe-Spedition GmbH BTG Messe-Spedition GmbHExclusive Coordinator for EntireInternational ParticipationMrs. Maria Lorenz, Managing DirectorTel. +49 (0821) 498 61 63Fax +49 (0821) 498 61 5486462 Langwied, Ausburg, Germany

-2005 --2005MAKS-2005 Official Catalogue Publisher

..INTERVESTNIK Publishing HouseOfficial Catalogue PublisherN.Laskov, Director GeneralTel. +7 (095) 926 52 11Fax +7 (095) 151 61 50, 125057, , / 77P.o.Box 77, 125057, Moscow, Russia

-2005"MAKS-2005 Review" Official MagazinePublisher

... .. A.B.E. Media LtdE. Semenov, Director GeneralTel. +7 (095) 926 53 56Fax +7 (095) 933 02 97, 119048, , / 127P.o.Box 127, 119048, Moscow, Russia

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Advertising on the exhibitors arena

- .. HELVETIKA Ltd.S. Savelyev, Director General Tel. +7 (095) 632 25 72Fax +7 (095) 632 25 73, 103309, , ., 34/4, .134/4 bld.1 Electrozavodskaya Str.,103009, Moscow, Russia

Advertising on the aerostats

..Zhukovsky Aerostatic ClubV. Boksha, Director GeneralTel. +7 (095) 556 79 45, 140185, ,., / 655P.o. Box 655, Zhukovsky, Moscow region,140185 Russia

.Outdoor advertising in Zhukovsky

.. Dekart LtdE. Pavlov, Director GeneralTel. +7 (09648) 7 75 30, 140180, ,., ., .11a Shkolnyj pr., Zhukovsky, Moscowregion, 140180 Russia

Screen advertising at the exhibition area

"", .. Wings LlcS. Vikulin, Director GeneralTel. +7 (095) 556 51 12, 556-51-49Fax +7 (095) 556 54 34., 140182, ,., . .. Gromov Flight Research Institute,Zhukovsky, Moscow region, 140182Russia

-Organization of a press-centre

..

ETS PARTNERSA. Son, Director GeneralTel. +7 (095) 921 83 17, 921 87 63, , . , . 3/73/7, Pokrovka str, Moscow, Russia

Telephone communication organizer

TEL .. Telecommunication company TELA. Egorov, Director GeneralTel. +7 (095) 787 42 00Fax +7 (095) 787 42 01, 125167, , . 4-, .33, Vosmogo Marta 4-th str., 125167,Moscow, Russia

Tickets sales partner

..Mostransagentstvo JSCV.Gorin, Director GeneralTel. +7 (095) 730 40 30Fax + 7(095) 928 15 85, 101000, , ., . 24/7, .124/7, build. 1, Miasnitskaya str., 101000,Moscow, Russia

Transport service

..Mostransavto A. Zhizhaev, Director General Tel. +7 (095) 200 61 44Fax. +7 (095) 299 25 08, 127051, , 21, .821, build. 8, Tsvetnoy Bulvar str. ,Moscow 127051 Russia

Catering Service

.. Silver Cloud Llc D. Chilikin, Director General Tel. +7 (095) 778 19 42Fax. +7 (095) 254 38 56, 123056, , ., .1111 Saratovskaya str., Moscow 123056Russia

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/ SPECIAL PROGRAMS

Civil Aviation Business Centre

.. Expo Technologies Centre (ETC) LlcD. Lobastov, Director GeneralTel: +7 (095) 502-66-72Fax: +7 (095) 748-10-60105082, . , . ., .32, .1232, build.12, B.Pochtovaya str., Moscow 105082 Russia

2- - UNIMAKS2nd International Exhibition of aviation and engineering work of youth ..UNIMAKSP. Golandsky, Executive DirectorTel:+7 (095) 556-81-11Fax: +7 (095) 556-10-94140180, , . , , .11a Shkolnyj pr., Zhukovsky, Moscow region, 140180 Russia

: Seminar Organizer

() ..Russian High Technologies Development FundP.Provintsev, DirectorTel./Fax +7 (095) 200 26 31, 103051, , . , .24/124/1, Petrovka Str., 103051, Moscow, Russia

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www.rg.ru

www.idr.ru

www.ato.ru

www.radiomayak.ru

-

www.airfleet.ru

Air Fleetwww.airfleet.ru

www.airfleet.ru

www.milparade.ru

www.avtoradio.ru

-www.militarynews.ru

www.trud.ru

www.pwgs.org

- www.almaz-media.ru

www.take-off.ru

Monchwww.monch.com

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INFORMATION SPONSORS

31

www.aviamodel.ru

www.bossmag.ru

JET www.jetmedia.ru

www.mediaguide.ru

, www.mediaguide.ru

tm-magazin.ru

tm-magazin.ru

www.vertolet-media.ru

- www.almaz-media.ru

www.aviapanorama.ru

www.aviavestnik.ru

www.aviation-time.kiev.ua

[email protected]

www.aviationunion.ru

www.pressmk.ru

tm-magazin.ru

[email protected]

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1. 95

2. 160

3. 22

4. - 204 - 300

5. - 334

6. - 114

7. -76 90

8. 96 - 300

9. 76

10. 171 -

11. - 8 -

12. - 8 -

13. -

14. 21 - 93

15. - 29

16. - 292

17. - 29

18. - 29

19. 31

20. - 890

21. - 103

22. 3( )

23. 2 ( 2)( )

24. - 32

25. - 52

26. - 60

27. - 50

28. - 28

29. - 226

30. - 31

31. - 12

32. - 17

33. - 01

34. - - 02

35. - 05

36. - 140 -

37. 201

38. EUROPA XS 411

39. - 40

40. 50

41.

42. Robinsin R44

43. Bell - 407

44. 8

45. - 26

46. 114 ( )

47. (

48. RV 7A RV Group (OOO RVAirplanes)

49. Velocity SE RG

50. - 38 ..

51. - 54 . ..

52. 28 ..

53. u 12 () -

54. Au 11 ( ) -

55. Au 29 ( ) -

56. BB20GP ( ) -

57. EVROSTAR EV-97 ()

58. 55 ( ) . ..

59. L 39 ( - ... )

60. 26 ( -- )

61. 29 ( -- )

62. 30 2 ( )

63. 47 ( )

64. 27 ( )

65. 30 ( )

66. 80 ( )

67. 39 (

68. 32 ( - )

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LIST OF RUSSIA AND CIS` AIRCRAFT

69. 33 ( )

70. 31 ( - )

71. 2 () -

72. 52 (- ) ...

73. 130 (- ) . ..

74. 130 (, - ) . ..

75. -

76. -

77.

78.

79. 18 . ..

80. - 4 . ..

81. 39 . ..

82. Cessna 172S Skyhawk SP . ..

83. 154 . ..

84. 24 . ..

85. 27 . ..

86. 30 . ..

87. L 29 (- )

88. 2000

(- )

89. 103 ( ) . ..

90. 223 ( )

()

91. 103 ( ) . ..

92.

93.

94. 8

95. 28

96. - 24

97. - 31

98. 27

99. 27

100. 24 - 2

101. 25

102. 26

103. 2

104. 35

105. F 32

106. 92 -

107. -124-100 -

108. .

109. .

110. .

111. .

112. .

113. .

114. .

115. .

116. Discus .

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117. -2 .

118. -06- .

119. .

120. .

121. .

122. -06 .

123. 148-100 . ..

124. 451

125. 471

126. 410

( - ())

127. - 54 . ..

128. - 55 . ..

129. 140 100 ( )

130. 21

131. ( )

132. ( )

133. 100 ( )

134. 2 ( )

135. 10

136. Piper Malibu Meridian The New Piper Aircraft / Air Alpha Aircraft Sales

137. Pulatus PC- 12 Pilatus Aircraft / Air Alpha Aircraft Sales

138. Pilatus PC- 6/B2- H4 Pilatus Aircraft / Air Alpha Aircraft Sales

139. Grand Caravan C208B Loyds Investment Corp. (USA)

140. Skylane C182T Loyds Investment (USA) Corp.

141. Global 5000 Bombardier

142. Learjet 60 Bombardier

143. Challenger 800 Bombardier

144. CL604 Bombardier

145. DA40 TDI Diamond Star Diamond Aircraft Industries

146. DA42 Twinstar Diamond Aircraft Industries

147. DA42 MPP Twinstar Diamond Aircraft Industries

148. FALCON 2000 EX F Dassault Aviation

149. FALCON 900 EX F Dassault Aviation

150. AlphaJet French Air Force / Patrouille de France

151. MIRAGE 2000 French Air Force

152. Hawker 800XP Beechcraft Hawker Raytheon Aircraft

153. Hawker 400XP Beechcraft Hawker Raytheon Aircraft

154. Premier I Beechcraft Hawker Raytheon Aircraft

155. Beechcraft 1900D Beechcraft Hawker Raytheon Aircraft

156. Beechcraft King Air 350 Beechcraft Hawker Raytheon Aircraft

157. Bell 407

158. Robinson R44

159. Robinson R44

160. G-222 Italian Air Force / Flight Test Center

161. Aermacci MB339A Italian Air Force / Frecce Tricolori

162. Legacy EMBRAER

163. F/A-18 US Navy

164. F-16C US Air Force

165. F-15E US Air Force

166. B-1B US Air Force

167. KC-10 US Air Force

168. KC-135 US Air Force

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-3 / An-3

-32 / An-32 , . . . . . . . . . . . . . . . . . . . . . . . . . . 23.68Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29.2Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 74.98Wing area, sq.m , . . . . . . . . . . . . . . . . . . . 17300Empty weight, kg , . . . . . . . . . . . . . . 27000Max take-off weight, kg , . . . . . . . . . . . . . . . . . . 6700Commercial load, kg , / . . . . . . . 530Max cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . 9400Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 2500Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 13.65Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 18.19Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 71.52Wing area, sq.m , . . . . . . . . . . . . . .5800Max take-off weight, kg , . . . . . . . . . . . . . . . . . . .1800Commercial load, kg , / . . . . . . . . . . . . . . . . . . . .220Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . . . .815Range, km

6700 - -20 -20 5180 .. - -32 9 1976 . - 1982 . 350 , -, , , , , . -32 : -32 ( , - 7200 ), -32(, 8 ), -32-200 (--, 7500 , ). -32 31 1995 ., -32 10 1995 .

A turboprop transport featuring the 6,700-kg lifting capacity andintended for countries with hot and/or mountainous climate. Theaircraft is powered by two AI-20M or AI-20DM 5,180 hp engines.The An-32 prototype maiden flight took place on 9 July, 1976.Since 1982, the aircraft has been in series production at theKiev-based Aviant plant. There have been built more than 350aircraft that were exported to India, Afghanistan, Nicaragua,Peru, Ethiopia, Bangladesh and Sri Lanka. The An-32 served asa baseline model for deriving the An-32B civilian transport with-out airborne operations equipment, featuring a 7,200-kg liftingcapability, An-32P fire-fighter capable of carrying 8 tonnes ofwater, as well as An-32V-200 military airlifter with lifting capaci-ty of 7,500 kg and western-made avionics.

- , - -2 -20 1430 .. -. -3 13 1980 ., 1991 . - . -2 -3 - . 4 - 2000. : -3 (-, 2200 ) -3 (- -, 12 1800 ). -3 -23 -36 25 2000 . 2003 . - 12 -3 -3.

The An-3 is s multipurpose turboprop aircraft intended for usein agriculture and by local airlines an upgraded version of theAn-2 piston-engine biplane powered by a single TVD-201,430-hp turboprop engine and fitted by more up-to-date equip-ment. The An-3 prototypes maiden flight took place on 13 May,1980; in 1991, the aircraft successfully passed the official test-ing programme. The earlier-built An-2s are being upgraded tomeet the An-3 standard at the Omsk-based Polyot aerospaceassociation. The first four upgrades were shipped to the cus-tomers in the year 2000. The An-3 2001 production plan pro-vides for 30 aircraft. There are two versions offered for sale the An-3 agriculture version equipped with 2,200-litre chemicalstank and the An-3T convertible plane capable of carrying 12passengers in the passenger role or 1,800-kg cargo in thetransport version. The An-3T obtained its AP-23 and AP-36 cer-tificates on 25 April 2000.

. .. / ANTONOV ASTC

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-38 / An-38

- 26-27 2500 . TPE331-14GR-801E 1500 .. (-38-100) 24 1994 . . ... 24 1997 . -25. 2001 . 5 , . -38-100 -38-200 -20-03 -36-02. 2001 . -38 : , ,- 3200 .

The An-38 multipurpose transport/passenger aircraft intended forlocal airlines and powered by two turboprops. The aircraft isdesigned to carry 26-27 passengers or 2,500-kg cargo. The maid-en flight of the aircraft, powered by 1,500-hp Garret TPE331-14GR-801E engines (An-38-100), was made on 24 June 1994.The series production of the An-38 began at the Novosibirsk-based Chkalov aircraft production association (NAPO). On 24April 1997, the aircraft was issued its AP-25-compliant airworthi-ness certificate. By 2001, customers had taken delivery of fiveproduction aircraft, with another one being in operation with theNAPO. A Russian engine-powered variant An-38-200 wasderived from the An-38-100. It is powered by two TVD-20-03engines with AV-36-02 propellers. Its trials are slated to kick off in2001. In addition to the passenger and transport versions, the fol-lowing An-38 variants could be built - the administrative, mede-vac, patrol/troop carrier ones as well as a transport featuring the3,200-kg lifting capacity for container cargo traffic.

, . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.54Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22.06Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39.8Wing area, sq.m , . . . . . . . . . . . . . . . . . . . . . . . . 5530Empty weight, kg , . . . . . . . . . . . . . . . . . . . . 8800Normal take-off weight, kg , . . . . . . . . . . . . . . . . . . . . . . 2500Commercial load, kg , / . . . . . . . . . . 380Max cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . . . . 4200Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1900Range, km

-70 / An-70 , . . . . . . . . . . . . . . . . . . . . . . . . . 40.73Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 44.06Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 204Wing area, sq.m , . . . . . . . . . . . . . . . 112000Normal take-off weight, kg , . . . . . . . . . . . . . 130000Max take-off weight, kg , . . . . . . . . . . . . . . . . . 35000Commercial load, kg , / . . . . . . 750Max cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . 12000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . 4800Range, km

35 -27. -70 16 1994. ( 10 1995 .). 24 1997 . . - -70 -

The An-70 is a transport aircraft powered by four D-27 propfans and fea-turing a lifting capacity of 35 tonnes. The An-70 prototypes maiden flighttook place on 16 December 1994, with the aircraft crashing on 10 February1995. On 24 April, 1997, the flight testing of the second prototype com-menced. In 2002, it is to be joined by another prototype nearing completionat Antonov ANTK, which, in turn, will be followed by first production planes.

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. . - -70 - -70. : -70 ( -- 20-35 -27; : -, ,-, .); -70-100 ( -70 - ); -70 (- 20-35 4 -27); -70-100 ( -70 - 10-30 -27); -70 (- 150 30 ; : -, .); -70-200( -70-100 -93); -70-300 (- -70-100 CFM56-5C4); -70-400( -70 CFM56-5C4)

The military transport version of the An-70 became the base for deriving theAn-70T civilian transport. The aircraft is slated for series production at theAviant (Kiev) and Aviakor (Samara) plants. The An-7X export version pro-gramme has been devised for the company to took part in the joint airliftertender for Western Europe and other prospective buyers.The versions offered are the An-70 four-D-27-powered military transportbasic version featuring short take-off and landing and lifting capacity of20-35 tonnes, a tanker plane, an airborne early warning and control(AEW&C) aircraft, SAR or naval patrol aircraft; An-70-100 a versionfeaturing an upgraded avionics and smaller crew; An-70T four-D-27-powered civilian transport with a lifting capacity of 20-35 tonnes,An-70T-100 a version of the An-70T with a lifting capacity of 10-30tonnes powered by two D-27 engines; An-70TK a convertible civiliancargo/passenger aircraft capable of seating 150 passengers or carrying30-tonne cargo, also it could be built in the following versions forest fire-fighter, ecological environment monitoring aircraft, etc.; An-70T-200 aversion of the An-70T-100 powered by two NK-93 engines; An-70T-300 a version of the An-70T-100 fitted with two CFM56-5C4 engines; An-70T-400 a version of the An-70T powered by four CFM56-5C4 engines.

-72 -74 / An-72 and An-74 , . . . . . . . . . . . . . . . . . . . . . . . 28.07Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . 31.89Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . 98.53Wing area, sq.m , . . . . . . . . . . . . . . . 20200Empty weight, kg , . . . . . . . . . . 36500Max take-off weight, kg , . . . . . . . . . . . . . . 10000Commercial load, kg , / . . . . . . . . . . . . . . . 705Max speed, km/h , / . . . . . . . . . . . . . . . . . 600Cruising speed, km/h , . . . . . . . . . . . . . . . . . 11800Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . 1350Range, km

- 7,5-10 -36 6500 . -72 31 1977 . 1985 . -. 150 . -74 - -72 ( 1983 .), . -74 1989 . , 1993 . (. ). -74 2 1991. -74-100 7 1997 . : -72 ( - 10 -36); -72 ( -); -72 ( ); -71( ); -74 ( - ); -74 ( ); -74-100( -74 4 ); -74-200 (-74 , - 2 ); -74 (- 52 . 10 ); -74-100 ( -74 4 ); -74-200 ( -74 -, 2 ); -74-200( VIP-). : -74-68 (, 68 ), -174 ( , 20 ) .

It is a STOL transport powered by two D-36 6,500-kgf turbofanengines and featuring a lifting capacity of 7.5-10 tonnes. Theprototypes maiden flight was made on 31 August, 1977. Underseries production since 1985 at the Kharkov-based StateAircraft Production Plant (KhGAPP). Over 150 aircraft havebeen built. The An-74 designation was initially assigned to thepolar version of the An-72 (built in 1983). Later, all civilian ver-sions of that aircraft family were given that designation. Theseries production of the An-74 commenced at the KhGAPP in1989 with the Polyot plant (Omsk) beginning its series produc-tion in 1993. The primary versions are the An-72 basic version of militarytransport with 10-tonne lifting capacity powered by two D-36engines; An-72V export version with smaller crew; An-72P bor-der troops patrol aircraft; An-71 experimental AEW&C aircraft;An-74 polar transport; An-74T transport basic version fitted withcargo handling equipment; An-74T-100 a version of the An-74T with four crew; An-74T-200 an An-74T version featuringupgraded avionics, engines and crew of two; An-74TK convert-ible transport/passenger aircraft intended to carry 52 passen-gers or 10-tonne cargo; An-74TK-100 an An-74TK versionmanned by the crew of four; An-74TK-200 an An-74TK ver-sion with upgraded avionics, engines and crew of two; An-74-200D a VIP aircraft. Under development are the following ver-sions the An-74-68 passenger plane for 68 seats, the An-174stretched-body aircraft with lifiting capacity of 20 t, etc.

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-124 / n-124 Ruslan

-74TK-300 / An-74TK-300

, . . . . . . . . . . . . . . . . . . . . . . . . . 69.1Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 73.3Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 628Wing area, sq.m , . . . . . . . . . . . . . . . . . . 175000Empty weight, kg , . . . . . . . . . . . . . 405000Max take-off weight, kg , . . . . . . . . . . . . . . . . . 150000Commercial load, kg , / . . . . . . . . . . . 850Max speed, km/h , / . . . . . . . . . . . . . . . . . . 800Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . 9500Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . 4500Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . . 28.07Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31.89Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 98.62Wing area, sq.m , . . . . . . . . . . . . . . . 34500Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . 10000Commercial load, kg , / . . . . . . . . 725Max cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 11100Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . 2200Range, km

- - 52 10 -36 .4 6500 , - -72/-74. - ( ), - , -, - -, , - . - 20 2001 . -4361 7500 . .

The An-74TK-300 is a convertible cargo/passenger jet aircraft tohaul either 52 passengers or 10 t of cargo. A further An-72/An-74 derivative, it is powered by two D-36 Series 4A engines pro-ducing 6,500-kg thrust. It differs from the baseline aircraft in itsunderwing engine arrangement, a modified wing, uprated aircraftsystems, an up-to-date flight navigation suite compliant withinternational standards, as well as enhanced comfort of the cock-pit and passenger cabin. The aircraft completed its maiden flighton 20 April, 2001. In the future, the plane is going to be outfittedwith 7,500-kgf D-436T1 engines. It is being productionised bythe Kharkov-based KhGAPP aircraft plant.

- 150 -18 23400. 26 1982 . (. ) 1985 ., , - . ... : -124 ( - , - - 1987 .); -124-100 ( ). 30 1992 . -, - .

A heavy transport jet featuring a lifting capacity of 150 tonnespowered by four D-18T 23,400-kgf engines. The maiden flightwas made on 26 December, 1982. Since 1985, the aircraft hasbeen under series production at the Aviastar plant (Ulyanovsk),first planes were built in Kiev, wings are manufactured at theTashkent Aircraft Production Corporation (TAPC). 55 aircraftwere built. The primary versions are the An-124 (the baselineheavy airlifter operated by the Russian Air Force since 1987)and the An-124-100 (a civilian transport).

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-140 / An-140

-225 / An-225 Mriya

, . . . . . . . . . . . . . . . . . . . . . . . . . . 22.46Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24.25Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 51.0Wing area, sq.m , . . . . . . . . . . . . . . . . . . . 10600Empty weight, kg , . . . . . . . . . . . . . . . . 16700Normal take-off weight, kg , . . . . . . . . . . . . . . 19150Max take-off weight, kg , . . . . . . . . . . . . . . . . . . 4900Commercial load, kg , / . . . . . . . 575Max cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . 7200Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 2100Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . 84.0Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 88.4Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 905Wing area, sq.m , . . . . . . . . . . . . . 600000Max take-off weight, kg , . . . . . . . . . . . . . . . . . 250000Commercial load, kg , / . .. .850Max cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . . 5300Range, km

- -18 23 400 250 . 21 1988 . .13 1989 . -225 - "". 2000-2001 . . - 7 2001 . - - -225-100. - 23 2001 . - .

A dedicated super-heavylifter powered by six D-18T 23,400-kgfengines to carry bulky cargoes, weighing up to 250 tonnes, bothinside the cargo cabin and externally on its fuselage. Its maidenflight was made on 21 December, 1988. One aircraft has beenbuilt. On 13 May, 1989, the first flight was made by the An-225with the Buran space shuttle mounted on top of the aircraft. In 2000-2001, the first An-225 was upgraded with advancednavigation and communications aids. Following the seven-yearmothballing and the following upgrade, the aircraft was flight-tested on 7 May, 2001. The improved Mriya is poised to obtainits type certificate soon as well as a new designation An-225-100. The aircraft is slated to launch commercial operations asearly as 2001.

3-117-1 (22500 ..) 46-52 . 2100-2650 . - 17 1997 . - - () 1999 . -140 2000. 2000 . - . 1995 . - -140 ( -140) . -140 7 2001 . : -140 ( 6 ); -140 (- ); -140-100 ( 68 ); -142 (- ).

An aircraft for local airlines powered by two TV3-117VMA-SBM12,500-hp engines. The maiden flight of the prototype took placeon 17 September 1997. The first production aircraft was rolledout by the KhGAPP (Kharkov State Aircraft ProductionCompany) in 1999. The airworthiness certificate was received inApril 2000. Production aircraft deliveries to Ukrainian operatorsbegan in 2000. Also, its production is being prepared at theAviakor plant (Samara). 1995 witnessed a contract concludedfor launching An-140 (designated as IrAn-140) production at anaircraft production plant in the Iranian city of Isfaghan. The firstIranian IrAn-140 took off on 7 February, 2001. The versions in development are the An-140T transport featur-ing a lifting capacity of 6 tonnes; An-140TK convertible pas-senger/transport aircraft; An-140-100 stretched 68-seat airlinerfeaturing more powerful engines; An-142 military transport.

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-12-200 / Be-12P-200

-40 / -40 Albatross

. . . / BERIEV COMPANY

, . . . . . . . . . . . . . . . . . . . . . . . . . . 30,11Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29,842Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 99,0Wing area, sq.m , . . . . . . . . . . . . . . . . . . . 24500Empty weight, kg , . . . . . . . . . . . . . . 36000Max take-off weight, kg , / . . . . . . . . . . . . 580Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 470Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . 8000Service ceiling, m ( ), . . . . . . . 1500Range with max payload, km , . . . . . . . . . . . . 3600Max range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 43.84Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41.6Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 200.0Wing area, sq.m , . . . . . . . . . . . . . . 86000Max take-off weight, kg , / . . . . . . . . . . . . 820Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 760Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . 9700Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 5500Range, km

- - -20 5180 .., - -12, 18 1960 . - 1963-1973 . 140 -12, - ( ) . -12 - , - , -12( , 1992 .) -12 (-, 1992 .). - - -12-200 - , - - -200. -12-200 1996 .

The Be-12P-200 is a fire-fighting amphibian powered by two AI-20D turboprops 5,180 horsepower each a civilian version ofthe Be-12 ASW aircraft whose maiden flight took place on 18October, 1960. All in all, from 1963 to 1973 the Taganrog-basedaircraft production plant manufactured a total of 140 Be-12 ASWamphibians that had been operated for a long time by the Soviet(and later Russian and Ukrainian) Navys Aviation as well asnaval aviation of some other countries. Following the beginningof en masse Be-12 decommissioning, a programme waslaunched to convert the aircraft with a sizeable remaining serv-ice life into commercial versions for civilian operators. The vari-ants derived were the Be-12NKh transport and multipurposeamphibians (1992) and Be-12P fire-fighting aircraft (1992). Thelatter was used for deriving the Be-12P-200 fire-fighting aircraftfitted with a set of relevant equipment designed to be mountedon the new amphibian Be-200. The maiden flight of the Be-12P-200 took place in August 1996.

- -30 12000 , . 8 1986 . . -40 - -42 -27. -40 -42 - -40 (-40) -27 . -40.

The A-40 Albatross is a antisubmarine warfare (ASW) amphibianjet powered by two D-30KPV 12,000-kgf engines the world-largest aircraft of this type. Its maiden flight was performed on 8December, 1986. Two prototypes were built. The Be-42 SARamphibian powered by two D-27A propfans was derived from theA-40. The A-40P (A-40PE) patrol amphibian, powered by D-27Aengines and featuring advanced ASW system and avionics, isbeing derived from the A-40 and Be-42 for the Russian naval avi-ation and for export sales. The third A-40 prototype could becompleted as such a variant.

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-50 / -50

-103 / Be-103

, . . . . . . . . . . . . . . . . . . . . . . . . . 46.6Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 50.5Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 300.0Wing area, sq.m , . . . . . . . . . . . . . . . . . . 119000Empty weight, kg , . . . . . . . . . . . . . . .190000Max take-off weight, kg , / . . . . . . . . . . . 785Max speed, km/h , . . . . . . . . . . . . . . . . . . . . 10500Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . 5100Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.65Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.72Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 25.1Wing area, sq.m , . . . . . . . . . . . . . . . . . . . . 1540Empty weight, kg , . . . . . . . . . . . . . . . . . 1800Normal take-off weight, kg , . . . . . . . . . . . . . . . 2050Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . 385Commercial load, kg , / . . . . . . . . . . . . 285Max speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 3000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . 1280Range, km

"" -30 12000 . . .. -76. 19 1978. . .. 20 , . 1999 . -50 - -50, . 28 1999 ., -. -50.

An airborne early warning and control (AEW&C) aircraftequipped with the Shmel radar system and four D-30KP 12,000-kgf engines. It was derived by Beriev from the Il-76MD transport.Its maiden flight was made on 19 December, 1978. TheTashkent Aircraft Production Corporation (TAPC) producedabout 20 such aircraft which are in service with the Russian AirForce. The upgraded versions are being developed as well asones intended for foreign customers.

- - Teledyne Continental IO-360ES - 210 .. 4-5 400 - . , , - . 15 1997 . -103 26 2001 . - -- 1999 . . -103 2002 . -20 -14.

A light multipurpose amphibian powered by two TeledyneContinental IO-360ES 210-hp piston engines and capable ofcarrying 4-5 passengers or 400-kg cargo to the areas inacces-sible for other transportation means and featuring a lot of riversand lakes. The aircraft could be operated in medevac, agricul-tural, patrol and other versions. The maiden flight was made on15 July 1997. The two early prototypes were crashed. The thirdhas been test-flown since 1999. Production was launched in1999 by the Komsomolsk-on-Amur Aircraft ProductionAssociation (KnAAPO).

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-200 / Be-200

. . . / ILYUSHIN JSC

, . . . . . . . . . . . . . . . . . . . . 31.43Length, m , . . . . . . . . . . . . . . . . . . . . . . 32.78Wing span, m , 2 . . . . . . . . . . . . . . . . . . 117.44Wing area, sq.m , . . . . . . . . . . . . 25340Empty weight, kg , . . . . . . . . . 37200Normal take-off weight, kg , . . . . . . 43000Max take-off weight, kg , . . . . . . . . . . . . 8000Commercial load, kg , / . . . . . 750Max speed, km/h , . . . . . . . . . . . . . . 11000Service ceiling, m , . . . . . . . . . . . . . . . . . . 2800Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 40.75Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37.42Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 140Wing area, sq.m , . . . . . . . . . . . . . . . . . . . 34 000Empty weight, kg , . . . . . . . . . . . . . . 66 000Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . . 5400 Combat load, kg , / . . . . . . . . . . . . . . . . . . 685Max speed, km/h , . . . . . . . . . . . . . . . . . . . . . 10 000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . 8500Range, km

- - -436 7500 . - , - 24 1998 . . : -200 (-); -200 ( 50 , 60 , 30 );-200 ( - ); -210 ( 72 ) . ( -200) -200 ( 27 2002 .). -200 10 2001 . -200 2003 .

A multipurpose amphibian jet powered by two D-436TP7,500-kgf engines. The first version was built by the IAIA as a fire-fighter aircraft whose flying-out was made on 24 September,1998. Series production commenced by the Irkutsk AircraftIndustrial Association (IAIA). The versions offered are the Be-200firefighter; Be-200ChS a multipurpose aircraft intended for theRussian Ministry for Emergencies and capable of carrying 50rescuers seats or 60 casualties on the folding, or 30 casualtieson the stretchers; Be-200P patrol aircraft to defend the Russianshoreline and monitor the economic zones; Be-210 72-seat pas-senger aircraft; etc. The second flying prototype (in the Be-200ChS version) is expected to began its flight trials in 2001. Bylate 2001, the Be-200 firefighter is to have obtained its limitedcategory type certificate. The Russian Ministry for Emergenciesin 2002-2003 is to take delivery of the initial seven-craft Be-200ChS batch.

-38 / IL-38

-- - -20 4250 .. - -18, 27 1961 . - ( . .. ) 1965-1972 . 60 , 5 . 1968 . - , - . 2001 . - -38 . 2002 . . .. - -38SD.

The Il-38 is a medium-range antisubmarine warfare aircraft fittedwith the Berkut ASW system and powered by four AI-20M4,250-hp turboprop engines. The aircraft was derived from theIl-18D airliner, with its maiden flight made on 27 September,1961. It was in production between 1965 and 1972 at theMoscow-based Znamya Truda Machine-building Plant (nowa-days MiG Aircraft Corporations Voronin Production Centre).A total of about 60 aircraft were built, of which several oneswere exported to India for the Indian Navy. Since 1968, the Il-38has been in service with the Soviet (now Russian) Navy. 2001saw the manufacture of the first upgraded Il-38M patrol aircraftboasting a novel avionics suite.

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-76 / IL-76

-78 / IL-78

, . . . . . . . . . . . . . . . . . . . . . . . . . 53.19Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 50.5Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 300.0Wing area, sq.m , . . . . . . . . . . . . . . . . . . 101000Empty weight, kg , . . . . . . . . . . . . . . . 200000Normal take-off weight, kg , . . . . . . . . . . . . . 210000Max take-off weight, kg , . . . . . . . . . . . . . . . . . 52000Commercial load, kg , / . . . . . . . . . . . 850Max speed, km/h , . . . . . . . . . . . . . . . . . . . . 12000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . 5200Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . 53.19Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 50.5Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 300.0Wing area, sq.m , . . . . . . . . . . . . . 190000Max take-off weight, kg , / . . . . . . . . . . . 850Max speed, km/h , / . . . . . . . . . . . . . . . . . . 750Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . 12000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . 5200Range, km

- 40-47 -30 12000 . -76 25 1971 . 1973 . - . ... 850 -, 120 . : -76 -76 (-); -76 -76 ( ); -76 (-- ); -76 (-); -76 ( 60 , -90-76 14000 - , 1 1995 .) . -76 -76 - -76 -90-76 .

The Il-76 is a medium transport jet featuring a lifting capacity of40-47 tonnes and powered by four D-30KP 12,000-kgf engines.The prototypes maiden flight was made on 25 March, 1971.Since 1973, it has been in series production at the TashkentAircraft Production Corporation (TAPC). Over 850 aircraft havebeen built, of which 120 were exported. The primary versionsare the Il-76M and Il-76MD military transports; Il-76T and Il-76TD civilian transports; Il-76MDPS SAR aircraft equipped withan airdroppable rescue boat; Il-76P firefighter; Il-76MF trans-port fitted with four PS-90A-76 14,000-kgf engines, stretchedfuselage and featuring a lifting capacity of 52 tonnes, its maid-en flight was made on 1 August, 1995; etc.

- - -76 -30 12000 . 26 1983 . 1984 . . ... 45 -, -78 . -38 . - 2003 . - -78 .

A tanker plane derived from the Il-76MD military transport andpowered by four D-30KP 12,000-kgf engines. The maiden flightwas made on 26 June, 1983. It has been in series production atthe TAPC since 1984. The total of 45 aircraft has been manu-factured, including upgraded Il-78Ms featuring an increasedtake-off weight and non-opening ramp

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-86 / IL-86

-96 / IL-96

, . . . . . . . . . . . . . . . . . . . . . . . . . 59.54Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 48.06Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 330Wing area, sq.m , . . . . . . . . . . . . . 215000Max take-off weight, kg , . . . . . . . . . . . . . . . . . 42000Commercial load, kg , / . . . . . . . . . . . 950Max speed, km/h , / . . . . . . . . . . . . . . . . . . 850Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . 11000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . 3700Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . 55.35Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 60.105Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . 391.6Wing area, sq.m , . . . . . . . . . . . . . . . . . . 119000Empty weight, kg , . . . . . . . . . . . . . 240000Max take-off weight, kg , . . . . . . . . . . . . . . . . . 40000Commercial load, kg , / . . . . . . . . . . . 900Max speed, km/h , / . . . . . . . . . . . . . . . . . . 850Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . 12000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . 10000Range, km

300 -90 16000 . - 28 1988 . 1990 ., 2004 . 14 , - , - , -96-300 . -96-300 29 1992 . - 2 -96-300 . -96 1997 . - 31 1998 ., 1999 . - -96, . 2003 . -96-400, -96 - -90.

A long-range 300-seat wide-body airliner powered by four PS-90A 16,000-kgf turbofan engines. The prototypes maiden flightwas made on 28 September, 1988. The aircraft has been in pro-duction at the Voronezh aircraft plant since 1990. Ten aircrafthave been made by 2001, of which six are in service withAeroflot, three are operated by Domodedovo Airlines, with yetanother one Il-96-300PU is built for the Russian president.The Il-96-300 was certified on 29 December, 1992. In the nearfuture, another six-ship batch is expected to be received byAeroflot, with another three Il-96-300s to possibly be bought byChina. The Il-96-300 baseline model is employed to derive thestretched Il-96-3XX PS-90A-powered freighter with lifting capac-ity of 92 t.

-86 350. 22 1976 . - 1977-1997 . . - 103 . -86 24 1980 . - 2003 . 73. -86 , . 1987 . - -86. -86 : -- ( 1 ) ( 4 ).

A 350-seat wide-body airliner powered by four NK-86 turbofanengines. The maiden flight made on 22 December, 1976.It had been under series production at the Voronezh aircraftplant during 1977-1997. 103 aircraft were built.Three aircraft were exported to China, with several more air-liners leased to a number of other countries. Since 1987, theaircraft have been powered by NK-86A upgraded engines. Thefollowing versions have been derived from the Il-86 baselineaircraft a troop-carrying airlifter (one was built) and an air-borne command post (four were built). By 2001, Il-86 aircrafthad been in service with Russian, Armenian, Kazakh, Uzbek,Macedonian, Chinese, Pakistani and some other air compa-nies.

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-103 / IL-103

-114 / IL-114

, . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.0Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.56Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 14.71Wing area, sq.m , . . . . . . . . . . . . . . . . . . . . 765Empty weight, kg , . . . . . . . . . . . . . . . 1460Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . 395Commercial load, kg , / . . . . . . . . . . . . 340Max speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 3000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . 1070Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 26.88Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30.0Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 81.9Wing area, sq.m , . . . . . . . . . . . . . . . . . . . 15000Empty weight, kg , . . . . . . . . . . . . . . 22700Max take-off weight, kg , . . . . . . . . . . . . . . . . . . 6500Commercial load, kg , / . . . . . . . . . . . . . . . . . . . 500Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . 7600Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 1000Range, km

Teledyne Continental IO-360ES 210 .. - 4 400 , - , , , . - 17 1994 . 1995 . - (), . -23 15 1996 ., - FAR-23 9 1998 . 2001 . 20 - -103, 6 . -103 . 2000 . -103., 2003 . - -103 .

The Il-103 is a light multirole aircraft powered by the TeledyneContinental IO-360ES 210-hp piston engine. The aircraft isintended to carry four passengers or 400 kg of cargo, fly air sur-veillance missions, patrol motorways, oil pipelines and forestsand be used for training flight crews. The maiden flight of the Il-103 prototype took place on 17 May 1994. The aircraft was putin production in 1995 at the Lukhovitsy Machine-building Plant(LMZ) part of the MiG Russian Aircraft Corporation. The air-craft has been certified in compliance with the Russian standardAP-23 on 15 February 1996, with its US airworthiness FAR-23-compliant type certificate being issued on 9 December 1998. Asof 2001, about 20 Il-103 aircraft are flown, with six aircraft beingexported to Peru. In 2000, the Il-103SKh dedicated agriculturalversion was developed.

7-117 2500.. 64 . 29 1990 . 2 ( ), . 1992 . . ... 2001 . 10 -. 26 1997 . 27 - 1998 . ( - ). -114 . -114 7-117 : -114 (- 7000 , 14 1996 .); -114 ( - ); -114-100 ( -114 Pratt&Whitney Canada PW-127H - 2750 .., 26 1999 ., 27 1999 .); -114-100 (- -114-100) .

A passenger aircraft designed for local airlines and powered bytwo TV7-117S 2,500-hp engines to carry 64 passengers. Theprototypes maiden flight was made on 29 March 1990. Two fly-ing prototypes were built, with the second of them being lost intrials. Series production commenced in 1992 by the TashkentAircraft Production Corporation (TAPC). By 2001, about 10 air-craft has been manufactured. The aircraft gained its IAC certifi-cate on 26 April, 1997. The Il-114 commercial operation beganon 27 August, 1998 in Uzbekistan: the Uzbekistan Airways flagcarrier took delivery of the first two-ship batch. The following vari-ants were derived from the Il-114: the Il-114T transport featuringa lifting capacity of 7 tonnes with the fly-out performed on 14September, 1996; Il-114P border guard patrol aircraft fitted withthe Strizh system; Il-114-100 a version of the Il-114 powered bytwo Pratt&Whitney Canada PW-127H 2,750-hp turboprops withthe maiden flight made on 26 January, 1999 and its certificateobtained on 27 December, 1999; Il-114-100T a transport ver-sion of the Il-114-100; etc.

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-27 -28 / Ka-27 and Ka-28

-29 / -29

/ KAMOV COMPANY

, . . . . . . . . . . . . . . . . . . . . . . . . . . 11.3Length, m , . . . . . . . . . . . . . . . . . . . 15.9Main rotor diameter, m , . . . . . . . . . . . . . . . . 10700Normal take-off weight, kg , . . . . . . . . . . . . . . 11000Max take-off weight, kg , . . . . . . . . . . . . . . . . . . 3000Commercial load, kg , / . . . . . . . . . . . . 290Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 230Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 2200Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . 3500Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 700Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 11.3Length, m , . . . . . . . . . . . . . . . . . . . 15.9Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . 5520Empty weight, kg , . . . . . . . . . . . . . . . . 11100Normal take-off weight, kg , . . . . . . . . . . . . . . 12600Max take-off weight, kg , . . . . . . . . . . . . . . . . . . 4000Commercial load, kg , / . . . . . . . . . . . . 280Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 235Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 3000Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . 4300Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 460Range, km

- 3-117 2200 .. 8 1973 . - 1979 . . 2001. 270 -. . -27 : -27 (--, 16 , 8 1974 .); -28 ( - , 1982 ., , , ).

A shipborne antisubmarine warfare (ASW) coaxial-rotor helicop-ter equipped with the Osminog ASW system and twoTV3-117VK 2,200-hp turboshaft engines. The maiden flight wasmade on 8 August, 1973. The helicopter has been in series pro-duction since 1979 at the Kumertau-based helicopter plant. Asof 2001, about 270 machines were made. The aircraft is operat-ed by the Russian Navy. It served as the base for deriving theKa-27PS SAR helicopter to carry 16 rescuees (its maiden flightwas made on 8 August, 1974); Ka-28 ASW export version fea-turing an increased fuel endurance (the maiden flight was madein 1982, the helicopter was exported to India, Yugoslavia,Vietnam).

- -27 3-117 (3-117) 16 , - -. 28 1976 . - 1984 . - . 2001 . 59 .

A combat transport helicopter derived from the Ka-27 and pow-ered by two TV3-117VK (TV-117VMA) gas turbine engines. Itwas designed to carry 16 assault troops and armed with cannonand rockets. The maiden flight took place on 28 July, 1976.Under series production at the Kumertau Aircraft ProductionAssociation since 1984. Operated by the Russian Navy. As of2001, 59 helicopters were built.

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-31/ Ka-31

-32 / -32

, . . . . . . . . . . . . . . . . . . . . . . . . . . 11.25Length, m , . . . . . . . . . . . . . . . . . . . 15.9Main rotor diameter, m , . . . . . . . . . . . . . . 12500Max take-off weight, kg , / . . . . . . . . . . . . 250Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 220Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . 3500Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 600Range, km

-27 -29 3-117 2200 .. -801 . 1987 . 1998 . , .

The Ka-31 is an airborne early warning and control (AEW&C)helicopter derived from the Ka-27 and Ka-29 and powered bytwo TV3-117VMA 2,000-hp engines. The machine carries the E-801 AEW radioelectronic suite, with the 360-deg. underbelly-mounted surveillance antenna. The helicopter flew its maidenflight in October 1987. Its series production commenced at theKumertau Aircraft Production Association in 1998. The helicop-ter also is exported.


-27 3-117 3-117 2200 .. - 8 1980 . - 1986 . - : -32 (); -32 (-, 5 ); -32 ( - -); -32 ( 3-117, - 16 1993 .); -321( , 12 1994 .); -322 ( ); -327 (-327, -); -3211 ( -32 - , FAR-29 1997 .); -3212 ( -32, - JAR-29 1996 .) . 2003 . 68 -32, 40 -. -32 .

A multipurpose coaxial transport helicopter derived from the Ka-27PS and powered by two TV3-117VK or TV3-117VMA 2,200-hp gas turbine engines. The maiden flight was made on 8October, 1980. Series production started at the KumertauAircraft Production Association in 1986. The following versionswere developed: Ka-32S shipborne ice patrol helicopter; Ka-32Ttransport featuring a lifting capacity of 5 tonnes; Ka-32K flyingcrane ; Ka-32A upgraded transport fitted with two TV3-117VMAengines , its Russian airworthiness certificate was received on16 July 1993); Ka-32A1 rescue helicopter for rescuing peoplefrom highriser fires (its maiden flight was made on 12 January,1994); Ka-32A2 police patrol helicopter; Ka-32A7 (Ka-327)armed borderguard patrol helicopter; Ka-32A11 the Ka-32Aversion intended for export to Canada (certified in line with USairworthiness standard FAR-29 in 1997); Ka-32A12 a Ka-32Aversion certified under the JAR-29 standard in Switzerland inJune 1996; etc.

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-50 / -50

-52 / -52

, . . . . . . . . . . . . . . . . . . . . . . . . . . 14.2Length, m , . . . . . . . . . . . . . . . . . . . 14.5Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . 7700Empty weight, kg , . . . . . . . . . . . . . . . . 9800Normal take-off weight, kg , . . . . . . . . . . . . . . 10800Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . . 2000Combat load, kg , / . . . . . . . . . . . . 350Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 255Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 4000Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . 5500Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 520Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 13.53Length, m , . . . . . . . . . . . . . . . . . . . . 14.5Main rotor diameter, m , . . . . . . . . . . . . . . . . . 10400Normal take-off weight, kg , . . . . . . . . . . . . . . . 11900Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . . . 2000Combat load, kg , / . . . . . . . . . . . . 300Max speed, km/h , . . . . . . . . . . . . . . . . . . . . . . . 3600Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . 6000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . 520Range, km

- 3-117 2200 .. - . - 17 1982 . - . 1991 . 2001 . - 12 , . 28 1995 . - - -50 - - . -50 : -50 ( -, - -50, 4 1997 .); -50-2 (- ( ) , 1999. - ) .

A single-seat coaxial combat helicopter powered by twoTV3-117VMA 2,200-hp engines and armed with powerfulweapons suite incorporating an automatic cannon and missiles.The maiden flight was made on 17 June, 1982. It has beenseries-produced at the Progress plant (Arsenyev) since 1991.As of 2001, 12 helicopters are built, with several of them beingtransferred to the Russian Army Aviation. The machine wasfielded with the Russian Army on 28 August, 1995. The baselinemodel, the Ka-50 Black Shark attack helicopter, is fitted with theShkval-V surveillance and sighting system for daytime opera-tions. The baseline Ka-50 was used to derive the Ka-50Sh day-and-night single-seat attack helicopter fitted with the Shkval-Vand Samsheet-50 systems (the maiden flight was made on 4March, 1997); Ka-50-2 Erdogan tandem-seat combat helicopterfeaturing an Israeli avionics suite and designed in 1999 to com-pete in a Turkish armed forces-held tender for a new combathelicopter; etc

- 3-117 2200 .. - , - - - - . -52 25 1997 . -52 2001 . -52 .

This is a twin-seat multirole combat helicopter powered by a pairof TV3-117VMA 2,200-hp engines. The crew is seated side byside. The machine boasts the Samsheet-E optronics sightingsystem and the Arbalet multirole radar system. The Ka-52Alligator prototype completed its maiden flight on 25 June, 1997.In 2001, the Ka-52K two-seat multirole combat helicopter wasderived from the Ka-52. The derivative mounts a modified avion-ics suite to meet the requirements of a potential foreign cus-tomer.

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-60 / -60

-226 /-226

, . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.25Length, m , . . . . . . . . . . . . . . . . . . . . 13.5Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . . 3700Empty weight, kg , . . . . . . . . . . . . . . . 6500Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . 2750Commercial load, kg , / . . . . . . . . . . . . . 300Max speed, km/h , / . . . . . . . . . . . . . . . . . . . . 270Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . . 2100Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . . 5150Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . 700Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 8.1Length, m , . . . . . . . . . . . . . . . . . . . . 13.0Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . 1950Empty weight, kg , . . . . . . . . . . . . . . . . . 3100Normal take-off weight, kg , . . . . . . . . . . . . . . . 3400Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . 1300Commercial load, kg , / . . . . . . . . . . . . 205Max speed, km/h , / . . . . . . . . . . . . . . . . . . . . 195Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . . 2160Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . . 5700Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . 600Range, km

- -600 1300 .. 14 2 . 10 1998 . . -60 : -62( - 14-16 , 2000 2750 , :, -, ( -) .); -64 ( -62 General Electric CT7-2DL (T700), LHTEC CT8-800, Rolls-Royce/Turbomecha RTM-322, , ).

An Army multipurpose troop-carrying single-rotor fenestron-equipped transport powered by two RD-600V 1,300-hp enginesand designed to carry 14 assault troops or 2-tonne cargo. Themaiden flight was made on 10 December, 1998. The helicopterhas been productionised at the Lukhovitsy machine-buildingplant (part of the MiG Russian Aircraft Corporation). The following helicopters were derived from the Ka-60: the Ka-62 utility transport/passenger helicopter to carry 14-16 passen-gers, 2,000-kg cargo in the cabin or 2,750-kg cargo slung underthe fuselage (medevac, SAR, business and VIP versions arepossible); Ka-64 an export version of the Ka-62 powered bytwo General Electric CT7-2DL (T700), or LHTEC CT8-800, orRolls-Royce/Turbomecha RTM-322 engines and fitted with newpassenger cabin, regular tail rotor and western-made avionics.

Allison 250-C20B - 420 .., -26. 3 1997 . . 2000 . -226 , . 2003 . -226 - , 22 .

A 8-seat multipurpose coaxial helicopter powered by two Allison250-C20V 420-hp gas turbine engines a top-to-bottom upgradeof the Ka-26 helicopter. The Ka-226s prototype maiden flightwas made on 3 September, 1997. The helicopter has been pro-ductionised at the Strela plant (Orenburg) in cooperation withKumertau Aircraft Production Association. The first series-pro-duced helicopter was built in late 2000. In 2001, the RussianMinistry for Emergencies is to receive the first two of 5 orderedKa-226 helicopters (in Ka-226A version). An order from Moscowcity administration and Gazprom JSC are also expected. Ka-226is to be certified in 2002.

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/ Ansat

/KAZAN HELICOPTERS

, . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.54Length, m , . . . . . . . . . . . . . . . . . . . . 11.5Main rotor diameter, m , . . . . . . . . . . . . . . . . . 3000Normal take-off weight, kg , . . . . . . . . . . . . . . . 3300Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . . 1300Commercial load, kg , / . . . . . . . . . . . . . 285Max speed, km/h , / . . . . . . . . . . . . . . . . . . . . . 250Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . . . 3000Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . . 6000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . 595Range, km

- 1300 Pratt&Whitney Canada PK-206C 640 .. - 1996 . , , 1999 . 17 1999 ., 6 1999 . 2001 . - PW-207. - - -29 FAR-29. - , .. -- . - -, 9 1000 (1300 ) VIP- 4-5 , -, , , --, -, . - , , - .

The Ansat is a lightweight multirole cargo/passenger helicopterwith the 1,300-kg lifting capacity. The machine is powered by apair of Pratt&Whitney Canada PK-206C 640-horsepower turbineengines. The first static prototype was built in 1996. The secondprototype was built for flight trials in 1999. The first hovering wasmade on 17 August, 1999, with the maiden circuit flight on 6October, 1999. The helicopters design meets the AP-23 (FAR-23) airworthiness standard. Currently, the machines testing isunder way, with the third prototype being built by and productionbeing set up at the KHP.

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. . . /

MIL MOSCOW HELICOPTER PLANT-8 / Mi-8

-8 -17 / Mi-8MT and Mi-17

, . . . . . . . . . . . . . . . . . . . . . . . . . . 18.31Length, m , . . . . . . . . . . . . . . . . . . . 21.29Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . 7260Empty weight, kg , . . . . . . . . . . . . . . . . 11100Normal take-off weight, kg , . . . . . . . . . . . . . . 12000Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . 4000Commercial load, kg , / . . . . . . . . . . . . 250Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 225Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 1800Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . 4500Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 520Range, km


2-117 - 1500 .. -24 24 1961 ., 2-117 9 1963 . 1965 . - ( 4500 -), 1970 . - ( 2800 , -). 7300 -, 1400 57 . : -8 (, 4 24 ); -8 (, 28 ); -8 ( ); -8 ( ); -8 -8 ( ); -9 ( ) .

A multipurpose transport single-rotor helicopter powered by twoTV2-117A 1,500-hp gas turbine engines. The AI-24V single-engine-powered prototypes maiden flight was made on 24June, 1961. The prototype powered by two TV2-117 enginestook to the air on 9 October, 1963. Since 1965, the helicopterhas been series-produced at the Kazan helicopter plant withabout 4,500 aircraft having been built. Since 1970, the Ulan-Udeplant has been producing the Mi-8 too, the total of 2,800 heli-copters has been built as of 1999 with production carrying on).All in all, around 7,300 helicopters were made, of which over1,400 were exported to 57 countries. The main versions are asfollows: the Mi-8T 24-seat/4-tonne transport; Mi-8P 28-seatpassenger helicopter; Mi-8TV armed transport; Mi-8AT upgrad-ed transport; Mi-8PPA and Mi-8SMV electronic warfare (EW)helicopters; Mi-9 aerial command post; etc.

3-117 3-117 1900 .. 17 - 1975 . ( 1977 .) - ( 1991.). 2001 . 3000 , 800 . - : -8 -17 ( -

A multipurpose single-rotor helicopter powered by twoTV3-117MT or TV3-117VM gas turbine engines. The maidenflight was made on 17 August, 1975. Series production has beencarried out at the Kazan helicopter plant since 1977 and Ulan-Ude plant since 1991. As of 1999, there were produced about3,000 aircraft, of which over 800 were exported all over theglobe. The primary versions are the Mi-8MT and Mi-17 multipur-pose helicopters featuring a lifting capacity of 5 tonnes and pow-

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5000 3-117); -8 -17, -8-1 -17-1 (- 3-117, - ); -8-2( -8-1); -8-3 -172, -8 -171 ( - ); -8-5 -17 (- - ); -8 -171( ); -8 (- ); -19 ( - ) . 2000 . -8 , (- -8, -8 .). - - -8 (-17) -8, , . 2003 . -8. -171 29 1995 ., -171 () -172 ( ) 3 1997 .

ered by two TV3-117MT 1900-hp engines; Mi-8MTV and Mi-17V, Mi-8MTV-1 and Mi-17-1V helicopters powered by TV3-117VM 2200-hp engines which retain their performances at ahigh altitude and in high temperature; Mi-8MTV-2 an Army ver-sion of the Mi-8MTV-1; Mi-8MTV-3 and Mi-172, Mi-8AMT andMi-171 helicopters featuring modified electric equipment and arange of other improvements; Mi-8MTV-5 and Mi-17MD assaulttroops transport fitted with a cargo ramp and an increased num-ber of the troops carried; Mi-8AMTSh and Mi-171Sh an Armyattack helicopter armed with the Shturm or Ataka guided mis-siles; Mi-8MTP electronic warfare helicopters (several versions);Mi-19 airborne command post, etc. The year 2000 witnessed thelaunching of an upgrade programme for the Mi-8MTV operatedby the Russian Army Aviation. The machines are to be upratedthrough making them night-capable (the Mi-8MTKO variant fea-turing new avionics).

-24 -35 / Mi-24 and Mi-35 , . . . . . . . . . . . . . . . . . . . . . . . . . . 17.51Length, m , . . . . . . . . . . . . . . . . . . . 17.3Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . 8340Empty weight, kg , . . . . . . . . . . . . . . . . 11200Normal take-off weight, kg , . . . . . . . . . . . . . . 11500Max take-off weight, kg , . . . . . . . . . . . . . . . . . . 2400Commercial load, kg , / . . . . . . . . . . . . 335Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 280Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 2000Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . 4600Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 450Range, km

- - 3-117 2200 .. 1970-1989 . -- 3000 ., 600 30 . :-24 -25 ( - - -12,7); -24 -35 ( -); -24 -35 (-24 -30); -24 (-24 -23); -24 (--); -24 ( -); -24 -35 ( - -28 , 1999 .) . 2000 . - -24 -24 ( -24 .).

An Army attack/transport helicopter powered by two TV3-1172,200-hp engines. The helicopter had been under series productionduring 1970-1989 at the Arsenyev and Rostov-on-Don plants. Atotal of over 3,000 helicopters have been manufactured, of whichabout 600 were exported to over 30 nations. The main versions arethe Mi-24D and Mi-25 armed with the Falanga-P ATGM system andYakB-12.7 machinegun; Mi-24V and Mi-35 armed with the Shturm-V ATGM system; Mi-24P and Mi-35P armed with the GSh-30K can-non; Mi-24VP a version armed with the GSh-23 cannon; Mi-24Kreconnaissance/fire controller helicopter; Mi-24R radiation/chemicalreconnaissance helicopter; Mi-24VM and Mi-35M upgraded heli-copters fitted with the Mi-28 rotor system and sophisticated avion-ics. In the year 2000, upgrade of the Mi-24V and Mi-24P waslaunched to enable them fly combat operation round the clock (theMi-24VK version, etc.).

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-26 / Mi-26

-28H / Mi-28N

, . . . . . . . . . . . . . . . . . . . . . . . . . . 33.73Length, m , . . . . . . . . . . . . . . . . . . . 32.0Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . 28270Empty weight, kg , . . . . . . . . . . . . . . 56000Max take-off weight, kg , . . . . . . . . . . . . . . . . . . 20000Commercial load, kg , / . . . . . . . . . . . . 295Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 255Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 1800Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . 4600Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 470Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 16.85Length, m , . . . . . . . . . . . . . . . . . . . 17.2Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . 8600Empty weight, kg , . . . . . . . . . . . . . . . . 10700Normal take-off weight, kg , . . . . . . . . . . . . . . 12000Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . . 2300Combat load, kg , / . . . . . . . . . . . . 300Max speed, km/h , / . . . . . . . . . . . . . . . . . . . 265Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . 3700Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . 5700Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . 460Range, km

- 20 -136 11400 .. 14 1977 . "" 1980 . 2001 . 290 , - 16 8 . -26 : -26 (1995 .) - ; -26(1992 .) -26 (1997 .) - - -- - -; -26 (1994 .) -; -27 (1988 .) - . 27 1995 . -26 - FAR-29 - -26. 2001 . - -26 -26, - - - -, - - .

A heavy single-rotor transport/troop carrier helicopter featuring alifting capability of 20 tonnes powered by two D-136 11,400-hpengines. Its maiden flight took place on 14 December, 1977.Series production began at the Rostvertol plant in 1980. As of2001, about 290 aircraft were built, of which at least 16 wereexported to eight countries. The Mi-26 served as a base forderiving the Mi-26T civilian transport (1995), Mi-26TM (1992)and Mi-26PK (1997) crane helicopters with an add-on craneoperator cabin, Mi-26TP firefighter helicopter (1994), Mi-27 air-borne command post (1988), etc. In 1995, the Mi-26T obtaineda IAC Aviaregister certificate under the FAR-29 and was redes-ignated as Mi-26TC.

3-117 2200 .. . -28 10 1982 ., -28 1988 . 4 -28 -28. -28 14 1996 . -28.

A twin-seat Army day-and-night combat helicopter powered bytwo TV3-117VMA 2,200-hp engines and armed with the AtakaATGM system. The Mi-28 prototypes maiden flight took placeon 10 November, 1982 with the upgraded Mi-28A version takingto the air in January 1988. Four Mi-28 and Mi-28A helicopterswere built. The Mi-28N (N stands for night) prototypes maidenflight took place on 14 November, 1996. In 1999, the Rostvertolcompany commenced the preparation for the Mi-28N series pro-duction.

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-34 / Mi-34

, . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.71Length, m , . . . . . . . . . . . . . . . . . . . . 10.0Main rotor diameter, m , . . . . . . . . . . . . . . . . . . . . 950Empty weight, kg , . . . . . . . . . . . . . . . . . 1280Normal take-off weight, kg , . . . . . . . . . . . . . . . 1450Max take-off weight, kg , / . . . . . . . . . . . . . 225Max speed, km/h , / . . . . . . . . . . . . . . . . . . . . 180Cruising speed, km/h , . . . . . . . . . . . . . . . . . . . . . . . 1600Hovering ceiling, m , . . . . . . . . . . . . . . . . . . . . . . 5000Service ceiling, m , . . . . . . . . . . . . . . . . . . . . . . . . . 370Range, km

- -1426 325 .. - 17 1986 . . 1993 . . 2001 . 15 . 1995 . -34 . - -34. 1993 . -34. : -34 ( Allison 250-C20R); -34 -34 ( - -426). 2003 . -34 -34, -34 -.

A light trainer/sports helicopter featuring a single rotor and pow-ered by the M-14V26V 325-hp piston engine. Its maiden flightwas made on 17 November, 1986. Series production was initi-ated at the Arsenyev plant in 1993 and at Mil Light Helicopters(Moscow). By 2001, about 15 aircraft had been built. In 1995,the machine was awarded its airworthiness certificate. Certifiedhelicopters have a designation Mi-34S. In 1993, the Mi-34Ppolice patrol helicopter was developed on order by the Moscowmayors office. The following derivatives powered by differentengines were under development: the Mi-34A powered by asingle Allison 250-C20R turbine engine; Mi-34VAZ and Mi-34Mpowered by two VAZ-426 rotor-piston engines.

/ MIG RUSSIAN AIRCRAFT CORPORATION

-29 / MiG-29 , . . . . . . . . . . . . . . . . . . . . . . . . . . 17.32Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.36Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 38.1Wing area, sq.m , . . . . . . . . . . . . . . . . . . . 10900Empty weight, kg , . . . . . . . . . . . . . . . . 15300Normal take-off weight, kg , . . . . . . . . . . . . . . 19700Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . . 4000Combat load, kg , / . . . . . . . . . . . . . . . . . . . . . . 2450Max speed at high altitude, km/h , / . . . . . 1500Max speed at sea level, km/h . . . . . . . . . . . . . . . . . . . . . . . 2.3Max M number , . . . . . . . . . . . . . . . . . . . . . 18000Service ceiling, m , . . . . . . . . . . . . . 1500Range, km

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-29CMT / MiG-29SMT , . . . . . . . . . . . . . . . . . . . . . . . . . . . 17,32Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11,36Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 38.1Wing area, sq.m , . . . . . . . . . . . . . . . . 16850Normal take-off weight, kg , . . . . . . . . . . . . . . 21000Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . . 4000Combat load, kg , / . . . . . . . . . . . . . . . . . . . . . . 2450Max speed at high altitude, km/h , / . . . . . 1500Max speed at sea level, km/h . . . . . . . . . . . . . . . . . . . . . . . 2,3Max M number , . . . . . . . . . . . . . . . . . . . . . 18000Service ceiling, m , . . . . . . . . . . . . . 2200Range, km

- - -33 8300 . -29 6 1977 . (1982 ., . . . ), - -29 - ( 1985 .). 2001 . - 1500 -29 -, 400 - , 5 . -29 : -29 (- - , 29 1981 ., 2001 . 200 , ); -29 (- - , - 26 1986 ., 1986-1991 . - 6 ); -29 -29 ( - -- -, 1992 .); -29 ( -29 - ); -29 ( -29 - , 1995 .) .

A fourth-generation single-seat supersonic tactical fighter pow-ered by two RD-33 8,300-kgf turbofans. The MiG-29s prototypemade its maiden flight on 6 October, 1977. The fighter has beenseries-produced at the MiG Russian Aircraft CorporationsVoronin Production Centre since 1982 with the MiG-29UB twin-seat combat trainer having been manufactured at the Sokol air-craft plant (Nizhny Novgorod) since 1985. As of 2001, the totalof around 1,500 aircraft of all versions have been made, of whichover 400 were exported to nearly twenty countries, while the restof them have been operated by the Russian Air Force as well asby five CIS air forces too.The MiG-29 served as the base for deriving the following ver-sions: the MiG-29UB twin-seat combat trainer (its maiden flightwas on 29 April, 1981, as of 2001 about 200 aircraft have beenmade with the production being carried on); MiG-29M upgradedfighter featuring the new fire control system and a range of seri-ous improvements, its maiden flight was made on 26 April, 1986with six planes built during 1986-1991); MiG-29S and MiG-29SEsingleseaters boasting improved radars and RVV-AE air-to-airmissiles (series-built since 1992); MiG-29SD a version of theMiG-29 made for the Malaysian Air Force and equipped with thein-flight refuelling system and a range of other improvements;MiG-29SM a MiG-29 version design to deliver precision strikesagainst ground targets (1995); etc.

, -29 . -29 22 1998 . - 2000 . 917, . -29 - -29 , .

The MiG-29SMT is a singleseat supersonic multirole fighter,essentially, a MiG-29 upgrade featuring a novel avionics suiteand increased fuel capacity. The MiG-29SMT prototype first flewon 22 April 1998. In April 2000, the prototype with side number917 commenced its flight trials, with the prototype embodyingthe whole set of avionics improvements. The MiG-29s withRussian Air Force combat units are to be upgraded into the MiG-29SMT variant.

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-29K / MiG-29K

-AT / MiG-AT

, . . . . . . . . . . . . . . . . . . . . . . . . . . . 17,32Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11,99Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . 42,0Wing area, sq.m , . . . . . . . . . . . . . . . . . 18550Normal take-off weight, kg , . . . . . . . . . . . . . . . 22400Max take-off weight, kg , . . . . . . . . . . . . . . . . . . . . . 4500Combat load, kg , / . . . . . . . . . . . . . . . . . . . . . . 2400Max speed at high altitude, km/h , / . . . . . . 1400Max speed at sea level, km/h . . . . . . . . . . . . . . . . . . . . . . . 2,26Max M number , . . . . . . . . . . . . . . . . . . . . . . 17500Service ceiling, m , . . . . . . . . . . . . . 2000Range, km

, . . . . . . . . . . . . . . . . . . . . . . . . . . 12.01Length, m , . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.16Wing span, m , 2 . . . . . . . . . . . . . . . . . . . . . . . . . . 17.67Wing area, sq.m , . . . . . . . . . . . . . . . 4600Normal take-off weight, kg , . . . . . . . . . . . . . . 7200Max take-off weight, kg , / . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 850Max speed at sea level, km/h . . . . . . . . . . . . . . . . . . . . . . 0.85Max M number , . . . . . . . . . . . . . . . . . . . . . 15500Service ceiling, m , . . . . . . . . . . . . 1200Range, km

- Snecma/Turbomecha "" 04-R20 1440 . - 16 1996 . - 28 1997 . - . .. "" 1996 . 2001 . - 15 , . - , - -1700.

A twin-seat trainer powered by two Snecma/Turbomecha Larzac04-R20 1,440-kgf turbojet engines and foreign-made avionicssuite. The maiden flight was on 16 March, 1996. The second air-craft equipped with the Russian-made avionics was flown out on28 October, 1997. Series production was launched by the MiGRussian Aircraft Corporations Voronin Production Centre in 1996.By 2001, 15 airframes of production aircraft had been at differentdegrees of assembly, with one aircraft having been transferred tothe design bureau. The trainer is planned to be exported in a con-figuration powered by French-made engines and avionics, while avariant with Russian-made avionics and RD-1700 engines inbeing developed for the Russian Air Force.

, - -29. -29 -33 9400 1988 . - " " - -29. - 23 1988 . - -29, 420, .. 100 . 1998 . - -29 - -33 .3, -29 -29 ( 1988 .), - -29, " ".

The aircraft is a supersonic ship-borne single-seat multirolefighter derived from the baseline MiG-29 light tactical fighter.The first variant of the MiG-29K powered by two 9,400-kgf RD-33K turbofan engines was developed in 1988 to be deployed onthe Admiral Kuznetsov carrier. It was heavily commonised withthe MiG-29M multirole fighter. The MiG-29K completed its maid-en flight on 23 June 1988. A total of two MiG-29K prototypeshave been built. They have logged in excess of 420 sorties,including about 100 sorties from and onto the carrier. In 1998,the MiG-29K multirole carrier-borne fighter programme wasresumed for one of foreign customers. It provides for developingan aircraft powered by RD-33 Series 3 engines and featuring ahigh degree of airframe commonality with the MiG-29 and MiG-29K (vintage 1988) fighters and a high degree of avionics com-monality with the MiG-29SMT tactical fighter to be deployed onAdmiral Gorshkov aircraft carrier.

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-31 / MiG-31

1.44 / MiG 1.44

Официальный каталог МАКС 2005/Official Catalogue MAKS 2005

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