English name: Elevation

TYPE: Twin-turboprop airliner.

PROGRAMME: Licence-built Antonov An-140. Selected by Iran in 1995, against competition from 12 other contenders; initial agreement leading to Iranian manufacture signed February 1996; first stage is assembly from imported KhGAPP CKD kits at rate of up to 12 per year (first two kits received by early 2000); long-term objective is gradual progress to local parts manufacture; Iranian engineers installed at Antonov from 1997. Similar agreement with TEM to assemble power plant. Contract announced late 1998 for initial quantity of 80 aircraft by second quarter 2009, for Iranian domestic (civil and military) use only, but possibility of additional 25 production for export to CIS states has been suggested. In May 1999, Iran Electronics and Leninets (St Petersburg, Russia) signed contract for Ir.An-140 avionics development. Assembly of first aircraft (c/n 90-01) began at Esfahan March 1999 and completed by September 2000; maiden flight achieved on 7 February 2001. Second aircraft (of initial batch of eight) rolled out 26 December 2002, maiden flight in March 2003. Iranian certification awarded 14 April 2003. First two aircraft (EP-SFD and 'SFE) handed over to Safiran on 10 October 2003 and began revenue services on 29 November 2004; third completed late 2003 but still unflown by March 2005, at which time two more awaiting acceptance and further three reportedly in final assembly. Fourth aircraft reported to have been completed by time of Dubai Air Show in November 2005, when agreement signed for supply of a further 40 An-140-100 kits, assembly of which scheduled to begin in second quarter of 2010.
Total of 14 originally scheduled for completion from CKD kits by end of 2004, but due to funding delays only three completed at that time. Revised plan called for additional four by March 2006 and next eight by March 2007, with annual output rate of 12 to be achieved in 2008. Offered for passenger (including VIP) civil transport, aeromedical (ambulance or flying hospital) use, cargo/passenger or parachutist carrying, photogrammetry, geosurvey, environmental research, fisheries protection and pollution control; military versions could include staff or personnel transport, coastal and maritime patrol, radar patrol/missile guidance, elint and crew training. MPA to be next version developed; HESA reports IRI Navy requirement for about 10; hoped to roll out first example in 2006.

CURRENT VERSIONS: Ir.An-140: First three Iranian-assembled aircraft. Following description applies to this version.
Ir.An-140-100: Iranian production switched to this version from fourth aircraft onwards. KhGAPP scheduled to deliver first four CKD kits in 2004; up to 10 supplied or earmarked by mid-2006.
Stretched version: Projected version with 3.80 m (12 ft 5½ in) longer fuselage seating up to 68 passengers; 2.237 kW (3,000 shp) engines, 22.400 kg (49,383 Ib) MTOW and 917 n mile (1,700 km; 1,056 mile) range.
Ir.An-140MPA: Maritime patrol version; under collaborative design development with three other companies in 2002-03 (undisclosed, but thought to be KhGAPP, Antonov and Thales). Major changes (based on Ir.An-140-100 airframe) would be: bubble window each side of front fuselage; undernose FLIR turret; ventral search radar; underwing stations for weapons or auxiliary fuel tanks; MAD tailboom; and ESM suite. Internally, cabin configured for up to four systems operator positions. Roles could be extended to ASuV and/or ASW missions.
Ir.An-140T: Military transport; as TC but without rear ramp.
Ir.An-140TC: Tactical transport; under similar collaborative design development to MPA version; planned to be third version developed; rear fuselage redesigned to incorporate rear-loading ramp. Internal capacity for (typically) three 106 mm AA guns, three light vehicles or five LD3 containers; or up to 36 paratroops and a jumpmaster.

CUSTOMERS: Launch customers initially reported as Iran Air and Iran Asseman Airlines, of which latter signed order for 20 in October 1999, but Iran Air later declined to operate the type. Stated in October 2000 that 'orders' had been received for 127, but these revealed by early 2005 as letters of intent and total reduced to 112. Briefly operated in mid-2003 by Kish Air, first two then being delivered in October 2003 to Safiran Airlines, which has ordered six. Scheduled services with Safiran (Tehran to Gorgan) began 29 November 2004. Seventh aircraft, due to be delivered in 2006, will be first of four ordered by Arvand Air. Estimated Iranian market for 80. Likely also to be procured by Iranian Air Force and Navy (potential roles tactical transport, maritime patrol and EW). Africa regarded as most likely export market.

COSTS: USD8.5 million unit price (2005); set-up of production line USD273 million.

POWER PLANT: Two TEM-assembled AI-30 Series I (Motor-Sich-built Klimov/ZMKB Progress TV3-117VMA-SBM1) turboprops, each flat-rated at 1,864 kW (2,500 shp) and driving an AV-140 six-blade propeller. First Iranian-assembled engine completed January 2005. Fuel capacity 5,460 litres (1,442 US gallons; 1,201 Imp gallons).

AVIONICS: Supplied initially by Avio Pribor; Thales (Sextant) suite under negotiation in 2002-03.

DIMENSIONS, EXTERNAL:

• Wing span: 25.505 m (83 ft 8¼ in)
• Wing aspect ratio: 11.5
• Length: overall: 22.605 m (74 ft 2 in)
• fuselage: 22.46 m (73 ft 8¼ in)
• Fuselage max diameter: 2.82 m (9 ft 3 in)
• Height overall: 8.23 m (27 ft 0 in)
• Elevator span: 9.385 m (30 ft 9½ in)
• Wheel track (c/l of shock struts): 3.18 m (10 ft 5¼ in)
• Wheelbase: 8.125 m (26 ft 8 in)
• Distance between propeller centres: 8.20 m (26 ft 10¾ in)
• Propeller diameter: 3.72 m (12 ft 2½ in)
• Passenger door (rear, port): Height: 1.68 m (5 ft 6¼ in)
• Width: 0.915 m (3 ft 0 in)
• Service door (rear, stbd): Height: 1.29 m (4 ft 2¾ in)
• Width: 0.62 m (2 ft 0½ in)
• Cargo door (fwd, stbd): Height: 1.29 m (4 ft 2¾ in)
• Width: 0.985 m (3 ft 2¾ in)
• Emergency exit (fwd, port): Height: 1.18 m (3 ft 10½ in)
• Width: 0.51 m (1 ft 8 in)

DIMENSIONS, INTERNAL:

• Passenger cabin:
• Length:
• excl galley/lavatory and baggage area: 11.60 m (38 ft 0¾ in)
• incl galley/lavatory and baggage area: 14.51 m (47 ft 7¼ in)
• Max width: 2.60 m (8 ft 6¼ in)
• Width at floor: 2.28 m (7 ft 5¾ in)
• Aisle width: 0.46 m (1 ft 6 in)
• Max height: 1.90 m (6 ft 2¾ in)
• Underfloor cargo hold: Length: 3.98 m (13 ft 0¾ in)
• Width: 1.45 m (4 ft 9 in)
• Max depth: 0.545 m (1 ft 9½ in)
• Baggage/cargo compartment volume:
• rear: 6.1 m³ (215 cu ft)
• underfloor: 3.0 m³ (106 cu ft)
• Overhead bins volume (total): 2.3 m³ (81 cu ft)

AREAS:

• Wings, gross: 56.36 m² (606.6 sq ft)

WEIGHTS AND LOADINGS:

• Weight empty: 11,800 kg (26,015 lb)
• Max fuel weight: 4,370 kg (9,634 lb)
• Max payload: 6,000 kg (13,228 lb)
• Baggage/cargo compartment capacity:
• rear: 1,040 kg (2,293 lb)
• underfloor: 560 kg (1,235 lb)
• Max T-O weight: 21,500 kg (47,399 lb)
• Max landing weight: 21,000 kg (46.297 lb)
• Max zero-fuel weight: 19,200 kg (42,329 lb)
• Max wing loading: 381.5 kg/m² (78.13 lb/sq ft)
• Max power loading: 5.64 kg/kW (9.26 lb/shp)

PERFORMANCE:

• Max cruising speed at FL180: 288 kt (533 km/h; 331 mph)
• Max rate of climb at S/L: 420 m (1,378 ft)/min
• Service ceiling: 7,600 m (24,940 ft)
• Max operating altitude: 6,250 m (20,500 ft)
• T-O distance, 10° flap: 1,350 m (4,430 ft)
• Landing distance, 40° flap: 1,295 m (4,250 ft)
• Range at optimum cruising speed, 45 min reserves:
• with 52 passengers: 1,112 n miles (2,060 km; 1,280 miles)
• with 46 passengers: 1,430 n miles (2,650 km; 1,646 miles)
• with 34 passengers: 1,987 n miles (3,680 km; 2,286 miles)
• Ferry range: 2,105 n miles (3,900 km; 2,423 miles)
• Endurance: 6h

OPERATIONAL NOISE LEVELS (estimated):

• T-O, flyover: 85.0 EPNdB
• Sideline: 82.5 EPNdB
• Approach: 89.5 EPNdB

The article appears in the following publication:
Jane's All the World's Aircraft 2007-2008. Jane's Information Group Ltd. 2007. ISBN: 0-7106-2792-0