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Pazmany PL-2
Lipnur Aircraft Industry LT-200

 

pazpl-2


Developed from the PL.1 “Laminar”, the PL.2 is a side by side two seater, all metal tricycle undercarriage, dual control aircraft. The parallel chord wing panels incorporate flanged aluminium ribs, a main spar with machined extruded booms, a metal false rear spar and aluminium skins. The fuselage is built up of conventional pressed metal frames longerons and skins. The curved sides of the cockpit are designed to break outwards in a crash. The all flying tail is equipped with an anti-servo tab for trimming and providing adequate stick forces. The main undercarriage is attached to the wing spar and the steerable nosewheel to the engine mount. Shock absorbers are of the oleo pneumatic type. Brakes are fitted to the main wheels. All fuel is carried in two 10 Imp. gallon wing tip tanks. Cabin width is 3’ 4”. Engines from 100 to 150 hp may be fitted. And, it is stressed for aerobatics.
The design followed his earlier PL-1 but with improvements in construction techniques intended to make the aircraft easier for amateur engineers to build. Noticeable changes included an increase in dihedral for the PL-2 from 2.5 to 5 degrees and a change in the fuselage to provide for 5cm of increased cabin width.

The first one flew on April 4, 1969.

Along with the PL-1, the PL-2 is for amateur builders. The external shape and flight characteristics are almost identical to the PL-1, but the construction has been simplified. The PL-2 offers a wider cockpit, better canopy and fuselage lines, simplified dihedral and the possibility of using engines from 90 to 150-hp, Despite its aerodynamically clean lines, there are no compound curves anywhere in the skin. This is partly the result of the use of a fiberglass cowl to streamline the nose. Pilots who have flown the PL-2 say it is an airplane flown with the fingers and not the fist. And, like the PL-1, it is stressed for aerobatics.

The Vietnam, Royal Thai and Korea Air Forces have each built a prototype. So, also, has the Miyauchi Manufacturing Company in Tokyo, which hoped to market this 'homebuilt' as a production aircraft.

The PL-2 has been evaluated by the air forces of Indonesia, Korea, Thailand and Vietnam as a trainer. Fifty PL-2, known as the LT-200, were built in 1976 by Indonesia's Lipnur Aircraft Industry. The Indonesian air force's production facility, Lembaga Industri Penerbangan Nurtanio, flew the prototype (IN-200) of the LT-200 two-seat lightweight trainer on 9 November 1974; this was based on the PL-2.

PL-2
Engine: Lycoming O-235-C1B, 108 hp
Speed max: 138 mph
Cruise: 119 mph
Range: 492 sm
Stall: 41 mph
ROC: 1200 fpm
Take-off dist: 700 ft
Landing dist: 600 ft
Service ceiling: 18,000 ft
Fuel cap: 25 USG
Weight empty: 875 lb
Gross: 1416 lb
Height: 7.7 ft
Length: 19.3 ft
Wing span: 27.8 ft
Wing area: 116 sq.ft
Seats: 2
Landing gear: nose wheel

PL-2
Engine: Lycoming O-290-G, 125 hp
Wing span: 28 ft
Airfoil: NACA 63-615
Length: 18 ft. 11 in
Height: 7 ft. 7 in
Wing area: 116 sq.ft
Wing loading: 12 lb/sq.ft
Seats: 2
Empty weight: 820 lb
Useful load: 526 lbs
Gross weight: 1,400 lbs
Power loading: 11 lb/hp
Fuel capacity: 25 USG
Baggage capacity: 40 lbs
Rate of climb: 1,500 fpm
Max speed: 144 mph
Cruise speed (75% power): 130 mph
Range (at max cruise, no res): 450 sm
Stall speed (flaps down): 54 mph

PL-2
Engine: Lycoming, 135 h.p
Span: 28’ 0”
Length: 19’ 8”
Wing Area: 116 sq. ft
Empty Weight: 900 lb
Loaded Weight: 1,445 lb
Wing Loading: l2.41b/sq. ft
Max. Speed: 140 mph
Cruise Speed: 120 mph
Stall Speed: 54 mph
Initial Climb: 1,000 fpm
Range: 490 miles

PL-2A
Engine LYC-235
Power Range 108-100-150 hp
Height 7.7 ft
Length 19.3 ft
Wing Span 27.8 ft
Wing Area 116 sq. ft
Empty Weight 875 lb
Gross Weight 1,416 lb
Fuel Capacity 25 USG
Top Speed 138 mph
Cruise 119 mph
Stall 52 mph
Range 492 mi
Rate of Climb 1200 fpm
Take-Off Distance 700 ft
Landing Distance 600 ft
Service Ceiling 18,000 ft
Number of Seats 2
Landing Gear Trigear
Information Package PDF 2009 $9
Information Package printed 2009 $12
Plans 2009 $425

PL-2B
Engine: Lycoming O-320 E2A, 150hp
Propellor: Ian Henry 69x66
Span: 9.0m
Length: 6.0m
Height: 2.2m
Empty weight: 423kg
MAUW: 625 kg
Baggage: 18kg
Fuel capacity: 2 x 50 lt
Endurance: 3 hr
Fuel consumption: 32 lt/hr
VNE: 162 kts
Cruise 2450 rpm: 115 kts
Max struc cruise: 130 kts
Vfe: 88 kts
V approach: 65 kts
Vs: 45 kts
ROC: 350 ft/min at 2450 rpm
Manoeuvre envelope: +6, -3g

 

 


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