Schweizer 300C Helicopter

Transcription

S chwei z er 3 0 0 C T M H elicopter
T echnical I nformation
Schweizer 300CTM Helicopter
Piston-Powered Multi-Mission
Specifications
Performance
Standard day, sea level, maximum gross weight unless otherwise noted
Maximum speed (VNE) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95
Maximum cruise speed (VH) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86
Hover ceiling, In-Ground-Effect (1700 lb). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,800
Hover ceiling, Out-of-Ground-Effect (1700 lb) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8,600
Range (long range cruise* speed @ 4,000 feet) (no reserve)
- 32.5 gallon. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 191
- 64.0 gallon. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 375
kts . .
kts . .
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3,292
2,621
km/hr
km/hr
m
m
nm . . . . . . . 354 km
nm . . . . . . . 694 km
Weights
Maximum takeoff gross weight. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2,050 lb . . . . . . .
Empty weight, standard configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1100 lb . . . . . . .
Useful load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 950 lb . . . . . . .
930 kg
499 kg
431 kg
Dimensions
Fuselage length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22.19
Fuselage width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.25
Fuselage height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.17
Overall length (rotors turning). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30.83
Overall height (to top of tail rotor). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.72
Width (canopy) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.25
Main rotor diameter. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26.83
Tail rotor diameter. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.25
Main landing gear tread (fully compressed). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.54
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6.76
1.30
2.18
9.40
2.65
1.30
8.18
1.30
1.99
m
m
m
m
m
m
m
m
m
Accommodation
Normal cabin seating (training) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
Maximum certified cabin seating (utility). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
Cabin length. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.75 ft. . . . . . .
Cabin width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.92 ft. . . . . . .
1.45 m
1.50 m
Powerplants
Type . . . . . . . . . . . . . . .
Powerplant ratings (per engine,
- Takeoff (5-minute) . . . . . . .
- Maximum continuous . . . . .
. . . . .
standard
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. . . . .
day, sea
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. . . . . . . . . . . . . . . . . . . . . . . . Textron Lycoming HIO-360-D1A
level)
. . . . . . . . . . . . . . . . . . . . . . . . . . 190 shp . . . . . . 141 kw
. . . . . . . . . . . . . . . . . . . . . . . . . . 190 shp . . . . . . 141 kw
Fuel Capacity
Standard fuel capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32.5 US gal . . . 123.03 l
Extended range capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64.0 US gal . . . 242.27 I
1
Schweizer 300C Technical Information
SZR-004 February 2008 1473
Aircraft Dimensions
8.72 ft
(2.65 m)
6.54 ft
(1.99 m)
4.25 ft
(1.30 m)
15.29 ft
(4.66 m)
30.83 ft
(9.40 m)
13.42 ft
(4.09 m)
Anti-Submarine Warfare
(ASW)
Search and Rescue
(SAR)
6.88 ft
(2.10 m)
7.17 ft
(2.18 m)
6.17 ft
(1.88 m)
4.25 ft
(1.30 m)
8.25 ft
(2.51 m)
22.19 ft
(6.76 m)
Vertical Replenishment
(VERTREPS)
Anti-Surface Warfare
(ASuW)
2
Cockpit Layout
The 300CTM helicopter’s cockpit offers two different configurations. The standard right-hand Pilot-In-Command (PIC) flight control
configuration allows for comfortable seating of an instructor and student. With the optional left-hand PIC configuration, the right-hand
controls can be removed making it possible to seat a pilot and two passengers.
3
Cockpit Instrument Display Panel
Standard Panel
Intermediate Panel
Full Panel (Police/Military)
Small Profile Panel
4
Standard Equipment
Included in the aircraft basic certified empty weight. Based on 2007 data.
Airframe and Control Systems
• Three bladed fully articulated main rotor
• Elasometric main rotor dampers
• Dual flight controls, left hand pilot-in-command
• Collective friction control
• Cyclic friction control, two axis
• Electric cyclic trim, two axis
• Tubular skid-type landing gear
• Conical tail rotor teetering bearings
• Offset anti-torque pedals
• Booted Oleo landing gear dampers
• Heavy duty skid shoes
• Ground handling wheel brackets
• Fuselage jack/lift fittings
• Tie down kit
• White Glasurit Urethane paint
• Three piece chin skin with integral side fairings
Powerplant, Systems and Instruments
• 32.5 gallon fuel tank
• Airspeed indicator
• Altimeter
• Ammeter
• Cylinder head temperature indicator
• Dual engine/rotor tachometer
• Dual large oil coolers
• Engine oil pressure indicator
• Engine oil temperature indicator
• Exhaust collector
• Fuel pressure indicator
• Fuel quantity indicator
• Fuel shut-off valve
• Fuel flow oil filter, remotely mounted
• Low fuel warning light
• Lycoming HIO-360-D1A engine
• M/R transmission oil temp/pressure warning light
• Magnetic compass
• Manifold pressure gauge
• Oil cooling system with integral spin-off oil filter
• Oil filler/dipstick
• Outside air temperature gauge
• Running time (Hobbs) meter, panel mounted
• T/R transmission chip detector warning light
Electrical System
• 70 amp alternator
• Cabin accessory plug
• Circuit breaker protection
• Cyclic mounted radio frequency scrolling switch*, **
• External APU plug
• Lead acid battery
• Light weight, high torque starter
• Modular electric harness
• Night lights with strobe beacons
• Switchable hot mic intercom system
*Requires purchase of communication transceiver
**Not available w/cargo hook - optional grip available
Electrical System
• Adjustable ventilation system
• Three-seat cushioned interior
• Clear cabin door windows
• Floor/cabin carpet
• Circular air scoop vents on doors
• Lap belts and shoulder harnesses
• Tinted canopy windows
• Single latch doors
• Glove box
Note: Manufacturer reserves the right to modify this configuration by substituting comparable or better equipment.
5
Optional Equipment
Utility and Convenience Options
• Alternator, electrosystems 130 amp
• Cabin cover
• Cargo hook installation
• Cargo rack
• Cyclic grip, special
• Door openers, pneumatic
• Doors, triple latch
• Elastomeric teeter bearings
• Fire extinguisher, dry chemical
• Fire extinguisher, halon
• First aid kit
• Float kit, fixed
• Fuel system, auxiliary (64 gallon)
• Grease fitting, short shaft
• Ground handling wheels, flyable
• Heater, muff
• Heater, Paravion
• High stance landing gear with extra heavy duty gear
• Hobbs meter - landing gear contact switch
• Landing lights - two or three position
• Map case
• Muffler
• Skid shoes, extra heavy duty
• STAR system (start-up overspeed limiter, automatic rotor
engagement, low RPM warning device)
• Up-stack exhaust installation
• Up-stack exhaust with supertrap
• Windows, with sliding glass
Avionics Options
• ADF receiver, KR87 with KI227-00 indicator
• Attitude gyro
• Audio panel, KMA24H-71
• Blind encoder, ACK A-30
• Clock, electrical
• Clock, quartz (LC-2)
• Clock, quartz (LC-2E)
• Comm/GPS, Garmin GNC 420
• Comm/GPS, Garmin GNC 420A
• Comm/GPS, moving map, Garmin 250XL
• Comm transceiver, KY196A
• Comm transceiver, KY96A
• Compass-vertical card, overhead
• Compass system, KCS55A with HSI and heading transmitter
• Dimmer assembly, supplemental
• Directional gyro
• Emergency locater transmitter, EBC502
• Fan, avionics cooling
• Intercom foot switch
• Headset, David Clark H10-56
• Intercom, NATAA80
• Intercom, NATAA83 stereo
• Intercom, NATAA85
• Marker beacon, KR21
• Master avionics switch
• NAV/COMM, KX155-39 with 203 CDI
• NAV/COMM/GS, KX155-43 with KI209 CDI
• NAV/COMM/GS Garmin GPS, GNC 430 with Gi106A indicator
• Transponder, Garmin GTX320A, 327
• Turn coordinator
• Turn and slip indicator, Electric Gyro Corp.
• Vertical speed indicator, United 7000
6
Paint Options
BASF Glasurit exterior paint is used on all Schweizer 300CTM helicopters. It is one of the most technically advanced paints
available and is used by numerous premium automobile companies such as BMW and Mercedes. The Schweizer nine-step
paint process assures superior corrosion protection and a durable, yet highly attractive appearance. The 300C helicopter
is offered with an all white base coat as standard. Optional paint colors and trim schemes are available upon request.
Factory Standard Trim Styles
Type A
Type B
Type C
Type D
7
Safety and Crashworthiness
The 300CTM helicopter’s extraordinary safety record is the result of its exceptional flight safety and crashworthiness
characteristics. It is the beneficiary of more than thirty years and 20-million flight hours of commercial and military
flight experience. Like its predecessors, the 300C aircraft retains high student margins that even seasoned pilots will
appreciate.
Crashworthiness Features
• Energy absorption through plastic deformation
• Seating configuration places occupants far from the rotor impingement zone
• Unique geometry eliminating tailboom strikes
Articulated rotor system
Mast: rollover
protection
Proven dynamic
system
Rapid throttle
response: reserve
power
Engine and fuel system Outside of Enclosed structure
Low aft mounted engine
Dual strobe lights – visible from all angles
Rotor impingement outside
crew envelope
Energy absorption, 23 inches of strokes
Safety Features
• Rugged, reliable component design
• Stable handling characteristics
• Excellent safety record
• Rapid throttle response
8
Mission Performance
Speed vs. Range
425.0
Maximum Range
400.0
Range (nautical miles)
375.0
1700 lb (771 kg)
350.0
325.0
VH
2050 lb (930 kg)
300.0
275.0
250.0
200.0
175.0
30
40
50
60
70
Airspeed (kts)
80
90
100
Speed vs. Endurance
8.00
Endurance (hourr – no reserves)
Maximum Endurance
7.00
1700 lb (771 kg)
6.00
5.00
2050 lb (930 kg)
4.00
3.00
2.00
20
30
40
50
60
70
80
90
Airspeed (kts)
Note: Performance charts vary with individual aircraft configuration. Consult Flight Manual for actual flight operations.
9
100
Mission Performance
Hover Ceiling
In-Ground-Effect
Pressure altitude (feet in thousands)
14
12
1700 lb (771 kg)
10
8
1900 lb (862 kg)
6
2050 lb (930 kg)
4
2
ISA + 20°
ISA
0
0
10
20
30
40
50
60
70
Ambient temperature (°F)
80
90
100
90
100
Hover Ceiling
Out-of-Ground-Effect
14
12
10
1700 lb (771 kg)
8
6
1900 lb (862 kg)
4
2050 lb (930 kg)
ISA + 20°
2
ISA
0
0
10
20
30
40
50
60
70
Ambient temperature (°F)
10
80
Mission Performance
Vne vs. Density
Altitude
Density altitude (feet in thousands)
16
Note: Maximum cruise
speed is limited by
Vne at higher altitudes
1700 lb (771 kg)
14
1900 lb (862 kg)
12
10
8
2050 lb (930 kg)
6
4
ISA
2
0
30
40
50
60
70
80
(Kias)
90
100
110
120
Rate of Climb
16
14
12
10
8
1900 lb (862 kg)
2050 lb (930 kg)
1700 lb (771 kg)
6
4
Engine Critical Altitude
2
0
0
200
400
600
800
1000
Rate of climb (feet per minute)
11
1200
1400
Mission Performance
Height-Velocity
Diagram
500
Height abovesurface (feet)
450
Smooth hard surface avoid
operation in crosshatched areas
350
300
Recommended takeoff profile
250
200
150
30
40
50
60
70
80
90
100
110
120
(Kias)
Autorotation
Rate of Descent
2200
Height abovesurface (feet)
2000
1800
1600
1400
1200
20
30
40
50
(Kias)
12
60
70
Overhaul and Retirement Schedule
Components with Scheduled Overhaul Times
Main rotor transmission. . . . . . . . . . . . . . .
Tail rotor transmission. . . . . . . . . . . . . . . .
Engine. . . . . . . . . . . . . . . . . . . . . . . .
Belt drive system overhaul
- Upper ball bearings, belt drive frame assembly. .
- Lower ball bearings, belt drive frame assembly. .
- Idler pulley bearings, belt drive assembly. . . . .
Hours
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,000
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,000
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1,500 *
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,000
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1,800
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,000
*Aircraft must be operated in accordance with Lycoming Service Instruction SI-1009
Components with Mandatory Retirement Times
Main transmission ring gear carrier/coupling. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6,000
Main transmission pinion assembly. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6,000
Main rotor drive shaft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,200
Main rotor hub. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8,000
Main rotor mast . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13,590
Main rotor thrust bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,000
Main rotor pitch bearing shaft. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,600
Main rotor blade assembly. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5,500
Tailboom assembly. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4,200
Horizontal stabilizer assembly. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4,200
Vertical stabilizer assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20,540
Tail rotor drive shaft assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6,000
Tail rotor gearbox input shaft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8,600
Elastomeric main rotor damper. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6,000
Tail rotor blade assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9,000
Tail rotor blade retention straps. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5,100
Lower pulley coupling shaft. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6,000
Tailboom attaching strut assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,700
13
Estimated Direct Operating Costs
The following represents estimated average operating costs over a period of 5,000 hours (1,000 hours per year over
five years) in US dollars, assuming US costs predicted for fuel, shop labor rates, and parts costs.
Fuel and lubricants
Average fuel consumption (gallons per hour). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel cost per gallon (dollars/gal) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Cost of fuel (dollars/fh). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Cost of lubricants, 3% of fuel (dollars/fh). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11.80
5.31
62.66
1.88
Total costs for fuel and lubricants (dollars/fh). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64.54
Maintenance Labor
Shop labor rate (dollars/fh). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Direct maintenance (m/fh). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Indirect maintenance (m/fh). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Total maintenance (m/fh). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
55.00
0.38
0.12
0.50
Total cost for maintenance labor (dollars/fh) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27.50
Reserves
Engine overhaul. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16.80
Unscheduled replacement and on-condition parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.70
Scheduled maintenance/inspection materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.80
Major component overhaul @ TBO and replacement of retirement items . . . . . . . . . . . . . . . . . . . . . . . . . . 14.62
Total cost of reserves . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36.92
Total direct operating cost (dollars/fh). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 128.96
Note: The operating data provided herein are estimates only. Schweizer Aircraft endeavors to ensure that this data is current and meaningful for
operating cost evaluations. Schweizer Aircraft, however, does not warrant, and you should not rely upon, this data as defining the operating costs
or overhaul/retirement times for any particular 300C helicopter or its components
14
Notes
Notes
Elmira, NY 14845, USA
+1 (607) 739-3821
www.sacusa.com
SXR-004 1473 5C February 2008

Schweizer 300C Helicopter

Transcription

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