|Brantly-Hynes Model 305|
Basically a larger-scale version of the Model B-2B, the prototype of the original Brantly Model 305 was flown for the first time during January 1964. Apart from its increased dimensions, it differs from its predecessor externally by having a small variable-incidence tail-plane. Considerably more power is provided by an Avco Lycoming flat-six engine, and an enlarged cabin accommodates a total of five persons on two side-by-side forward seats, and an aft bench seat for three.
D.Donald "The Complete Encyclopedia of World Aircraft", 1997
The B-2 was a successful programme for Brantly but there was no denying that the aircraft was small and there was an opportunity for a larger version of the design. 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.
R.Simpson "Airlife's Helicopter and Rotorcraft", 1998
Original first flight January 1964; FAA type approval 29 July 1965; 44 built during mid-1960s. Another four built by Hynes Aviation in 1985 as the H-5. 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.
DESIGN FEATURES: Rotor system and airframe as for B-2B, but enlarged.
FLYING CONTROLS: Conventional direct mechanical.
STRUCTURE: As for B-2B.
LANDING GEAR: 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.
POWER PLANT: One 227.4kW Textron Lycoming IVO-540-B1A flat-six engine, 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.
ACCOMMODATION: Two individual seats side by side, with dual controls. Rear bench seat for three persons. Door on each side. Rear compartment for 113kg of baggage, with downward hinged door on starboard side.
AVIONICS: AlliedSignal or Narco radio, to customer's specification.
EQUIPMENT: Blind-flying instrumentation available, but helicopter not certified for instrument flight.
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Reed S West, e-mail, 09.01.2021 Rebecca Tracer