By September 2003,
Robinson had produced 5,000 helicopters, including 390 in
2000, 328 in 2001 and 255 in
2002. Production rate
11 helicopters per week in 2003. Factory floor area 24,150m2.
Workforce totals 820. Company is ISO 9001 certified.
ROBINSON R22 BETA II
TYPE:
Two-seat helicopter.
PROGRAMME: Design began 1973; first flight 28 August 1975;
first flight of second R22 early 1977; FAA certification 16
March 1979; UK certification June 1981; Japanese
certification 18 November 2002; deliveries began October
1979; early versions were R22 (O-320-A2B engine; 199 built)
and R22HP (O-320-B2C; 151 built), both with 621kg max T-O
weight. R22 Alpha (O-320- B2C and 621kg MTOW) certified
October 1983 (further 151 built); R22 Beta certified 5
August 1985. Current Beta II introduced in 1995. More
powerful Textron Lycoming O-360 engine provides better
high-level hover performance and allows take-off power to be
sustained up to 2,285m. Previously optional, tinted
windscreen and door windows fitted as standard. Production
began at c/n 2571 in 1995.
CUSTOMERS: Total production more than 3,300 by end of 2002.
3,000th handed over 15 October 1999; deliveries in 1999
totalled 128, followed by 126 in 2000, 134 in 2001, and 107
in 2002.
COSTS:
US$170,000 for basic R22 Beta II (2003). Direct operating
cost US$27.30 per hour; total cost (500 hours annually)
US$76.61 per hour (2003).
DESIGN
FEATURES: Simple, pod-and-boom light helicopter; horizontal
stabiliser, starboard side only; vertical stabiliser above
and below boom; offset to starboard; tall rotor mast.
Horizontally mounted piston engine drives transmission
through multiple V belts and sprag-type overrunning clutch;
main and tail gearboxes use spiral bevel gears;
maintenance-free flexible couplings of proprietary
manufacture used in both main and tail rotor drives.
Two-blade semi-articulated main rotor, with tri-hinged
underslung rotor head to reduce blade flexing, rotor
vibration and control force feedback, and an elastic teeter
hinge stop to prevent blade-boom contact when starting or
stopping rotor in high winds; blade section NACA 63-015
(modified); two-blade tail rotor on port side; rotor brake
standard.
FLYING
CONTROLS: Manual. Removable dual controls standard.
STRUCTURE: All-metal bonded blades with stainless steel spar
and leading-edge, light alloy skin and light alloy honeycomb
filling; frame section of steel tube with light alloy
skinning; full monocoque light alloy tailboom.
LANDING GEAR: Welded steel tube and light alloy skid landing
gear, with energy-absorbing crosstubes.
POWER
PLANT: One Textron Lycoming O-360 flat-four engine, derated
to 97.5kW, mounted in the lower rear section of the main
fuselage, with cooling fan. Light alloy main fuel tank in
upper rear section of the fuselage on port side, usable
capacity 72.5 litres. Optional auxiliary fuel tank, capacity
39.75 litres. Oil capacity 5.7 litres. Transmission overhaul
interval 2,200 hours or 12 years.
ACCOMMODATION: Two seats side by side in enclosed cabin,
with inertia reel shoulder harness. Curved two-panel, tinted
windscreen. Removable door, with tinted window, on each
side. Baggage space beneath each seat. Cabin heated and
ventilated.
SYSTEMS: Electrical system, powered by 12V DC alternator,
includes navigation, panel and map lights, dual landing
lights, anti-collision light and battery.
AVIONICS: Comrns. Bendix/King KY 197A VHF com radio;
KT 76C transponder with Mode C altitude encoder; and NAT AA
80 intercom system with floor and hand switches. Options
include Garmin 430 GPS/COM/VOR/LOC/GS with 106A CDI,
replacing KY 197A; Pointer 3000-10 or 4000-10 (Canadian
spec) ELT; NAT AA 12 intercom controller; and David Clark
H10-13H or Bose Series X headsets.
Flight: Garmin 150XL, 250XL and 400 GPS optional.
Instrumentation: Standard equipment includes ASI; VSI;
rotor/engine dual tachometer; sensitive altimeter; magnetic
compass; digital OAT gauge; CHT gauge; oil temperature and
pressure gauges; ammeter; hours meter; manifold pressure
gauge; quartz clock; and warning lights for low voltage, low
oil pressure, low fuel, low rotor rpm and horn, main gearbox
temperature, main and tail rotor gearbox chips, starter
engaged, and rotor brake engaged. Optional instruments
include BFG (AIM) 1100 artificial horizon with/without slip
indicator; BFG (AIM) 205-1A DG; turn coordinator; PAI-700
vertical compass (replaces standard compass); United
Instruments IVSI (replaces standard VSI); LC-2 digital clock
(replaces standard clock); and Millibar altimeter.
EQUIPMENT: Standard equipment includes rotor brake; tinted
windscreen and windows; belly hardpoint; dual landing
lights; navigation, panel and map lights; anti-collision
light; ground handling wheels; rotor blade tiedowns; and
windscreen cover.
Optional equipment includes three-cylinder engine priming
system; RHC oil filter; cabin heater/defogger; metallic base
or trim exterior colours; and leather seats.