SOCATA TB 9 TAMPICO, TB 10 and TB 200 TOBAGO GT

TYPE: Four-seat lightplane.

PROGRAMME: Design of original TB series launched 1975; first flight of original TB 10 (F-WZJP), powered by 119 kW (160 hp) Textron Lycoming O-320, 23 February 1977; second prototype powered by 134 kW (180 hp) Textron Lycoming.
In June 1999, Socata announced irs Nouvelle Generation (New Generation) series of single piston-engined models. The title Generation Two (GT) was subsequently adopted. These feature aerodynamic and other improvements that may subsequently be incorporated in the Socata MS diesel-engined light aircraft described elsewhere in this entry. Modifications include a curved dorsal fairing for the fin, upturned wingtips, raised cabin roofline with new single-piece carbon fibre/honeycomb roof, revised window pillar design, flush-mounted windows, larger baggage door, redesigned interior and new fuel filler door. From 201st TB in mid-2003 (TB 10F-GOIH c/n 2200, displayed at Paris, 15 to 22 June 2003) all aircraft fitted with Mortiz engine control panel.
The TB 9C Tampico Club, TB 9 Sprint, TB 10 Tobago, TB 10 Tobago Privilege and TB 200 Tobago XL are now out of production, having been replaced in February 2000 by the GT series.

CURRENT VERSIONS: TB 9 Tampico Sprint GT: Baseline model. 119 kW (160 hp) Textron Lycoming O-320-D2A flat-four engine driving a Sensenich two-blade fixed-pitch metal propeller. Fuel capacity 158 litres (41.7 US gallons; 34.8 Imp gallons), of which 152 litres (40.2 US gallons; 33.4 Imp gallons) are usable. Oil capacity 8 litres (2.1 US gallons; 1.8 Imp gallons).
TB 10 Tobago GT: 134 kW (180 hp) Textron Lycoming O-360-A1AD flat-four engine. Detailed description applies to this version.
TB 200 Tobago GT: Similar to TB 10 Tobago GT, but with 134 kW (180 hp) fuel-injected Textron Lycoming IO-360-A1B6 engine.

CUSTOMERS: Total of 468 Tampicos and Tampico Clubs in service by June 1999 with customers in Africa and Middle East, Asia-Pacific, Australasia, Europe and North America. Total of 637 Tobagos and 87 Tobago XLs delivered by June 1999, to customers in Africa and Middle East, Australasia, Europe, North America and elsewhere. Production of first-generation TBs (9, 10, 200, 20 and 21) totalled 1,928, including prototypes.
Deliveries in 2000 totalled 45, 22 in 2001 and 12 in 2002, comprising three TB 9s, seven TB 10s and two TB 200s. Launch order for six TB 200 GTs, plus six options, placed by Aeronautical Academy of Europe, based in Portugal.

DESIGN FEATURES: Conventional light tourer and trainer.
Wing section RA 16.3C3; thickness/chord ratio 16 per cent; dihedral 4o 30'.

FLYING CONTROLS: Manual, with pushrod actuation for ailerons, rudder and all-moving tailplane; cable-actuated anti-balance tab on tailplane, plus ground-adjustable tabs on ailerons and rudder; strakes on lower edges of fuselage just aft of wing control turbulence under rear fuselage; electrically actuated flaps.

STRUCTURE: Conventional light alloy; single-spar wing; GFRP tips, engine cowlings, cabin roof structure and dorsal strake. Triple anti-corrosion protection.

LANDING GEAR: Non-retractable tricycle type, with steerable nosewheel. Oleo-pneumatic shock-absorber in all three units; trailing-link suspension main landing gear legs. Mainwheel tyres size 6.00-6 (6 ply), pressure 2.30 bar (33 lb/sq in) on TB 10 GT/200 GT; 15x6.00-6 (6 ply) on TB 20 GT/21 GT. Nosewheel 5.00-5 on TB10 GT/200 GT and 5.00-4 on TB 20 GT/21 GT. Glass fibre wheel fairings on all three units. Hydraulic disc brakes. Parking brake.

POWER PLANT: One 134 KW (180 hp) Textron Lycoming O-360-A1AD flat-four engine, driving a Hartzell two-blade constant-speed propeller. Two integral fuel tanks in wing leading-edges; total capacity 210 litres (55.0 US gallons; 46.2 Imp gallons), of which 204 litres (53.9 US gallons; 44.9 Imp gallons) are usable. Oil capacity 8 litres (2.1 US gallons; 1.8 Imp gallons).

ACCOMMODATION: Four or five seats in enclosed cabin, with dual controls. Separate, adjustable front seats with inertia reel seat belts. Two separate rear seats or removable three-place bench seat with safety belts. Sharply inclined low-drag windscreen. Access via upward-hinged window/doors of glass fibre. Baggage compartment aft of cabin, with external door on port side. Cabin carpeted, soundproofed, heated and ventilated. Windscreen defrosting standard.

SYSTEMS: Electrical system includes 28 V 70 A alternator and 24 V 10 A battery. Hydraulic system for brakes only.

AVIONICS: Honeywell Silver Crown avionics suite to customer choice, including Bendix/King KLN 90 GPS.
Instrumentation: Typical IFR package includes dual altimeters; dual true airspeed indicators; dual artificial horizons; vertical speed indicator, electric turn coordinator; directional gyro, tachometer; oil temperature, oil pressure, fuel pressure, fuel quantity, manifold pressure, CHT/EGT and OAT gauges; ammeter, voltmeter and compass.

EQUIPMENT: Includes armrests for all seats, map pockets, antiglare visors, stall warning indicator, tiedown fittings and towbar, landing and navigation lights, four individual cabin lights and instrument panel lighting.

 

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