The FMA IA 63 Pampa is an advanced trainer aircraft with combat capability, produced in Argentina by Fabrica Militar de Aviones (FMA) with assistance from Dornier of Germany.
- IA 63
Production of the initial series has been delayed and hampered by the state of the Argentinian economy, and as a result only 18 production aircraft have been built in the first batch (1988–90) and six in the second batch (2006–07) for the Argentine Air Force. First deliveries occurred in April 1988. The 18 aircraft are in service, all modernized, with the IV Brigada Aérea (English: IV Air Brigade) at Mendoza for the advanced training role of Argentine pilots.
Vought Pampa 2000
In the 1990s, LTV/Vought selected the IA 63 as the basis for the Pampa 2000, which Vought entered into the Joint Primary Aircraft Training System competition for the United States Air Force. The Pampa 2000 lost to the Beechcraft/Raytheon entry which became the T-6 Texan II.
AT-63 Pampa “Phase 2”
With the acquisition of FMA by Lockheed Martin the Pampa was upgraded with a new engine and a more advanced avionics package compatible with the A-4AR and weapons system. This new project was called AT-63 Pampa “Phase 2″(for attack trainer) and was marketed by Lockheed Martin. The only client is the Argentine Air Force. With Lockheed Martin AN/APG-67(V)4 multimode radar Lockheed Martin Naval Electronics & Surveillance Systems selected to integrate APG-67 in Pampa.
A-4AR Fightinghawk: Details
IA-63 Pampa GT “Phase 3”
A third batch of forty new units of the redesigned Pampa was announced by FADEA on 10 October 2013. After a long delay, finally in 2015 a prototype of the third version of the IA-63 Pampa was introduced to the press. However, rampant inflation and a severe recession have made impossible for the Argentine government to finance the manufacturing of any of the promised planes.
DESIGN FEATURES: Intended for cost-effective pilot training in mission management techniques, advanced fighter lead-in training and extended-range anti-drug patrol missions. High degree of commonality with the original IA 63 Pampa, providing a customised low life-cycle cost fleet. Fail-safe service life 8,000 hours.
Non-swept shoulder-mounted wings and anhedral tailplane, sweptback fin and rudder; single engine with twin lateral air intakes. Wing section Dornier DoA-7/-8 advanced transonic; leading-edge sweep 5° 24′; thickness/ chord ratio 14.5 per cent at root, 12.5 per cent at tip: anhedral 3°.
FLYING CONTROLS: Conventional hydraulically powered ailerons, rudder, all-moving tailplane, single-slotted Fowler flaps, and door-type airbrake, deployable at all speeds, on each side of upper rear fuselage; primary surfaces have Liebherr tandem actuators and electromechanical trim.
STRUCTURE: Conventional all-metal semi-monocoque/ stressed skin; two-spar wing box forms integral fuel tank. Modified fuselage nosecone, tailcone and fintip in AT 63.
LANDING GEAR: SHL (Israel) retractable tricycle type, with hydraulic extension/retraction and emergency free-fall extension. Oleo-pneumatic shock-absorbers. Single Messier-Bugatti wheel on each unit with Goodrich (main) or Continental (nose) low-pressure tyre; nosewheel offset 10 cm (3.9 in) to starboard. Tyre sizes 6.50-10 (10 ply) on mainwheels, 380×150 (4/6 ply) on nosewheel, with respective pressures of 6.55 bar (95 lb/sq in) and 4.00 bar (581b/sqin). Nosewheel retracts rearward, mainwheels inward into underside of engine air intake trunks. Messier- Bugatti mainwheel hydraulic disc brakes incorporate antiskid device; nosewheel steering (±47°). Gear designed for operation from unprepared surfaces.
ACCOMMODATION: Tandem, rear seat elevated, on UPC (Stencel) S-III-S3IA63 zero/zero ejection seats. Ejection procedure can be preselected for separate single ejections, or for both seats to be fired from front or rear cockpit. HOTAS operation; dual controls standard. One-piece wraparound windscreen. One-piece canopy, with internal screen, is hinged at rear and opens upward. Entire accommodation pressurised and air conditioned. (Note: all British components from the aircraft, such as the Martin Baker ejection seats and replaced them with the Russian K-36)
Martin Baker ejection seatsRussian K-36
SYSTEMS: Honeywell environmental control system, maximum differential 0.30 bar (4.4 lb/sq in), supplied by high- or low-pressure engine bleed air, provides a 1,980 m (6,500 ft) cockpit environment up to flight level 5,730 m (18,800 ft) and also provides ram air for negative g system and canopy seal. Oxygen system supplied by 10 litre (0.35 cu ft) lox converter. Engine air intakes anti-iced by engine bleed air.
Two independent hydraulic systems, each at pressure of 207 bar (3,000 lb/sq in), each supplied by engine-driven pump. Each system incorporates a bootstrap reservoir pressurised at 4 bar (58 lb/sq in). No.l system, with flow rate of 16 litres (4.2 US gallons; 3.5 Imp gallons)/min, actuates primary flight controls, airbrakes, landing gear and wheel brakes No. 2 system, with flow rate of 8 litres (2.1 US gallons; 1.75 Imp gallons)/min, actuates primary flight controls, wing flaps, emergency and parking brakes, and nosewheel steering. Honeywell ram air turbine provides emergency hydraulic power for No. 2 system if engine shuts down in flight and pressure in this system drops below minimum.
Electrical system (28 V DC) supplied by Lear Siegler 400 A 11.5 kW engine-driven starter/generator; secondary supply (115/26 V AC power at 400 Hz) from two Flite- Tronics 450 VA static inverters and two SAFT 27 Ah sealed lead batteries. Thirty minutes of emergency electrical power available in case of in-flight engine shutdown.
AVIONICS: Comms: Two VHF/UHF transceivers and direction-finder, intercom and IFF or ATC transponder.
Radar: Lockheed Martin AN/APG-67(V)4 multimode radar optional (not fitted in Argentine Air Force aircraft).
Flight: VOR/ILS with marker beacon receiver; DME or Tacan optional; autonomous ESIS/air data computer, HSI, ADF, ADI; Honey well HG 764 laser INS with GPS; radar altimeter; air data computer.
Instrumentation: Single 127 mm (5 in) HUD (multimode: UFCP, PDU, PSVS and camera); colour HUD camera/airborne videotape recorder; video repeater; 12.7 x 17.8 cm ( 5 x 7 in) liquid crystal MFD in each cockpit for Argentine Air Force; second, similar MFD in each cockpit (for EICAS) for export version; Multirole central computer and MIL-STD-1553B digital databus.
Mission: New integrated weapon delivery system. Mission computer/symbol generator/integrated comms; weapon management system/data transfer unit; steerable laser ring finder optional: radar warning receiver optional; chaff/flare dispenser.
ARMAMENT: Five stations for external stores, stressed for 440 kg (970 lb) on centre fuselage and each inboard underwing station, 290 kg (639 lb) on each outboard underwing station, all at +5.5/—2 g. Phase III aircraft will have further pair of pylons further outboard, each rated at 170 kg (375 lb), for total of seven, plus uprated inboard wing pylons. Several external stores configurations including Mk 81 and Mk 82 bombs; LAU-32, LAU-51 and LAU-10 rocket pods; 30 mm gun pod (centreline), twin machine gun pods; and CBLS 200 practice bomb carriers.
Specifications (IA 63)
- Crew: two
- Length: 10.93 m (35 ft 10¼ in)
- Wingspan: 9.69 m (31 ft 9¼ in)
- Height: 4.29 m (14 ft 1 in)
- Wing area: 15.63 m2 (168.2 ft2)
- Airfoil: Dornier DoA-7
- Empty weight: 2,821 kg (6,219 lb)
- Loaded weight: 3,500 kg (7,716 lb)
- Max. takeoff weight: 5,000 kg (11,023 lb)
- Powerplant: 1 × Garrett TFE731-2-2N turbofan, 15.57 kN (3,500 lbf)
1 x Garrett TFE731-2-2N turbofan
Garrett TFE731-2-2N turbofan, 15.57 kN (3,500 lbf)
- Type: Turbofan
- Length: 50 in (127 cm)
- Diameter: 39 in (100 cm)
- Dry weight: 734 lb (333 kg)
- Compressor: 1 stage fan, 4 axial low pressure compressor stages, 1 centrifugal high pressure compressor stage
- Combustors: Annular
- Turbine: 1 stage high pressure turbine, 3 stage low pressure turbine
- Maximum thrust: 3500 lbf (15.6 kN)
- Overall pressure ratio: 13:1
- Fuel consumption: 875 lb. per hour
- Specific fuel consumption: 0.5 lb/lbf-hr
- Thrust-to-weight ratio: 4.7:1
Garrett TFE731-2 specification wikiwand.com
- Never exceed speed: Mach 0.81 (at 9,500 m (31,170 ft))
- Maximum speed: 819 km/h (442 knots, 509 mph) at 7,000 m (22,965 ft)
- Cruise speed: 747 km/h (403 knots, 464 mph) at 4,000 m (13,125 ft)
- Range: 1,500 km (809 nmi, 932 mi)
- Service ceiling: 12,900 m (42,325 ft)
- Rate of climb: 30.2 m/s (5,950 ft/min)
- Guns: 1× 30 mm (1.18 in) Defa-Giat 554
- Hardpoints: 5 with a capacity of
- 400 kg (880 lb) on inboard underwing pylons
- 250 kg (550 lb) on fuselage centerline and outer wing pylons
Source: sinodefenceforum.com, aviamarket.org, wiki
Updated Jan 04, 2017
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