Two-seat jet primary and basic trainer
Wings: Cantilever low-wing monoplane.
Wing section NACA 23015 (modified) at root, NACA 4412 (modified) at tip.
Dihedral 6°, Incidence 3° at root, 0°: at tip.
All-metal structure, with main and subsidiary spars, having three-point attachment to fuselage.
Metal-covered ailerons with balance tabs.
Hydraulically-operated slotted flaps.
Hydraulically-operated air-brakes and lift spoilers on wings at rear spar position ahead of flaps.
Air-brakes and flaps hydraulically-operated.
All-metal semi-monocoque stressed skin structure, built in two parts, comprising bulkheads, built-up frames and longerons, covered with light alloy panels.
Two sections are joined in line with wing subsidiary spar.
Hinged nose-cap provides access to pressurization, oxygen, radio and electrical equipment.
Cantilever all-metal structure.
Onepiece tailplane, interchangeable elevators, fln and rudder.
Fixed surfaces covered with smooth and movable surfaces with fluted alloy skin
Combined trim and balance tab in starboard elevator, balance tabs in port elevator and rudder.
Hydraulically-retractable tricycle type.
Main wheels retract inward into wings, nose-wheel forward.
Dowty oleo-pneumatic shock-absorbers.
Dunlop wheels and tubeless tires.
Dunlop hydraulic disc brakes.
One Rolls-Royce Bristol Viper Mk 202 turbojet engine (2,500 lb = 1,134 kg st) in fuselage aft of cockpit.
Lateral intakes on each side of forward fuselage.
Internal fuel capacity (one integral tank outboard and three bag tanks inboard in each wing) is 262 Imp gallons (1,191 liters).
Refuelling point near each wingtip.
Two wingtip fuel tanks, total capacity 96 Imp gallons (436 liters), are standard on Mk 55 aircraft
All tanks in wings are interconnected.
System designed to permit 30 seconds of inverted flight.
Oil capacity 1.75 Imp gallons (8 liters).
Two persons side-by-side in pressurised cabin, on Martin-Baker automatic ejection seats suitable for use down to ground level and 90 knots (104 mph = 167 km/h).
Power-operated rearward-sliding canopy.
Dual controls standard in T.Mk 5.
Pressurization and air-conditioning system by Normalair and Tiltman Langley, differential 3 lb/sq in (0.21 kg/cm² using engine bleed air.
Hydraulic system, pressure 1,500 lb/in² (105 kg/cm², for landing gear, flaps, air-brakes, lift spoilers and wheel brakes.
Engine-driven generator provides 28V DC supply.
Two 25Ah batteries.
Two inverters supply phased AC to flight instruments and fire warning system.
Automatically-controlled gaseous oxygen system for each crew member.
The Mk 55 is fitted with GM2L reflector gun-sights, but as an alternative SFOM sights can be fitted.
Provision is made for a camera recorder, and two 7-62-mm FN machine-guns (with 550 rpg) are fitted in the nose of each engine air intake duct.
Strong points are provided under each wing for the carriage of external stores.
For the Mk 55, these include: two 75 Imp gallon (341 liter) fuel tanks; 12 × 8-cm Oerlikon 9-7 kg rockets; 18 × 8-cm Hispano-Suiza 11-9-kg rockets; 72 × 37mm SNEB rockets in four Matra launchers; four FN 7-62-mm; machine-guns in two pods (500 rounds per gun); 48 × 2-in rockets in two White & Riches launchers; 24 × 2-75-in rockets in four Matra launchers; four Aérospatiale AS.11 missiles; 6 × 3-in Mk 6 rockets with 60-1b heads or twelve with 25-1b heads; six Type T.10 rockets with 28-kg heads; four HVAR rockets with 35-1b or 52-1b heads; 28 × 68-mm SNEB rockets in four Matra launchers; two Beagle reconnaissance packs, each with one F.95 camera; eight 25-1b practice bombs; four 540-1b bombs; two 500-lb GP bombs, or eight 19-1b fragmentation bombs.
Wing span (Mk 5): 35 ft 4 in (10.77 m)
Wing span over tip-tanks (Mk 55): 36 ft 11 in (11.25 m)
Wing chord at root: 7 ft 8 in (2.33 m)
Wing chord at tip: 4 ft 4 in (1.31 m)
Wing aspect ratio: 5.84
Length overall: 34 ft 0 in (10.36 m)
Height overall: 10 ft 2 in (3.10 m)
Tailplane span: 13 ft 6 in (4.11 m)
Wheel track: 10 ft 8.9 in (3.27 m)
Wheelbase: 9 ft 7.4 in (2.93 m)
Wings, gross: 213.7 ft² (19.80 m²)
Ailerons (total): 19.06 ft² (1.77 m²)
Flaps (total): 24.80 ft² (2.30 m²)
T-O weight - 2 crew, fuel for one hour: 6,989 lb (3,170 kg)
T-O weight - 2 crew, full internal fuel: 7,629 lb (3,460 kg)
T-O weight - 2 crew, full internal fuel and tip-tanks: 8,524 lb (3,866 kg)
Overload max T-O weight: 9,200 ]b (4,173 kg)
Max level speed:
AUW of 6,400 lb (2,900 kg) at S/L: 355 knots (409 mph; 658 km/h)
AUW of 6,400 lb (2,900 kg) at 25,000 ft (7,620 m): 382 knots (440 mph; 708 km/h)
Rate of climb:
S/L at AUW 6,900 lb (3,130 kg): 4,000 fpm (1,220 mpm)
S/L at AUW 7,600 lb (3,447 kg): 3,550 fpm (1,082 mpm)
AUW 6,900 lb (3,130 kg): 36,750 ft (11,200 m)
AUW 7,600 lb (3,447 kg) 34,500 ft (10,500 m)
AUW 6,900 lb (3,130 kg): 1,070 ft (325 m)
AUW 7,600 lb (3,447 kg): 1,340 ft (410 m)
T-O to 50 ft (15 m):
AUW 6,900 lb (3,130 kg): 1,650 ft (503 m)
AUW 7,600 lb (3,447 kg): 2,070 ft (630 m)
Landing from 50 ft (15 m):
AUW 6,400 lb (2,900 kg): 2,360 ft (720 m)
AUW 7,200 lb (3,266 kg): 2,560 ft (780 m)
AUW 6,400 lb (2,900 kg): 1,540 ft (470 m)
AUW 7,200 lb (3,266 kg): 1,740 ft (530 m)
Max range: with tip-tanks, at 160 knots (184 mph; 296 km/h) EAS at 35,000 ft (10,670 m) with 288 lb (130 kg) reserve fuel:
780 nm (900 miles; 1,450 km)
1. Wikepedia. BAC Jet Provost, 27 November 2009
2. Taylor, John W.R. (ed.) Jane's All The World’s Aircraft 1971-72. London: Jane's Yearbooks,1971. ISBN 07-032191-4.
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