RANS S-16 Shekari

Prototyped as a taildragger at Oshkosh in 1994, it was later improved, first flown on 25 March 1997, as a nose gear, with a shorter and narrer chord wing, but 160 lb heavier. Powered by an 80 hp Rotax 912, it was shown at Sun ‘n Fun in April 1997.

The prototype was then fitted with a 129 hp Continental IO-240-B and a 66 x 66 Sensenich propeller.

The S-16 spar had been tested to + and –9G ultimate and the tail surfaces to the limit of Vne. The aircraft can be assembled without jigs. The spars are attached to the fuselage and the wing is then built around the spars. The fuselage is a composite shell, moulded in quarters, and encloses a prewelded 4130 tubular cage in the cockpit area. Four aluminium bulkheads are positioned between the rear of the turtledeck baggage compartment, which can be extended, and the tailcone. The fuselage composite is a straight laminate without a core.

The wing has a NASA GAW(2) series semi-symmetrical airfoil. It is all aluminium, covered with 2024-T3, 0.025 sheet. The main spars are tapered box beams of maximum 6 inch height with 2.5 inch caps. The rear spars are C channels. Each wing half has nine stamped aluminium ribs. Ailerons and flaps have an equal 50% span. Ailerons have a 2:1 differential with push-pull tube control; flaps offer three position deflection, manually operated to a maximum of 45 degrees through a centre positioned cockpit lever.

The tail’s vertical fin and stabiliser are seamless composite structures, moulded with the fuselage, and each having three composite ribs. Elevator and rudder are aluminium, containing four stamped ribs. The rudder is controlled by cable, and the elevator by torque tube. All of the aluminium components are assembled with Cherry Max blind rivets. Controls are dual, except the toe brakes on the left side only.

The cockpit is covered by a forward hinged, composite framed bubble canopy with gas lift struts. A composite and aluminium rollover arch is provided.

The option of nose or tailwheel is assisted by both type of gear sockets are included in the welded passenger cage. Both configurations use heat treated, tapered 6150 steel shaft. The tail spring is also tapered steel.  The nose gear uses a chromoly strut with heavy duty compression spring. Leg fairings are metal, wheelpants composite. Aero Trainer 6.00 x 6 tires are on spun aluminium Matco wheels with dual caliper brakes on the mains.

Approach speed is around 75 mph, across the fence at 60 mph, and touchdown at 55 mph.

In 1998 the kit price, including Continental engine, was US$39,000. Less engine the kit was US$25,000, and less firewall forward was US$21,000.

Engine: Rotax 912, 78 hp
HP range: 78-130.
Vne: 248 mph
Cruise: 140 mph.
Range: 630 sm
Stall: 50 mph.
ROC: 800 fpm
Take-off dist: 375 ft.
Landing dist: 500 ft
Service ceiling: 14,000 ft.
Fuel cap: 16 USG
Weight empty: 700 lbs.
Gross: 1200 lb
Height: 5 ft.
Length: 19.9 ft
Wing span: 24 ft.
Wing area: 86 sq.ft
Wing: NASA GAW(2)
Seats: 2.
Landing gear: tail wheel
Wheel tread: 6 ft 8 in
Cockpit width: 40 in
Headroom: 38 in
Legroom: 52 in
Horizontal tail span: 6 ft 9 in

Engine: Continental IO-240B,130hp
Propeller: 66 x 66 Sensenich
Height: 5.4 ft
Length: 18.7 ft.         
Wing span: 24 ft
Wing area: 87 sq.ft.
Wing: NASA GAW(2)
Weight empty: 830 lbs
MTOW: 1300 lbs.     
Fuel cap: 32 USG.
Vne: 248 mph.     
Cruise 65%: 170 mph
Stall: 55 mph.
Range: 850 sm
Rate of climb; 1200 fpm @ 95 mph
Take off speed: 60 mph
Take-off dist: 400 ft
Landing dist: 500 ft.     
Service ceiling: 14,000 ft
Roll rate: 200 deg/sec
Glide ratio: 9:1
Seats: 2
Cockpit width: 40 in
Headroom: 38 in
Legroom: 52 in
Landing gear: tail or nose.    
Wheel tread: 6 ft 8 in
Horizontal tail span: 6 ft 9 in
Design load: +9/-9g