MH-47E Chinook Specifications
|
Description
|
Twin-turbine, tandem-rotor, heavy-lift, special-mission helicopter
|
|
Program status
|
Low-rate initial production
|
|
Customer
|
U.S. Special Operations Command (USSOCOM)
|
|
Operators
|
160th Special Operations Aviation Regiment (SOAR) (A), Fort Campbell,
Ky.,and Savannah, Ga., and 1/245th Aviation (SO) (A) Oklahoma Army National
Guard (OKARNG), Lexington, Okla.
|
|
Missions
|
Long-range, covert, infiltration/exfiltration of special-operations
forces
|
|
Program Managers
|
|
Boeing
|
Ray Brosius
|
|
Customer
|
U.S. Special Operations Command
|
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Program Requirements
|
|
|
Total aircraft
|
26 (including 1 prototype)
|
|
Production deliveries
|
|
Number delivered
|
26 throughout May 1995
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Production funding
|
Definitive $350 million contract completed - November 1992
|
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Milestones
|
|
Program start
|
December 1987
|
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Prototype 1st flight
|
May 31, 1990
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Prototype delivery
|
May 10, 1991
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Production 1st del.
|
September 1993
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U.S. Army MH-47E Special Operations Chinook
| ENGINES |
| Manufacturer |
Textron Lycoming |
| Model |
Two T55-L-714 |
| Max shp (kw) |
4,867 |
(3,629) |
| Cont shp (kw) |
4,168 |
(3,108) |
| TRANSMISSIONS
|
| Max shp (kw) |
7,500 |
(5,593) |
| ROTOR SYSTEM |
| Blades per hub |
|
3 |
| Construction |
|
fiberglass |
| Speed, rpm |
|
225 |
| Diameter, ft(m) |
60.0 |
(18.29) |
| Disc area ft2 (m2) |
2,827.5 |
(262.67) |
| Blade folding |
|
manual |
| PERFORMANCE [at 50,000 lbs (22,680 kg)] |
| SL cruise, kts (km/h) |
140 |
(259) |
| Rate of climb, fpm (m/m) |
1,841 |
(561) |
| Service ceiling, ft (m) |
10,150 |
(3,094) |
| HIGE, ft (m) |
9,800 |
(2,987) |
| HIGE, ISA + 20 degrees C, ft (m) |
7,900 |
(2,408) |
| HOGE, ft (m) |
5,500 |
(1,676) |
| HOGE, ISA + 20 degrees C, ft (m) |
3,300 |
(1,006) |
| Range, SL and ISA, nm (km) |
613 |
(1,136) |
| ACCOMMODATION |
| Cockpit -- crew seats |
|
2 |
| Cabin -- troop seats, litters |
|
44 |
| DIMENSIONS, EXTERNAL |
| Length, fuselage, ft (m) |
52.08 |
(15.87) |
| Length, rotors turning, ft (m) |
99.00 |
(30.18) |
| Dist. between rotor centers, ft (m) |
39.17 |
(11.94) |
| Wheel base, ft (m) |
25.83 |
(7.87) |
| Width, landing gear, ft (m) |
11.92 |
(3.63) |
| Width, fuselage, ft (m) |
15.75 |
(4.80) |
| Height, to top of aft hub, ft (m) 16.13 |
18.33 |
(5.59) |
| Ground clearance, aft rotor, ft (m) |
16.08 |
(4.90) |
| Ground clearance, fuselage, ft (m) |
1.60 |
(0.49) |
| DIMENSIONS, INTERNAL |
| Length, max, ft (m) |
30.50 |
(9.30) |
| Width, max, ft (m) |
7.50 |
(2.29) |
| Height, max, ft (m) |
6.50 |
(1.98) |
| WEIGHTS |
| Max gross, lbs (kg) |
54,000 |
(24,494) |
| Empty, lbs (kg) |
26,918 |
(12,210) |
| Useful load, lbs (kg) |
27,082 |
(12,284) |
| Forward and aft hooks, lbs (kg) |
17,000 |
(7,711) |
| Center cargo hook, lbs (kg) |
26,000 |
(11,794) |
| FUEL CAPACITY |
| Internal, standard, gals (liters) |
2,068 |
(7,828) |
| 3 internal aux tanks, each, gals (liters) |
800 |
(3,028) |
