Slovene Military Aviation name: Hudournik (Swift)
Royal Thai Air Force designation: BF. 19

TYPE: Basic turboprop trainer.

PROGRAMME: Design began May 1982; aerodynamic elements tested on PC-7 1982-83; first flights by two preproduction PC-9s: HB-HPA on 7 May 1984 and HB-HPB on 20 July 1984; aerobatic certification 19 September 1985. PC-9M introduced early 1997.

CURRENT VERSIONS: PC-9: Standard production version until 1997.
PC-9/A: Australian version of PC-9.
PC-9B: German target towing version of PC-9, operated for German Air Force by EIS (previously Condor Flugdienst); increased fuel for a 3 hour 20 minute mission; two Meggitt RM-24 winches on inboard pylons with targets stowed aft of winch; TAS 06 acoustic scoring system.
PC-9 Mk II: Modified for US Air Force/Navy JPATS trainer programme (T-6A Texan II).
PC-9M: Upgraded version introduced 1997 and now the standard production model. Enlarged dorsal fin fairing (as on PC-7 Mk II M) improves longitudinal stability and reduces stick forces; modified wingroot fairings improve low-speed characteristics; 'exciter strips' on wing leading-edge improve stall characteristics; new engine/propeller control system separates flight idle and ground idle modes, reducing acceleration time and improving handling.
Detailed description applies to PC-9M.
Hudournik (Swift): Dedicated weapons training version in service with Slovene Military Aviation, modified after delivery by Radom Aviation Systems of Israel. First example to this standard (L9-61) made first flight early May 1999. Mission systems installation includes Litton INS-100G inertial navigation with GPS; HOTAS controls; Flight Visions HUD with up-front control abd rear cockpit video repeater; a central flight data recorder; chaff/flare dispenser and control panel; Honeywell EFIS and displays; new weapon selection and armament control unit and displays; MIL-STD-1553B dual databus; and RS-422/ARINC 429 datalink. Maximum external stores load increased to 1,250 kg (2,756 lb).

CUSTOMERS: Total of 267 ordered and 259 built by mid-2003. Saudi aircraft prepared for delivery by British Aerospace; first pair from second batch (Nos. 31 and 32) handed over in UK on 4 December 1995. Order for eight for Irish Air Corps announced 16 January 2003, for delivery and operational capability by mid-2004.

DESIGN FEATURES: Typical turboprop trainer; stepped cockpits; aerobatic; performance and handling ease student's transition to jets. Meets FAR Pt23 (Amendment 52) and special Swiss federal civil conditions for both Aerobatic and Utility categories; complies with selected parts of US military training specifications.
Conventional, low-wing monoplane; parallel chord wing centre-section; tapered outer panels; tailplane LERX.
Wing section PIL15M825 at root, IL12M850 at tip; quarter-chord sweepback 1°; dihedral 7° from centre-section; incidence 1° at root; twist -2°.

FLYING CONTROLS: Conventional and manual. Cable-operated elevator and rudder; ailerons operated by pushrods; mass-balanced, electrically actuated trim tab in each aileron and starboard half of elevator; electrically actuated trim/anti-balance tab in rudder controlled from rocker switch on power control lever. Trim aid device (TAD) automatically adjusts rudder trim tab setting in response to changes in engine torque or aircraft airspeed. This counteracts aircraft yaw induced by variations in effect of propeller slipstream, depending upon airspeed and engine power setting. TAD can be selected on or off by switch on trim control panel on left-hand side panel of front cockpit. Electrically operated split flaps; hydraulically operated 'perforated' airbrake under centre-fuselage.

STRUCTURE: All-metal with some GFRP wing/fuselage fairings; one-piece wing with auxiliary spar, ribs and stringer-reinforced skin.

LANDING GEAR: Retractable tricycle type, with hydraulic actuation. Mainwheels retract inward to lie semi-recessed in wing centre-section covered by bulged doors; nosewheel retracts rearward; all units enclosed when retracted. Oleo-pneumatic shock-absorber in each leg. Hydraulically actuated nosewheel steering. Goodrich wheels and tubeless tyres, with Goodrich multipiston hydraulic disc brakes on mainwheels. Main tyres 20x4.4 (8 ply), nose tyre 16x4.4 (8 ply). Low-pressure tyres optional. Parking brake.

POWER PLANT: One 857 kW (1,150 shp) Pratt & Whitney Canada PT6A-62 turboprop, flat rated at 708 kW (950 shp), driving a Hartzell HC-D4N-ZA/09512A four-blade constant-speed fully feathering propeller. Single-lever engine control. Fuel in two integral tanks in wing leading-edges, total usable capacity 518 litres (137 US gallons; 114 Imp gallons). Overwing refuelling point on each side. Fuel system includes 12 litre (3.2 US gallon; 2.6 Imp gallon) aerobatics tank in fuselage, forward of front cockpit, which permits up to 60 seconds of inverted flight. Provision for two 154 or 248 litre (40.7 or 65.5 US gallon; 33.9 or 54.5 Imp gallon) drop tanks on centre underwing attachment points. Total oil capacity 16 litres (4.2 UG gallons; 3.5 Imp gallons).

ACCOMMODATION: Two Martin-Baker Mk 11A adjustable ejection seats, each with integrated personal survival pack and fighter-standard pilot equipment. Stepped tandem arrangement with rear seat elevated 15 cm (5.9 in). Seats operable, through canopy, at zero height and speeds down to 60 kt (112 km/h; 70 mph) EAS. Anti-g system. One-piece acrylic Perspex windscreen; one-piece framed canopy, incorporating roll-over bar, opens sideways to starboard. Dual controls standard. Cockpit heating, cooling, ventilation and canopy demisting standard. Space for 25 kg (55 lb) or baggage aft of seats, with external access.

SYSTEMS: Vapour cycle air conditioning system and engine bleed air for cockpit heating/ventilation and canopy demisting. Fairey Systems hydraulic system, pressure 207 bar (3,000 lb/sq in), for actuation of landing gear, mainwheel doors, nosewheel steering and airbrake; system maximum flow rate 18.8 litres (4.97 US gallons; 4.14 Imp gallons)/min. Bootstrap oil/oil reservoir, pressurised at 3.45 to 207 bar (50 to 3,000 lb/sq in). A supplementary high-pressure, one-shot nitrogen storage bottle provides power to lower the landing gear in an emergency. This bypasses the main hydraulic systems by feeding directly into shuttle valves in the down side of the main door and landing gear actuators.
Primary electrical system (28 V DC operational, 24 V nominal) powered by 30 V 300 A starter/generator and 24 V 40 Ah Ni/Cd battery; two optional static inverters can supply 115/26 V AC power at 400 Hz. Ground power receptacle. Electric anti-icing of pitot tube, static ports and AoA transmitter standard; electric de-icing of propeller blades. Diluter demand oxygen system, capacity 1,350 litres (47.6 cu ft) selected and controlled individually from panel in each cockpit. OBOGS standard.

AVIONICS: Both cockpits fully instrumented to customer specifications, with Logic computer-operated integrated engine and systems data display. Customer-specified equipment provides flight environmental, attitude and direction data, and ground-transmitted position determining information.
Comms: Single or dual VHF, UHF and/or HF radios to customer's requirements. Audio management system controls audio services from com, nav and interphone systems.
Instrumentation: Standard IFR installation includes Mach/airspeed indicators; VSIs; main (encoding) and standby altimeters; standby attitude indicator; standby magnetic compass; combined aileron/rudder/elevator trim indicators; accelerometer indicators; electric clocks; and engine indication system with LCD displays. Advanced IFR with Flight Visions FV-4000E HUD with video camera, Astronautics and Meggitt AMLCD flight displays, rear cockpit repeater and video recorder, ADC and radar altimeter optional.

EQUIPMENT: Three hardpoints under each wing: inboard and centre stations each stressed for 250 kg (551 lb), outhoard stations for 110 kg (242.5 lb) each. Retractable 250 W landing/taxying light in each main landing gear leg bay. Optional equipment can include smoke generators for aerial displays, target towing kit, electronic jammer for EW training, and blind-flying hood.

ARMAMENT: FN Herstal package for Hudournik/Swift comprises HMP-250 12.7 mm gun pods; LAU-7A seven-round unguided rocket launchers; Alkan Type 65 adaptor and dispensers for IBDU-33 practice bombs; and a laser range-finder pod.