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M I C R O J E T |
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The Microjet programme was started in the early 80's by Microjet SA in France, a subsidiary of Groupe Creuzet, an aircraft component manufacturer. The program was initiated by Jean-Gabriel Bayard, then president of Microturbo. The Microjet was aimed at the military training market. First flight of a wooden prototype F-WZJF occured on 24 June 1980 with Jacques Grangette at the controls. He was also the one heading the design group. First flight of a pre-production aircraft (F-WDMT) took place on 19 May 1983. The third prototype had underwing hardpoints. The following description applies to the Microjet 200 B.
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The Microjet prototypes were powered by two Microturbo TRS-18-1, each rated at 293 lbst, uprated automatically to 326 lbst if the other engine should fail during take-off. The production aircraft was to be powered by the TRS-18-2 rated at 405 lbst. The structure was a classic semi-monocoque, gear was retractable (electrical actuators), cockpit unpressurized, seats staggered by 22in, avionics was IFR and included the military extras such as UHF, TACAN and IFF. The small vertical fins on the tail were added in 1989 to address spin recovery issues. Poor performance due to inadequate powerplant made the aircraft inappropriate for its intended market.
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| DIMENSIONS | ||
| Wing Span | 24 ft 9.75 in | 7.56 m |
| Wing root chord | 2 ft 9.5 in | 0.85 m |
| Wing aspect ratio | 9.1 | |
| Wing area | 67.60 sqft | 6.28 m2 |
| Aileron area | 4.80 sqft | 0.446 m2 |
| Flap area | 7.43 sqft | 0.69 m2 |
| Wing section | RA 16.3c3 | |
| Wing dihedral | 5 deg 2 sec | |
| Wing incidence | 3 deg | |
| Wing sweep | 0 deg at 30% chord | |
| Tail area | 27.13 sqft | 2.52 m2 |
| Tail dihedral | 35 deg | |
| Tail sweep | 26 deg at 50% chord | |
| Overall length | 21 ft 10 1/2 in | 6.665 m |
| Fuselage length | 21 ft 6 1/2 in | 6.56 m |
| Fuselage width | 3 ft 7 1/4 in | 1.10 m |
| Overall height | 9ft 0 5/8 in | 2.76 m |
| Wheel track | 6 ft 3 1/2 in | 1.92 m |
| Wheelbase | 8 ft 8 in | 2.64 m |
| WEIGHTS, LOADINGS | ||
| MTOW (+7/-3.5g) | 1140 lb | 2513 kg |
| MTOW (+4/-1.8g) | 1300 lb | 2866 kg |
| Empty weight | 1719 lb | 780 kg |
| Max. wing loading | 42.4 lb/sq ft | 207 kg/m2 |
| Max fuel | 750 lb | 340 kg |
| PERFORMANCE with 326 lbst engines | ||
| Never exceed speed | 300 kts | 555 km/h |
| Thrust loading | 2.68 lb/lb | 273 kg/kN |
| SPEEDS | ||
| Max. cruise speed SL (FL180) | 250 kts | 463 km/h |
| Best cruise speed (FL180) | 210 kts | 389 km/h |
| Stall speed (power off, flaps down) (VSC) | 79 kts | 146 km/h |
| TAKE-OFF (ISA, SL) | ||
| Ground roll | 2460 ft | 750 m |
| Obstacle clearance 15m / 50ft | 3800 ft | 1150 m |
| LANDING (ISA, SL) | ||
| Obstacle clearance 15m / 50ft | 2220 ft | 675 m |
| Ground roll | 1430 ft | 435 m |
| CLIMB AND ALTITUDE | ||
| Sea level | 1772 ft/min | 540 m/min |
| Engine out (SL) | 295 ft/min | 90 m/min |
| Service ceiling | 30000 ft | 9150 m |
| One engine inop ceiling | 10000 ft | 3050 m |
| RANGES | ||
| Range at best cruise (20 min res.) | 400 nm | 741 km |
| Maximum endurance | 2 h | |
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Source: Jane's All the World Aircraft 84-85.
Last update : 28NOV03
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