de Havilland Canada DHC-6 Twin Otter

In 1964 de Havilland Canada announced that it was developing a twin-turboprop high-wing monoplane with STOL capability to provide accommodation for 13 to 18 passengers. Identified as the de Havilland Canada DHC-6 Twin Otter, the first of an initial batch of five made its maiden flight on the 20th of May, 1965.

Powerplant for the first three aircraft consisted of two 432-ekW (579-ehp) Pratt & Whitney Aircraft of Canada PT6A engines, but the fourth and subsequent examples of this first Twin Otter Series 100 production version had PT6A-20 engines of similar output.

Design of the aircraft’s wing includes double-slotted trailing-edge flaps and ailerons which can be drooped simultaneously with the flaps to enhance STOL performance. Fixed tricycle landing gear can have optional float or ski installations, as well as the standard, intermediate or tundra wheels.

Intended primarily for service with commuter or third-level airlines, the Twin Otter has nevertheless seen wide use with air forces and government agencies. The aircraft is known for opening up northern Canada and making more accessible than ever before!

The Twin Otter Series 200 offers increased baggage capacity in a lengthened fuselage nose and is certified for operation at a higher gross weight. Series 300 has more powerful PT6A-27 engines, which make possible and increase of almost 1, 000 lbs in maximum take-off weight. Later production aircraft have a 20-seat commuter interior as standard and all floatplane versions, irrespective of series, retain the shorter fuselage nose of the original series 100.

The author has flown the aircraft throughout Canada, the Maldives, and South East Asia.

"The 'key' to the Twin Otter's STOL (short takeoff and landing) abilities are attribuited to its high thickness to chord ratio and tail mounted VORTEX generators".

TYPE: deHavilland DHC-6, Series 300 Twin Otter, utility STOL transport

COUNTRY OF ORIGIN: Canada

DIMENSIONS:
Wing span: 19.80 meters (65 feet)
Length: 15.10 meters (51 feet 9 inches)
Height: 5.70 meters (18 feet 7 inch)

POWER PLANT:
Two Pratt & Whitney Canada PT6A -20, -27, or -34 wing-mounted, turbo-shaft engines, each driving a three-bladed, reversible pitch, fully feathering propeller.

WEIGHTS:
Gross Take Off Weight: 12, 500 lbs
Max Landing Weight: 12, 300 (-29 deg C or below) / 12, 500 (-29 deg C or above) PERFORMANCE:

LIMITATIONS:
Maximum Crosswind Component: 27 KIAS

LOADS:
+ 3.17 to -1.5

PERFORMANCE:
Maximum airspeed (VMO):
0 – 6, 700 feet / 166 KIAS
10, 000 feet / 156 KIAS
15, 000 feet / 141 KIAS
20, 000 feet / 126 KIAS
25, 000 feet / 112 KIAS

Maximum Flap Extension Speed (VFE):
0 - 10 degrees / 103 KIAS
10 - 37.5 degrees / 93 KIAS

Minimum Control Speed / air (VMCA): 64 KIAS

Best Angle of Climb (VX): 87 KIAS

Best Rate of Climb (VY): 100 KIAS

Best Single Engine Rate of Climb (VYSE): 80 KIAS (FLAP 10)

Maximum Gust Intensity (VP/VB): 132 KIASMaximum Cruising Speed: 182 KIAS

Service Ceiling: 26, 700 FT

Range with 2500 LBS payload: 701 NM

Range with 5085 LBS maximum payload: 100 NM

CAPACITY:
Flight crew of two and typical passenger seating for 19

 

 

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