English name: Dawn

TYPE: Four-seat lightplane.

PROGRAMME: Design began 1992; construction of prototype started 1993; first flight 26 January 1995; further airframe for static testing; JAR 23-standard domestic type certificate awarded September 2000; construction of first production aircraft (now Fajr F-3A) began 2001; first deliveries 2002. Development plans so far announced include introduction of retractable landing gear (Fajr F-3B, certified in 2004) and some weight reduction measures to improve cruise performance.

CUSTOMERS: Domestic orders for 20 by January 2003. Five reportedly completed by that time, of which two then delivered; a sixth had been completed by November 2004. Ordered by Iranian Border Patrol, which is reported to have requirement for 10.

DESIGN FEATURES: Intended for pilot training and utility roles. Designed for low cost and easy maintenance.
Horstmann-Quast HQ-42E advanced laminar aerofoil section, with thickness/chord ratio of 16 per cent and 2° 17' sweepback. Dihedral 6° 30' from roots; twist -2° 30'; incidence 2° 18'. Raked wingtips.

FLYING CONTROLS: Conventional and manual (push/pull rods). Horn-balanced ailerons, elevators and rudder, each with inset tab (ground-adjustable on ailerons, electrically actuated on elevators and rudder). Electrically actuated single-slotted Fowler flaps. Deflection angles: ailerons +22/-15°; elevators +30/-25°; rudder ±30°; flaps +15/-40°; rudder and elevator trim tabs ±25°.

STRUCTURE: All-composites; monocoque fuselage; high-stress parts of glass fibre airframe are reinforced with carbon fibre. Wings and horizontal tail, including control surfaces, are two-spar (I and C section) structures primarily of glass fibre/epoxy/foam sandwich shells. Two-piece monocoque fuselage of similar construction, with unidirectional carbon fibre reinforcement; embedded longerons; integral fin; Kevlar cowling.

LANDING GEAR: Tricycle-type; fixed on first few aircraft; now also retractable. Goodyear tyres; size 15x6.00-6 (main) and 5.00x5 (6 ply) (nose); pressures 4.41 bar (64 lb/sq in) and 3.38 bar (49 lb/sq in) respectively. Nose gear is steerable (±18°) through a mechanical linkage to the rudder pedals. Parker Hannifin brakes are direct-operation, hydraulically actuated disc type. Minimum ground turning radius 2.75 m (9 ft 0¼ in).

POWER PLANT: One Textron Lycoming AEIO-540-L1B5D flat-six engine, flat rated at 201 kW (270 hp), driving a three-blade Hoffmann HOV 123K-KV-K200-AH constant-speed propeller. Fuel capacity 212 litres (56.0 US gallons; 46.6 Imp gallons) standard; 292 litres (77.1 US gallons; 64.2 Imp gallons) optional. Oil capacity 15.1 litres (4.0 US gallons; 3.3 Imp gallons).

ACCOMMODATION: Four persons, in pairs. Dual controls. Two upward-hinged window/doors of glass fibre. Cabin heated and ventilated.

SYSTEMS: 24 to 28 V DC electrical system powered by Gill 70 A 10 Ah alternator. Oxygen system.

AVIONICS: IFR or VFR, to customer's requirements. Options include Bendix/King VHF com, ADF and GPS.

DIMENSIONS, EXTERNAL:

  • Wing span: 10.50 m (34 ft 5½ in)
  • Wing chord: at root: 1.76 m (5 ft 9¼ in)
    • mean aerodynamic: 1.40 m (4 ft 7 in)
    • at tip: 0.94 m (3 ft 1 in)
  • Wing aspect ratio: 7.9
  • Length overall: 8.07 m (26 ft 5¾ in)
  • Height overall: 3.05 m (10 ft 0 in)
  • Tailplane span: 3.87 m (12 ft 8¼ in)
  • Wheel track: 2.08 m (6 ft 10 in)
  • Wheelbase: 1.78 m (5 ft 10 in)
  • Propeller diameter: 2.10 m (6 ft 10¾ in)
  • Propeller ground clearance: 0.175 m (7 in)

DIMENSIONS, INTERNAL:

  • Cabin: Length: 2.18 m (7 ft 1¾ in)
    • Max width: 1.25 m (4 ft 1¼ in)
    • Max height: 1.53 m (5 ft 0¼ in)

AREAS:

  • Wings, gross: 14.02 m² (150.9 sq ft)
  • Ailerons (total, incl tabs): 0.46 m² (4.95 sq ft)
  • Flaps (total): 0.95 m² (10.23 sq ft)
  • Fin: 2.33 m² (25.08 sq ft)
  • Rudder (incl tab): 0.91 m² (9.80 sq ft)
  • Tailplane: 2.95 m² (31.75 sq ft)
  • Elevators (total, incl tabs): 1.16 m² (12.49 sq ft)

WEIGHTS AND LOADINGS:

  • Weight empty: 1.100 kg (2.425 lb)
  • Max fuel weight: standard: 141 kg (311 lb)
    • optional: 204 kg (450 lb)
  • Max T-O and landing weight: 1.580 kg (3.483 lb)
  • Max wing loading: 112.7 kg/m² (23.08 lb/sq ft)
  • Max power loading: 7.85 kg/kW (12.90 lb/hp)

PERFORMANCE (A: fixed gear, B: retractable gear):

  • Never-exceed speed (VNE): A,B: 200 kt (370 km/h; 230 mph)
  • Max cruising speed: A: 148 kt (274 km/h; 170 mph)
    • B: 175 kt (324 km/h; 201 mph)
  • Cruising speed at 75% power: A: 128 kt (237 km/h; 147 mph)
    • B: 148 kt (274 km/h; 170 mph)
  • Stalling speed, power off:
    • flaps up: A, B: 67 kt (125 km/h; 78 mph)
    • flaps down: A, B: 56 kt (104 km/h; 65 mph)
  • Max rate of climb at S/L: A: 280 m (920 ft)/min
    • B: 314 m (1,030 ft)/min
  • Service ceiling: A: 5,180 m (17,000 ft)
    • B: 5,790 m (19,000 ft)
  • T-O run: B: 310 m (1,020 ft)
  • T-O to 15 m (50 ft): A, B: 630 m (2,070 ft)
  • Landing from 15 m (50 ft): A, B: 720 m (2,365 ft)
  • Landing run: B: 330 m (1,085 ft)
  • Range, standard fuel: A: 502 n miles (930 km; 577 miles)
    • B: 702 n miles (1,300 km; 807 miles)
  • Endurance: A: 4 h 30 min
    • B: 6 h
  • g limits: A, B: +4.4/-1.76