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MD HELICOPTERS
MD 600N
Type
Single-turboshaft light helicopter.
Programme
Stretched version of MD 520N. Announced as `concept', 8 November 1994;
prototype, then known as MD 630N (N630N, converted from MD 530F demonstrator),
first flight 22 November 1994, 138 days after project approval; public debut at
Heli-Expo in Las Vegas January 1995; production go-head 28 March 1995, at which
time designation changed to MD 600N; prototype first flown with production
standard engine and rotor system 6 November 1995; production prototype (N600RN)
first flown 15 December 1995, and became certification test vehicle leading to
FAR Pt 27 certification, but was destroyed in ground fire late May 1996
following emergency landing after rotor/tailboom strike during abrupt control
reversal tests. This resulted in changes to tailboom/rotor clearance; third
prototype flown 9 August 1996; further accidents in November 1996 and on
18 January 1997, both during autorotational descents, delayed certification and
first delivery, originally scheduled for 18 December 1996, to 15 May and 6 June
1997, respectively.
In July 1998, Boeing completed a year-long envelope expansion programme
for the MD 600N leading to FAA approval for operation at a density altitude of
2,135 m (7,000 ft) at a T-O weight of 1,746 kg (3,850 lb) and at a density
altitude of 1,220 m (4,000 ft) at a T-O weight of 1,860 kg (4,100 lb). Other
performance enhancements approved by the FAA included provision for doors-off
operation at speeds up to 115 kt (213 km/h; 132 mph), operation at temperatures
-40ºC/52ºC (-40ºF/126ºF), lifting up to 968 kg (2,134 lb) on the external cargo
hook, making slope landings up to 10º in any direction, operation with emergency
floats and for installation of a movable landing light and additional wire
strike protection on the fuselage. The MD 600N also completed HIRF trials at NAS
Patuxent River, Maryland.
Customers
Launch customer AirStar Helicopter of Arizona (two, of which first delivered 6
June 1997); Saab Helikopter AB of Sweden and Rotair Limited of Hong Kong ordered
one each in June 1995; other announced customers include Los Angeles County
Sheriff's Department Aero Bureau (three), Presta Services of France (one),
UND (University of North Dakota) Aerospace (one), West Virginia State Police
(one) and the US Border Patrol (45 of which eight received by end 1998).
Deliveries totaled 15 in 1997, 21 in 1998 and six in 1999; 42 in all.
Costs
US$1.2 million (1999). Direct operating cost US$230.83 per hour (1999).
Design Features
Stretched MD 520N airframe (less than 1 per cent new parts) by means of 0.76 m
(2 ft 6 in) plug aft of cockpit/cabin bulkhead and 0.71 m (2 ft 4 in) plug in
tailboom, combined with more powerful engine, uprated transmission and six-blade
main rotor. Cabin has flat floor to assist cargo handling, and will feature
quick-change interior configurations to suit multiple-use operators. Intended
for civil, utility, offshore, executive transport, medevac, aerial news
gathering, touring, law enforcement and other noise-sensitive operations; also
adaptable for armed scout, utility and other military missions.
Description generally as for MD 520N except as follows:
Power Plant
One 603 kW (808 shp) Rolls-Royce 250-C47M turboshaft, derated to 447 kW (600 shp)
for T-O and 395 kW (530 shp) maximum continuous, with FADEC. Transmission
manufactured from WE43A magnesium alloy for lower weight, greater strength and
enhanced corrosion resistance, rating 447 kW (600 shp). Fuel contained in two
crashworthy bladder tanks in lower fuselage, total capacity 435 litres (115 US
gallons; 95.8 Imp gallons).
Accommodation
Standard seating for eight, including pilot, in 3+3+2 configuration with centre
bench; alternative six-seat club
and coach layouts; utility with main cabin seats removed; EMS with accommodation
for pilot, one stretcher case and two medical attendants; or electronic news
gathering, with accommodation for pilot and passenger in cockpit and operator
with cabin and monitor in cabin. All facilitated by quick-release seat
mechanisms. Two removable centre-opening doors on each side of cabin; door to
cockpit on each side. Bubble `comfort' windows and sliding windows for cabin,
custom soundproofing and Integrated Flight Systems Inc air conditioning
optional.
Systems
Electrical system comprises 28 V 200 Ah starter-generator and 28 V 17 Ah Ni/Cd
battery. 24 V auxiliary power receptacle inside starboard cockpit door standard.
Avionics
To customer's choice, including VHF/UHF/FM/AM transceivers, GPS, transponder,
ELT, intercom, stereo tape system and PA system.
Equipment
Optional equipment includes dual controls, particle separator, heated pitot
tube, rotor brake, cargo hook, wire strike kit and emergency floats.
Dimensions, External
| Rotor diameter |
8.38 m (27 ft 6 in) |
| Rotor ground clearance |
2.65 m (8 ft 8½ in) |
| Length: overall, rotor turning |
10.79 m (35 ft 4½ in) |
| fuselage |
8.99 m (29 ft 6 in) |
| Fuselage width at cabin |
1.40 m (4 ft 7 in) |
| Height to top of rotor head: |
|
| standard skids |
2.65 m (8 ft 8½ in) |
| extended skids |
2.74 m (9 ft 0 in) |
| Height to top of fins: |
|
| standard skids |
2.68 m (8 ft 9½ in) |
| extended skids |
2.83 m (9 ft 3½ in) |
| Fuselage ground clearance, extended skids |
0.58 m (1 ft 10½ in) |
| Skid track |
2.47 m (8 ft 1¼ in) |
| Tailplane span, over fins |
2.01 m (6 ft 7¼ in) |
Dimensions, Internal
| Cabin, excl cockpit: |
|
| Length |
1.83 m (6 ft 0 in) |
| Width |
1.22 m (4 ft 0 in) |
| Height |
1.22 m (4 ft 0 in) |
Areas
| Rotor disc |
55.18 m2 (594.0 sq ft) |
Weights and Loadings (estimated)
| Weight empty, standard |
952 kg (2,100 lb) |
| Useful load: internal |
907 kg (2,000 lb) |
| external |
1,179 kg (2,600 lb) |
| Max hook capacity |
1,361 kg (3,000 lb) |
| Max T-O weight: internal load |
1,859 kg (4,100 lb) |
| slung load |
2,131 kg (4,700 lb) |
| Max disc loading: |
|
| internal load |
33.7 kg/m2 (6.90 lb/sq ft) |
| slung load |
38.6 kg/m2 (7.91 lb/sq ft) |
| Transmission loading at max T-O weight and
power: |
|
| internal load |
4.16 kg/kW (6.83 lb/shp) |
| slung load |
4.77 kg/kW (7.83 lb/shp) |
Performance
| Never-exceed speed (VNE) |
135 kt (250 km/h; 155 mph) |
| Max cruising speed, S/L to 1,525 m
(5,000 ft), ISA |
134 kt (248 km/h; 154 mph) |
| Max rate of climb at S/L, ISA |
411 m (1,350 ft)/min |
| Max operating altitude |
6,100 m (20,000 ft) |
| Hovering ceiling, ISA: IGE |
3,383 m (11,100 ft) |
| OGE |
1,829 m (6,000 ft) |
| Max range: |
|
| at S/L |
342 n miles (633 km; 393 miles) |
| at 1,525 m (5,000 ft), ISA |
382 n miles (707 km; 439 miles) |
| Endurance: at S/L |
3 h 36 min |
| at 1,525 m (5,000 ft) |
3 h 54 min |
MD 600N light helicopter (one Rolls-Royce 250 turboshaft)
(2000)
MD 600N eight-seat NOTAR helicopter (James Goulding/Jane's)
(1999)
| Height (m): |
2.65 |
| Hovering Ceiling (m): |
3383 |
| Length (m): |
10.79 |
| Max Level Speed (kts): |
134 |
| Max Range (nm): |
342 |
| Max Rate Climb (m/min): |
411 |
| Max T-O Weight (kg): |
1859 |
| Service Ceiling (m): |
6100 |
Source: 2001 Jane's Information Group