Royal Thai Air Force designation: BF 16

TYPE: Primary prop trainer/sportplane.

PROGRAMME: New Zealand redesign of Australian Victa Aircruiser; first flight 23 February 1972; deliveries began October 1973; 94 (plus two prototypes) built before production ended 1977 (75 CT/4A and 19 special military variants); production line reopened 1991 to build 12 civil CT/4Bs for Ansett Flying College and six for Thailand; last completed August 1992. First flight of CT/4C turboprop prototype (ZK-FXM, converted RAAF CT/4B) 21 January 1991.

CURRENT VERSIONS: T350: Turboprop version (previously known as CT/4C) with 313 kW (420 shp) Rolls-Royce 250-B17D (throttle limited to 261 kW; 350 shp) in lengthened nose. Certification was expected 1998 in anticipation of Southeast Asian order for 30, but this failed to materialise. Some interest still being shown in this version.
CT/4E: Developed version of CT/4B with more powerful engine; wing mounted slightly farther forward than on CT/4B; first flight (ZK-EUN, converted from RAAF CT/4A) 14 December 1991; NZ certification (FAR Pt 23 Amendment 36) 8 May 1992.
Detailed description applies to CT/4E.

CUSTOMERS: PAC previously built 75 CT/4As and 38 CT/4Bs further production of CT/4E began in 1997, of which 13 supplied on 20 year lease to the Royal New Zealand Air Force as replacements for CT/4Bs; contract signed 18 August 1998; first (NZ1985) delivered to Pilot Training Squadron at Ohakea in same month; last (NZ1997) on 8 June 1999; by late 2000 the fleet had accumulated 10,000 flying hours. Also used by Red Checkers aerobatic team. Thailand has requirement for 24 CT/4Es, initial order being for 12, deliveries of which began in July 1999 and were completed in June 2000 (final Thai aircraft first flew 11 May 2000). Further four Thai aircraft followed in August 2001. Total 32 (including demonstrator) built to late 2002; none further by mid-2003, although Thailand requires a further six. Two EFIS-equipped CT/4Es delivered to Singapore Youth Flying Club in June 2002.

DESIGN FEATURES: Metal translation of 1953-vintage wooden tourer. Conventional, low-wing lightplane. Tapered wings and constant-chord tailplane. Detachable wingtips to allow fitting of optional wingtip fuel tanks.
Wing section NACA 23012 (modified) at root, NACA 4412 (modified) at top; dihedral 6° 45' at chord line; incidence 3° at root; twist 3°; root chord increased by forward sweep of inboard leading-edges; small fence on outer leading-edges.

FLYING CONTROLS: Conventional and manual. Aerodynamically and mass-balanced bottom-hinged ailerons and statically balanced one-piece elevator actuated by pushrods; rudder by rod and cable linkage; ground-adjustable tab on rudder, electric trim control for elevator and rudder; electrically actuated single-slotted flaps.

STRUCTURE: Light alloy stressed skin except for Kevlar/GFRP wingtips and engine cowling; ailerons and flaps have fluted skins.

LANDING GEAR: Non-retractable tricycle type, with cantilever spring steel main legs; steerable (±25°) nosewheel carried on telescopic strut and oleo shock-absorber. Main units have Dunlop Australia wheels and tubeless tyres size 15x6.00, pressure 1.65 bar (24 lb/sq in); nosewheel has tubeless tyre size 14x4.5, pressure 1.24 bar (18 lb/sq in). Single-disc toe-operated hydraulic brakes, with hand-operated parking lock. Minimum ground turning radius 2.90 m (9 ft 6 in). Landing gear designed to shear before any excess impact loading is transmitted to wing, to minimise structural damage in event of crash landing.

POWER PLANT: One 224 kW (300 hp) Textron Lycoming AEIO-540-L1B5 flat-six engine with inverted oil system; three-blade Hartzell HC-C3YF-4BF/FC7663-2R or MT-Propeller MTV-9 series constant-speed metal propeller. Standard fuel capacity of 204.4 litres (54.0 US gallons; 45.0 Imp gallons) of which 200 litres (52.8 US gallons; 44.0 Imp gallons) are usable; wingtip tanks, each of 77.6 litres (20.5 US gallons; 17.1 Imp gallons) capacity, available optionally. Gravity fuelling point in each wing. Oil capacity 11.4 litres (3.0 US gallons; 2.5 Imp gallons).

ACCOMMODATION: Two seats side by side under hinged, fully transparent jettisonable Perspex canopy. Space to rear for optional third seat or 77 kg (170 lb) of baggage or equipment. Dual controls standard.

SYSTEMS: 28 V DC electrical system; ground power receptacle. Air conditioning optional.

AVIONICS: Garmin GNS 430 GPS/nav optional.