TYPE: Two-seat lightplane.

PROGRAMME: Development of L-4 Cub, via PA-11/US Army L-18B; first certified in PA-19/L-18C guise 1 April 1949, followed by civil PA-18 Super Cub equivalent 18 November 1949 (67 KW; 90 hp Continental C90-12F); further variants included PA-18-125 (L-21A), PA-18-135 (L-21B) and PA-18A agricultural version and PA-18S seaplane. Remained in production until final 24 Super Cubs built in 1994; marketing from mid-1980s was by WTA Inc of Lubbock, Texas, but aircraft supplied by Piper.
Current production began in 1999; prototype N901CC. Type certificate retained by New Piper Aircraft Inc, although that company does not participate in present aircraft.

CURRENT VERSIONS: PA-18-180 Top Cub: As described. Not previously available in this engine power from Piper; optional MTOW of 907 kg (2,000 lb). Custom options as described.
Cub Light: Described separately.

CUSTOMERS: Total 10,346 (plus three PA-19s) built by Piper. Cub Crafters registered 64th from current production in July 2003.

COSTS: US$135,975 (2002) standard 793 kg; 1,750 lb MTOW; US$139,470 for 907 kg (2,000 lb) MTOW.

DESIGN FEATURES: Braced high-wing monoplane, with V struts each side. Lightweight aluminium oil cooler below engine cowling is recognition feature of Cub Crafters' aircraft (but is optional Super Cub retrofit), as are optional drooped wingtips, anti-spin strakes ahead of tailplane and 36 vortex generators on each wing leading-edge, all for enhanced STOL performance.
Wing section USA 35B. Thickness/chord ratio 12 per cent. Dihedral 1°. No incidence at mean aerodynamic chord. Total washout of 3° 18'.

FLYING CONTROLS: Plain ailerons and trailing edge flaps of light-alloy construction and skinning. Tailplane incidence variable for trimming. Balanced rudder and elevators. Optional extended ailerons; optional drooping ailerons (18°).

STRUCTURE: Wing has 4130 aluminium spars and stamped aluminium ribs, aluminium sheet leading-edge and aileron false spar, with Ceconite 7600 covering polyurethane finished, pop-riveted to structure. The fuselage is a rectangular welded steel tube structure covered with Ceconite 7600; glass fibre engine cowling. Tail unit is a wire-braced structure of welded steel tubes and channels, covered with Ceconite 7600; optional metal belly skin extending 1.07 m (3 ft 6 in) forward of sternpost.

LANDING GEAR: Tailwheel type; fixed. Two side Vs and half axles hinged to bottom of fuselage. Rubber chord shock absorption. Mainwheel tyres size 8.50-6; optional Goodyear 26x10.50-6; (6 ply) or 79 cm (31 in) Alaska Bush wheels; Scott 3200 steerable leaf spring tailwheel size 2.60/2.50-4. Dual Cleveland wheels and brakes; parking brake standard. Wipline 2100 or EDO 2000 floats optional.

POWER PLANT: One 134 kW (180 hp) Textron Lycoming O-360-C4P flat-four engine, driving a Sensenich two-blade fixed-pitch metal propeller. Optional O-360-C1G with constant-speed propeller. One 68 litre (18.0 US gallon; 15.0 Imp gallon) metal fuel tank in each wing. Total fuel capacity 136 litres (36.0 US gallons; 30.0 Imp gallons), of which 135.5 litres (35.8 US gallons; 29.8 Imp gallons) are usable; no header tank. Refuelling points on top of wing. Fuel options comprise 68 litre (18.0 US gallon; 15.0 Imp gallon) belly tank with combined cargo pod for total 204 litre (54.0 US gallon; 45.0 Imp gallon) capacity; 121 litre (32.0 US gallon; 26.7 Imp gallon) belly tank for total 257 litre (68.0 US gallon; 56.7 Imp gallon) capacity; or replacement of existing wing tanks by two tanks totalling 182 litres (48.0 US gallons; 40.0 Imp gallons) or two totalling 231 litres (61.0 US gallons; 50.8 Imp gallons).

ACCOMMODATION: Two persons in tandem with dual controls. Adjustable front seat. Heater and adjustable fresh air control. Downward-hinged door on starboard side, and upward-hinged window above, can be opened in flight. Sliding window on port side. Baggage compartment aft of rear seat can be enlarged by removal of latter; additional 23 kg (50 lb) of baggage in optional cargo/fuel belly tank; optional 64 kg (140 lb) baggage (only) pod; baggage door on starboard side.

SYSTEMS: Electrical system comprising 50 A alternator, 12 V engine starter and 17 A battery, standard.

AVIONICS: Standard package includes an altimeter, airspeed indicator, magnetic compass, tachometer, oil pressure gauge, ELT.
Optional avionics packages comprise: Standard: Garmin GNC 250XL moving map GPS/com, Garmin GTX 327 transponder and PM1000 II intercom; Deluxe VFR: Garmin 420 moving map GPS/com, GTX 327 and PM1000; and Deluxe IFR: Garmin 430, GI 106A course deviation indicator, GTX 327, GMA 340 audio panel.

EQUIPMENT: Navigation lights standard.