BUMBLEBEE HEAVY LIFT UTILITY ROTORCRAFT A MODIFIED AND HEAVY LIFT VERSION OF THE SW205 MEDIUM HELICOPTER
THIS IS PRESENTED BY:
SOUTHWEST FLORIDA AVIATION, INC.
5847 SE. HWY. 31 BLDG. 33 CARLSTROM & DORR FIELD ARCADIA, FLORIDA 34266
ALL INFORMATION INCLUDED IN THIS PRESENTATION IS THE SOLE PROPERTY OF JAMIE R. HILL. ANYONE WHO WISHES TO UTILIZE THIS INFORMATION FOR ANY PURPOSE MUST OBTAIN THE WRITTEN CONSENT FROM JAMIE R. HILL. IF THIS INFORMATION IS UTILIZED WITHOUT A WRITTEN CONSENT, LEGAL ACTIONS WILL BE INITIATED.
Southwest Florida Aviation, Inc. TABLE OF CONTENTS
| SECTION | PAGE | |
| I. | INTRO | 1-2 |
| II. | DESIGN OF THE ROTORCRAFT | 3 |
| III. | POWER PLANT | 4 |
| IV. | PERFORMANCE | 5 |
| V. | FURTHER MODIFICATIONS | 6 |
| VI. | COSTS | 7 |
| VII. | DELIVERY SCHEDULE | 8 |
| VIII. | ATTACHMENT A | 9-10 |
| IX. | ATTACHMENT B | 11-13 |
| X. | ATTACHMENT C | 14-15 |
| XI. | ATTACHMENT D | 16-20 |
| MISC. | PROTOTYPE PICTURES | 21-23 |
SECTION I
INTRO
SOUTHWEST FLORIDA AVIATION HAS DEVELOPED A HEAVY LIFT ROTORCRAFT THAT IS DERIVED FROM THE SW205. THE ROTORCRAFT WILL BE BASED ON A HIGHLY SUCCESSFUL AIRFRAME POWERTRAIN AND ENGINE BUT WOULD BE MODIFIED SO AS TO PROVIDE GREATLY ENHANCED PERFORMANCE, PAYLOAD, SPEED, AND MANEUVERABILITY. GREAT EMPHASIS WOULD BE PLACED ON PRODUCING A TECHNICALLY SOUND, RELATIVELY UNSOPHISTICATED, AND RUGGED ROTORCRAFT, WHICH WOULD ENJOY LOW OPERATING COSTS AND SIMPLE MAINTENANCE PROCEDURES. BY MODIFYING EXISTING AIRFRAMES AND USING TOTALLY REMANUFACTURED ENGINES AND COMPONENTS, IT IS ANTICIPATED THAT THE COST OF PRODUCTION OF THIS ROTORCRAFT WOULD BE ABOUT ONE-THIRD THAT OF THE BELL'S ROTORCRAFT. THE RELATIVELY LOW COST, RELIABILITY, AND PERFORMANCE OF THE ROTORCRAFT SHOULD ENSURE A SUBSTANTIAL WORLDWIDE MARKET. IN THE FOLLOWING PAGES, THE PRESENTATION, AS WELL AS THE DETAILS OF THE ROTORCRAFT WILL BE EXAMINED IN DEPTH. THIS VENTURE WOULD BE A SATISFYING COMBINATION OF AMERICAN TECHNOLOGY AND FOREIGN CRAFTSMANSHIP. IT WOULD PROVIDE AN OPPORTUNITY TO ESTABLISH A PROFITABLE AVIATION INDUSTRY OUTSIDE OF THE UNITED STATES WITH CONSIDERABLE EXPORT EARNINGS.
SECTION II
DESIGN OF THE ROTORCRAFT
THE ROTORCRAFT WOULD BE BUILT UP FROM A SKELETON OF AN EXISTING HELICOPTER AIRFRAME (ATTACHMENT A). IT WOULD USE THE SAME ENGINE, TRANSMISSION, AND OTHER DYNAMIC COMPONENTS TO ENSURE RELIABILITY AND EASE OF MAINTENANCE.
EXTENSIVE AIRFRAME MODIFICATIONS WOULD REDUCE THE TOTAL WIDTH OF THE FUSELAGE TO ABOUT 3' 8", MODIFY THE COCKPIT TO SINGLE OR DUAL PILOT CONFIGURATION, SLIGHTLY SHORTEN THE MACHINE OVERALL, GIVE IT A MORE AERODYNAMIC NOSE AND PROVIDE FOR THE INSTALLATION OF WINGS (ATTACHMENT B). THE DRAWINGS FOR THE PROTOTYPE HELICOPTER ARE LOCATED IN ATTACHMENT C.
SECTION III
POWERPLANT
THE HIGH-PERFORMANCE HONEYWELL T53-L-703 ENGINE WOULD BE FITTED TO THE ROTORCRAFT IN ITS ORIGINAL CONFIGURATION. THIS IS CONSIDERED TO BE ADEQUATE GIVEN THE VERY CONSIDERABLE REDUCTION IN WEIGHT ACHIEVED BY CUTTING THE CREW FROM FOUR MEN TO ONE, AND THE REDUCTION OF ABOUT 1,000 LBS. FROM THE FUSELAGE AND AIRFRAME.
SECTION IV
PERFORMANCE
BY SUBSTANTIALLY MODIFYING THE ORIGINAL DESIGN WITH THE ADDITION OF STUB WINGS AND REDUCTION OF THE FRONTAL AREA OF THE HELICOPTER, THE OVERALL WEIGHT OF THE ROTORCRAFT WILL BE LIGHTENED. IT IS EXPECTED THAT PERFORMANCE FIGURES WILL DRAMATICALLY INCREASE, ESPECIALLY IN THE REALM OF ACCELERATION, CLIMB RATES, CRUISE SPEED, AND TOP SPEED. THE AIRFOIL CROSS-SECTION OF THE STUB WING WILL BE DESIGNED TO MAXIMIZE LIFT IN THIS FLIGHT REGIME. IT IS EXPECTED THAT THE ACTUAL LENGTH OF THE WINGS WILL BE LONGER THAN MOST CURRENTLY IN VOGUE WITH U.S. STUB WINGS, SO AS TO INCREASE LIFT APPRECIABLY.
SECTION V
FURTHER MODIFICATIONS
IT WOULD BE HIGHLY DESIRABLE TO EVENTUALLY PRODUCE A ROTORCRAFT WITH A PAIR OF HONEYWELL T53-L-13B OR HONEYWELL T53-L-703 ENGINES MARRIED TO THE SWFA PATENTED TANDEM TRANSMISSION WHICH WOULD PROVIDE A DRAMATIC INCREASE IN LIFTING POWER AND RELIABILITY. AN INTERIM MODIFICATION WOULD BE THE INSTALLATION OF THE LYCOMING T53-L-703 ENGINE WITH 1,800 SHP RATHER THAN THE STANDARD DASH 13 WITH 1,400 SHP. ANOTHER USEFUL MODIFICATION WOULD BE THE REPLACEMENT OF THE SKIDS WITH RETRACTABLE, SEMI-RETRACTABLE LANDING GEAR, OR FIXED WHEELS. SUCH MODIFICATION WOULD ALLOW EASIER GROUND MANEUVERING, LESS DRAG AIRBORNE, AND THE ABILITY TO TAKE OFF WITH HEAVIER LOADS THAN WITH SKIDS AS THE ROTORCRAFT COULD BE ROLLED OFF THE GROUND. THE INITIAL ROTORCRAFT WILL BE SINGLE-PILOTED, BUT A GROWTH VERSION WITH A CO-PILOT, MOUNTED IN TANDEM, WOULD BE DESIRABLE AS THE ROTORCRAFT GROWS FROM A DAYTIME VFR ROTORCRAFT TO ONE WITH ALL-WEATHER CAPABILITIES (IFR).
SECTION VI
COSTS
IF CONSTRUCTED IN THE USA, THE ROTORCRAFT WOULD COST APPROXIMATELY $6.8 MILLION USD, COMPLETE WITH SPECIFICATIONS AS NOTED IN ATTACHMENT D.
OTHER VERSIONS, INCLUDING TWIN-ENGINE MODELS WITH DUAL PILOT AND OTHER MODIFICATIONS, WILL BE PRICED ACCORDING TO COSTS AND COMPLEXITY. IN ANY CASE, THE COSTS WILL BE MUCH LOWER THAN COMPARABLE FOREIGN-MANUFACTURED ROTORCRAFT.
SECTION VII
DELIVERY SCHEDULE
THE DELIVERY SCHEDULE OF THE ROTORCRAFT IS COMPLETELY DEPENDENT ON THE REQUIREMENTS OF THE CUSTOMER. ON AN URGENT BASIS, THESE HELICOPTERS COULD BE PRODUCED IN A RELATIVELY SHORT TIME SINCE THE ENGINEERING AND DESIGN WORK HAS BEEN COMPLETED, AND THEY ARE BASED ON A WELL-ESTABLISHED AIRFRAME AND POWERPLANT.
SECTION VIII
ATTACHMENT A
SECTION IX
ATTACHMENT B
SECTION X
ATTACHMENT C
SECTION XI
ATTACHMENT D
HELICOPTER DIMENSION
| LENGTH | 57 FEET 1 INCH |
| HEIGHT | 13.4 FEET |
| WIDTH AT ELEVATORS | 7 FEET |
| WIDTH FUSELAGE | 3 FEET 8 INCHES |
| ROTOR SPAN | 48 FEET |
| WEIGHT (empty) approximately | 5,000 POUNDS |
PERFORMANCE
| VNE | 165 KNOTS |
| CRUISE | 150 KNOTS |
| GROSS WT. | 11,200 POUNDS |
| PAYLOAD | 6,200 POUNDS PLUS |
| RATE OF CLIMB (approximate) | 3,000 FEET PER MINUTE |
Performance specifications will be verified and adjusted by test flight.
STANDARD EQUIPMENT
AIRFRAME
Aluminum alloy fuselage
Fresh-air ventilators with adjustable outlets
Bleed-air heater and defroster with air noise suppression
Tinted overhead windows
Swing out jettisonable doors
Swing out panels for extended access to aft cabin (2)
Fixed step for entry to forward seats
Skid type landing gear
Mooring and jacking fittings (4)
External attachment fittings (12)
Semi-monocoque tailboom and vertical fin
Elevator (synchronized with fore and aft cyclic control)
Tail skid (tail rotor guard)
POWER PLANT
Lycoming T53-L-703 engine (1,800 SHP gas turbine) (T53-L-13B is an alternate engine)
Starter (integral with generator) Governor (automatic)
Power turbine control actuator
Ice detector with automatic anti-ice Magnetic chip detector
Fuel system (220 U.S. gal. capacity, 215 U.S. gal. usable)
Pumps (submerged in tanks and on the engine) Fuel filter assembly
Oil tank (3 U.S. gal. capacity) Oil cooler (turbine type)
Fire detection system RPM warning system Hinged cowling
TRANSMISSION DRIVE SYSTEM
Transmission (1,250 SBP T.O., 1,100 SBP Continuous)
Transmission oil cooler
Hydraulic pump for controls
Freewheeling unit (between the engine and main transmission)
ROTOR AND CONTROLS
Semi-rigid type main rotor
Semi-rigid, two-bladed all-metal tail rotor Stabilizer bar and dampers
All controls hydraulically boosted
Forced system on cyclic and directional controls RPM governor selector control
INSTRUMENTATION
Free air temps indicator
Altimeter (pressure)
Clock (8 day)
Magnetic compass
Airspeed indicator
Exhaust gas temperature indicator
Gas producer tachometer indicator
Torque meter indicator
D.C. voltmeter
A.C. voltmeter
Load meter
Engine out
Rate of climb indicator
Turn and slip indicator
Attitude indicator (3 axis Gyro 5 inch)
Dual tachometer (rotor and engine)
Engine oil-temperature indicator
Engine oil-pressure indicator
Master caution indicator
RPM warning light
Fuel pressure indicator
Transmission oil-temperature indicator
Transmission oil-pressure indicator
CAUTION PANEL
Master Caution System - When limits are approached, warning lights (with appropriate wording) draw attention to:
Engine oil pressure
Engine icing
Engine ice detector
Engine de-ice on
Left fuel boost
Right fuel boost
Engine fuel pump
20-minute fuel
Fuel filter
Emergency governor
Oil filter
Transmission oil pressure
Transmission oil hot
Hydraulic pressure
Instant inverter
D.C. generator
Spares
ELECTRICAL
Generator (30-volt, 300 ampere D.C. starter-generator)
Inverters (2) (Class B, 250-volt ampere, 3 phase)
Nickel-cadmium battery (40-amp hours)
Voltage regulator
Navigation lights
Landing light - retractable
Anti-collision lights
Searchlight - controllable
Cockpit light
External power receptacle
MISCELLANEOUS
Ground handling wheels
Turbine air inlet covers
Tailpipe cover
Pitot tube cover
Tail rotor tie-down strap
Rotor tie-down assembly
Maintenance and Overhaul manual
Parts Catalog
Flight Manual
Engine Logbook
This aircraft will be equipped with an engine exhaust and an infrared suppression kit.
PROTOTYPE PICTURE
