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de Havilland
DHC-5 Buffalo |
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DESIGN PHILOSOPHY:
Based on U.S. Army requirements for a turbine powered STOL aircraft with a larger cabin, greater payload weight capability,
higher speed and longer ferry range than the Caribou. This was the first DHC design to use spoilers to augment the ailerons for lateral control and to dump lift on landing and during braking in an aborted takeoff. The
design and tooling drew heavily on Caribou experience.Three models have been produced: DHC-5/CV-7A: 4 produced and delivered to the U. S. Army. Two of these served for a trial period in Vietnam
DHC-5A:
55 produced - Canadian Forces (15), Brazilian Air Force (24), Peruvian Air Force (16)
DHC-5B: A proposed version using the G.E. T64-P4C engine (never produced)
DHC-5C:
A proposed version for the Indian Air Force using the R.R. Dart 12 engine (never
produced)
DHC-5D: The last production version (S/N 60 and subsequent)The -5D introduced the concept of higher operating weights and increased payload when operating in a "Transport" role (firm, smooth
runways, 2.5g maneuver load factor, restricted flap settings, 10 ft/second limit rate of descent at landing touchdown) in addition to the "Assault" role capabilities of the earlier versions.
"Beta" propellers were introduced on S/N 79 and are standard on subsequent aircraft. The main differences between the models produced are summarized below: |
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MODEL |
DHC-5 |
DHC-5A |
DHC-5D |
ENGINES |
T64-10 |
CT64-820-1* |
CT64-820-4 |
MAX. POWER
(S/L, ISA, Static): |
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Takeoff (5 min) |
2,650 SHP |
2,825 SHP |
3,133 SHP |
Military (30 min) |
2,435 SHP |
2,710 SHP |
2,785 SHP |
Normal (Max. Cont.) |
1,850 SHP |
2,345 SHP |
2,745 SHP |
APU - Manufacturer |
Williams |
Williams |
Solar (Turbomach) |
APU -- Starting |
Hydraulic |
Electric |
Electric |
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*
Canadian Forces' engines have been upgraded to the CT64-820-3 standard (improved thermal performance and mechanical modifications) |
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DHC-5 BUFFALO Models |
MAX. WEIGHTS (lb) |
MODEL |
DHC-5 |
DHC-5A |
DHC-5D |
ROLE |
ASSAULT |
ASSAULT |
ASSAULT |
TRANSPORT |
Takeoff |
38,000 |
41,000 |
41,000 |
49,200 |
Landing |
36,500 |
39,100 |
39,100 |
46,500 |
Zero Fuel |
34,000 |
37,000 |
37,000 |
43,500 |
O.W.E. (Typical) |
23,400 |
24,500 |
25,052 |
25,052 |
Payload |
10,600 |
12,500 |
11,948 |
18,000 |
LANDING: |
Surface |
Selected, Unprepared |
Firm, Smooth |
Tire Pressure (psi) |
45 |
45 |
45 |
60 |
Limit Touchdown R of D (ft/sec) |
13 |
13 |
13 |
10 |
MANOEUVER: |
Limit Load Factor |
3 |
3 |
3 |
2.5 |
Max Oper. Airspeed (kCAS) |
230 |
230 |
230 |
200 |
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PROPULSION |
Engines: |
2 x GE CT648204 (Turboprop) |
Shaft Horsepower: |
3,133 |
Propellers: |
Hamilton Standard 63E6025, 3Bladed, Feathering and Reversible |
EXTERNAL DIMENSIONS |
Wing Span |
96 ft 0 in |
Length Overall |
79 ft 0 in |
Height |
28 ft 9 in |
Tailplane Span |
32 ft 0 in |
Wheel Track |
30 ft 6 in |
Wheel Base |
27ft 10 in |
Wing Area |
945.0 sq ft |
Aileron Area |
39.0 sq ft |
Flap Area |
280.0 sq ft |
Fin Area |
92.0 sq ft |
Rudder Area |
60.0 sq ft |
Tailplane Area |
151.5 sq ft |
Elevator Area |
81.5 sq ft |
INTERNAL DIMENSIONS |
Cabin Length |
31ft 5 in |
Maximum Width |
8ft 9 in |
Maximum Height |
6ft 10 in |
Floor Area |
242 sq ft |
Volume |
1,580 cu ft |
Cabin Doors - Left & Right |
33 x 66 in |
Cabin Doors - Rear |
921 x 82 in |
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