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MD HELICOPTERS
US Coast Guard designation: MH-90 Enforcer
also called the MD EXPLORER
Type
Eight-seat twin-engined light helicopter.
Programme
Initially known as MDX, then MD 900; McDonnell Douglas design; announced
February 1988; launched January 1989; Hawker de Havilland of Australia designed
and manufactures airframe; Canadian Marconi tested initial version of integrated
instrumentation display system (IIDS) early 1992; Kawasaki completed 50 hour
test of transmission early 1992. Other partners include Aim Aviation (interior),
IAI (cowling and seats) and Lucas Aerospace (actuators). Ten prototypes and
trials aircraft, of which seven (Nos. 1, 3-7 and 9) for static tests; first
flight (No.2/N900MD) 18 December 1992, followed by No.8/N900MH 17 September 1993
and No.10/N9208V 16 December 1993; first production/demonstrator Explorer
(No.11/N92011) flown 3 August 1994. FAA certification 2 December 1994; first
delivery 16 December 1994; JAA certification July 1996; FAA certification for
single-pilot IFR operation achieved January 1997.
Current Versions
MD Explorer: Initial civilian utility version, as described.
Details apply to civilian version except where indicated.
MD Enhanced Explorer: Improved version, announced September 1996;
originally MD 902. Main features include Pratt & Whitney Canada PW206E engines
with increased OEI ratings; transmission approved for dry running for 30 minutes
at 50 per cent power; improved engine air inlets, NOTAR inlet design and engine
fire suppression system, and more powerful stabiliser control system, resulting
in 7 per cent increase in range, 4 per cent increase in endurance and 113 kg
(250 lb) increase in payload over Explorer. First flight (N9224U; 42nd
production Explorer) 5 September 1997. FAA certification to Category A
performance standards (including continued take-off with one failed engine) and
single-pilot IFR operation achieved 11 February 1998; JAA certification for
Category A performance achieved July 1998. Retrofit kits will be available to
convert Explorers to Category A standard. First Enhanced Explorer delivery (45th
production) in May 1998 to Tomen Aerospace of Japan.
MH-90 Enforcer: Beginning March 1999, under a programme
code-named Operation New Frontier, the US Coast Guard used two leased MD 900
Explorers for anti-drug smuggling operations from the Coast Guard cutters
Gallatin and Seneca. Armed with a pintle-mounted M240 7.62 mm minigun at the
door station, the Explorers, designated MH-90 Enforcer by the USCG, intercepted
four high-speed smuggling vessels, resulting in the capture of 13 smugglers and
confiscation of six tons of marijuana and cocaine. In September 1999 the MD900s
were exchanged for two leased MD 902 Enhanced Explorers. The USCG has a
requirement for eight to 12 helicopters in the Explorer class.
Combat Explorer: Displayed at Paris Air Show, June 1995;
demonstrator N9015P (No.15), an MD 900 variant. Can be configured for utility,
medevac or combat missions; armament and mission equipment may include seven- or
19-tube 70 mm rocket pods, 0.50 calibre machine gun pods, chin-mounted FLIR
night pilotage system and roof-mounted NightHawk surveillance and targeting
systems. Combat weight 3,130 kg (6,900 lb); two P&WC PW206A engines. No
customers announced by January 2000, but N9015P became one of initial two MH-90s
(with third prototype, N9208V.
Customers
Market estimated at 800 to 1,000 in first decade; first
delivery 16 December 1994 to Petroleum Helicopters Inc (PHI) which ordered five;
second delivery (N901CF) December 1994 to Rocky Mountain Helicopters for EMS
duties with affiliate Care Flight unit of Regional Emergency Medical Services
Authority (REMSA) in Reno, Nevada. Total of two delivered in 1994, 12 in 1995,
15 in 1996, one in 1997, four in 1998 and 11 in 1999; cumulative total of 45
announced deliveries, although 58th production aircraft was registered in
November 1999. Other disclosed customers include Aero Asahi of Japan (15, of
which the first, JA6757, was delivered in July 1995 and five in service by
October 1999), Allegheny General Hospital, Pittsburgh,
Pennsylvania (four, delivered mid-1996), Belgian government (two delivered in
1996, with one option, in law enforcement configuration for Rijkswacht/Gendarmerie),
German State Police (two, delivered in August and September 1999), IBCOL Group
of Germany (one, delivered in early 1996, operated by Air Lloyd of Bonn), Idaho
Helicopters Inc/Life Flight (one, for EMS service at St Alphonsus Regional
Medical Center, Boise, Idaho), Japan Digital Laboratory (one), Luxembourg Air
Rescue (one, in EMS configuration), Mexican Navy (eight for SAR duties, of which
first two delivered in 1999), Police Aviation Services UK (10, of which initial
delivery was made in June 1998), Televisa of Mexico (one), Japanese distributor
Tomen (two), UND (University of North Dakota) Aerospace (one).
Costs
US$2.6 million (1999); direct operating cost US$368.85 (1999) per hour.
Design Features
NOTAR anti-torque system; all-composites five-blade rotor of tapered thickness
with parabolic swept outer tip with bearingless flexbeam retention and pitch
case; tuned fixed rotor mast and mounting truss for vibration reduction;
replaceable rotor tips; maximum rotor speed 392 rpm; modified A-frame
construction from rotor mounting to landing skids protects passenger cabin;
energy-absorbing seats absorb 20 g vertically and 16 g fore and aft; onboard
health monitoring, exceedance recording and blade track/balance.
Flying Controls
NOTAR tailboom (see details under MD 520N); mechanical engine control from
collective pitch lever is back-up for electronic FADEC. Automatic stabilisation
and autopilot available for IFR operation.
Structure
Cockpit, cabin and tail largely carbon fibre; top fairings Kevlar composites; no
magnesium; lightning strike protection embedded in composites skin. Transmission
overhaul life 5,000 hours; glass fibre blades have titanium leading-edge
abrasion strip and are attached to bearingless hub by carbon fibre encased glass
fibre flexbeams; rotor blades and hub on condition.
Landing Gear
Fixed skids with replaceable abrasion pads; emergency floats optional.
Power Plant
Two Pratt & Whitney Canada PW206E turboshafts with FADEC, each rated at 463 kW
(621 shp) for 5 minutes for T-O, 489 kW (656 shp) for 2½ minutes OEI and 410 kW
(550 shp) maximum continuous. Transmission rating 820 kW (1,100 shp) for T-O,
746 kW (1,000 shp) maximum continuous, 507 kW (680 shp) for 2½ minutes OEI and
462 kW (620 shp) maximum continuous OEI.
Fuel contained in single tank under passenger cabin, usable capacity 602
litres (159 US gallons; 132 Imp gallons); optional 818 litres (216 US gallons;
180 Imp gallons); single-point refuelling; self-sealing fuel lines.
Accommodation
Two pilots or pilot/passenger in front on energy-absorbing adjustable crew seats
with five-point shoulder harnesses/seat belts; six passengers in club-type
energy-absorbing seating with three-point restraints; rear baggage compartment
accessible through rear door; cabin can accept long loads reaching from flight
deck to rear door; hinged, jettisonable door to cockpit on each side; sliding
door to cabin on each side.
Systems
Hydraulic system, operating pressure 34.475 bars (500 lb/sq in).
Avionics
Full IFR capability for single- or two-pilot operation.
Comms: Two headsets standard. Honeywell Silver Crown VHF transceiver,
audio control panel, ELT, cockpit voice recorder and Wulfsberg Flexcomm II
optional.
Radar: Honeywell RDR 2000 vertical profile colour weather radar optional
with IFR package.
Flight: Optional equipment includes Honeywell Silver Crown VOR/ILS, HSI,
ADF, DME, marker beacon receiver, radar altimeter, Loran C and KLN 90B GPS.
Coupled three-axis autopilot optional.
Instrumentation: Single- or two-pilot instrument panels incorporate
Canadian Marconi integrated instrumentation display system (IIDS) with
high-resolution sunlight-readable LCD screen displaying engine and system
information including engine condition trend monitoring, exceedance recording,
caution annunciators, onboard track and balance of rotor and fan, weight on
cargo hook, outside air temperature, digital clock, running time meter and
RS-232 download modem interface for personal computer. Other standard
instrumentation includes airspeed indicator, encoding altimeter, vertical speed
indicator, turn and slip indicator, wet compass and clock. EFIS 40 electronic
flight information system and parallel IIDS monitor for long-line hook
operations from left seat optional.
Mission: Law enforcement panel with space for FLIR screen available.
Avionics and equipment options for law enforcement conversions are described in
Jane's Aircraft Upgrades.
Equipment
Standard equipment includes magnetic chip detectors on engines, tiedown
fittings, flush-mounted cargo tiedowns, rotor blade tiedowns, right side
passenger step, utility beige colour carpet, trim, wall and ceiling panels,
soundproofing, tinted windows, map case, recessed hover and approach light,
wander and white dome lights in cockpit, white dome light in cabin, utility
light in baggage compartment, single 28 V DC power outlet each in cockpit and
cabin, single colour external paint with two-colour accent stripes, FOD covers,
pitot tube cover and cockpit fire extinguisher.
Optional equipment includes dual controls, heated pitot head, rotor
brake, pilot-activated engine fire extinguisher, engine air particle separator,
maintenance hand pump for hydraulics, external cargo hook with 1,361 kg (3,000
lb) capacity 272 kg (600 lb) personnel hoist, wire strike kit, emergency floats
for skids, retractable landing light, port side cabin step, landing gear and
rotor fairing canopy cover, heater/defogger, vapour-cycle air conditioner,
upgraded soundproofing, passenger service unit with air gaspers and reading
lights, window reveal panels, matching close-out panel for aft baggage area,
upgraded passenger seats, smoke detector in baggage compartment, jack-point
fittings and ground handling wheels.
Dimensions, External
| Rotor diameter |
10.31 m (33 ft 10 in) |
| Length: overall, rotor turning |
11.83 m (38 ft 10 in) |
| fuselage |
9.85 m (32 ft 4 in) |
| Fuselage width at cabin |
1.63 m (5 ft 4 in) |
| Height: to top of rotor head |
3.66 m (12 ft 0 in) |
| to top of fins |
2.79 m (9 ft 2 in) |
| Min fuselage ground clearance |
0.38 m (1 ft 3 in) |
| Tailplane span |
2.84 m (9 ft 4 in) |
| Skid track |
2.24 m (7 ft 4 in) |
| Cabin door width |
1.27 m (4 ft 2 in) |
Dimensions, Internal
| Cabin: Length overall, incl baggage
compartment |
3.93 m (12 ft 10½ in) |
| Length, passenger compartment only |
1.91 m (6 ft 3 in) |
| Max height |
1.24 m (4 ft 1 in) |
| Max width |
1.45 m (4 ft 9 in) |
| Volume |
4.9 m3 (173 cu ft) |
| Baggage (if closed off) |
1.39 m3 (49 cu ft) |
Areas
| Rotor disc |
83.52 m2 (899.0 sq ft) |
Weights and Loadings
| Weight empty, standard configuration |
1,531 kg (3,375 lb) |
| Standard fuel load |
489 kg (1,078 lb) |
| Max internal payload |
1,292 kg (2,848 lb) |
| Max slung load |
1,361 kg (3,000 lb) |
| Max T-O weight: internal load |
2,835 kg (6,250 lb) |
| external load |
3,129 kg (6,900 lb) |
| Max disc loading: |
|
| internal load |
33.9 kg/m2 (6.95 lb/sq ft) |
| external load |
37.5 kg/m2 (7.68 lb/sq ft) |
| Transmission loading at max T-O weight and
power: |
|
| internal load |
3.80 kg/kW (6.25 lb/shp) |
| external load |
3.82 kg/kW (6.27 lb/shp) |
Performance (at max T-O weight, ISA, except where indicated)
| Never-exceed speed (VNE) at S/L, ISA |
140 kt (259 km/h; 161 mph) |
| Max cruising speed at S/L, 38ºC (100ºF)
|
134 kt (248 km/h; 154 mph) |
| Max rate of climb at S/L |
579 m (1,900 ft)/min |
| Vertical rate of climb at S/L |
411 m (1,350 ft)/min |
| Rate of climb at S/L, OEI |
305 m (1,000 ft)/min |
| Service ceiling: both engines |
5,335 m (17,500 ft) |
| OEI |
3,200 m (10,500 ft) |
| Hovering ceiling: |
|
| IGE, ISA |
3,353 m (11,000 ft) |
| IGE, ISA + 20ºC |
2,042 m (6,700 ft) |
| OGE, ISA |
2,743 m (9,000 ft) |
| OGE, ISA + 20ºC |
1,433 m (4,700 ft) |
| Hovering ceiling, OEI: |
|
| IGE, ISA at 87% max T-O weight |
1,220 m (4,000 ft) |
| Max range: at S/L |
257 n miles (476 km; 295 miles) |
| at 1,525 m (5,000 ft), ISA |
293 n miles (542 km; 337 miles) |
| Max endurance: at S/L |
2 h 54 min |
| at 1,525 m (5,000 ft), ISA |
3 h 12 min |
Operational Noise Levels
| T-O |
84.1 EPNdB |
| Approach |
88.9 EPNdB |
| Flyover |
83.1 EPNdB |
MD Explorer eight-seat commercial helicopter (Mike Keep/Jane's)
Two MD Explorers operated by the US Coast Guard during 1999
(2000)
Executive interior of MD Explorer
Dual-pilot instrument panels of MD Explorer
MD Explorer of Police Aviation Services/Dorset & Wiltshire constabulary in the
UK
(2000)
| Height (m): |
3.66 |
| Hovering Ceiling (m): |
3353 |
| Length (m): |
11.83 |
| Max Level Speed (kts): |
134 |
| Max Range (nm): |
257 |
| Max Rate Climb (m/min): |
579 |
| Max T-O Weight (kg): |
2835 |
| Service Ceiling (m): |
5335 |
Source: 2001 Jane's Information Group