Brantly 305 / H-5
Brantly produced an enlarged B-2, named the Model 305 which had a longer forward fuselage providing a rear 3-passenger bench seat. The new five seater (N2200U) made its first flight in January 1964, powered by a 305hp Lycoming IVO-540-A1A engine and received its type certificate on 29 July 1965. Brantly immediately commenced production but the Model 305 suffered from persistent ground resonance problems and they only built 45 examples.
It differs from the B2B externally by having a small variable-incidence tail-plane, and an enlarged cabin accommodates a total of five persons on two side-by-side forward seats, and an aft bench seat for three.
The rotor system and airframe was the same as the B-2B, but enlarged and conventional direct mechanical flying controls.
The landing gear was a choice of skid, wheel or float gear. Skid type has four oleo struts, two on each side, and small retractable ground handling wheels. Wheel gear has single mainwheels and twin nosewheels, all with oleo-pneumatic shock-absorbers of Brantly manufacture. Goodyear mainwheels and tyres size 5.00-5, pressure 1.93 bars. Goodyear single-disc hydraulic brakes on mainwheels.
The 227.4kW Textron Lycoming IVO-540-B1A flat-six engine, was mounted vertically, with dual cooling fans. One rubber fuel cell under engine, capacity 163 litres. Refuelling point in port side of fuselage. Oil capacity 9.5 litres. A rear compartment for 113kg of baggage, with downward hinged door on starboard side.
44 were built during the 1960s and another four built by Hynes Aviation in 1985 as the H-5. Michael K. Hynes, owner of the type certificates, established Brantly-Hynes Helicopter Inc. on 1 January 1975, initially to provide product support for the large number of Brantly helicopters in use. He subsequently started up a production line for the B-2B, and also the larger Model 305.
Improved prototype with redesigned rotor head and new blade aerofoil completed about 30 hours flying by mid-January 1990. New main rotor bearing fitted. Cabin streamlined. New production was to begin 1993, but none built.
Engines: Lycoming IVO-540-B1A, 305 hp, 227kW
Main rotor diameter: 8.74m
Fuselage length: 7.44m
Disc loading: 4.5 lb/sq.ft.
Pwr loading: 9.5 lb/hp.
Max TO wt: 1315kg, 2900 lb.
Empty wt: 816kg, 1732 lb.
Equipped useful load: 1106 lb.
Payload max fuel: 854 lb.
Range max fuel/ cruise: 199 nm/ 1.9 hr.
Range max fuel and payload: 354km
Service ceiling: 3660m, 11,000 ft.
Max speed: 193km/h
Max cruise: 177km/h, 104 kt.
Max range cruise: 95 kt.
ROC: 975 fpm.
HIGE: 4000 ft.
HOGE: 1500 ft.
Max sling load: 800 lb.
Fuel cap: 252 lb.