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Technical Specifications & Standard Equipment List TECHNICAL SPECIFICATIONS & STANDARD EQUIPMENT LIST TECHNICAL SPECIFICATIONS & STANDARD EQUIPMENT LIST Aircraft Overview The Viking 400S Twin Otter (“400S”) is an all-metal, high wing monoplane, powered by two wing-mounted turboprop engines, The aircraft is delivered with two Pratt and Whitney PT6A-27 driving three-bladed, reversible pitch, fully feathering propellers. engines that incorporate platinum coated CT blades. The aircraft carries a pilot, co-pilot, and up to 17 passengers in standard configuration with a 19 or 15 passenger option. The The 400S will be supplied with new generation composite floats aircraft is a floatplane with no fixed landing gear. that reduce the overall aircraft weight (when compared to Series 400 Twin Otters configured for complex utility or special mission The 400S is an adaptation of the Viking DHC-6 Series 400 Twin operations). The weight savings allows the standard 400S to Otter (“Series 400”). It is specifically designed as an economical carry a 17 passenger load 150 nautical miles with typical seaplane for commercial operations on short to medium reserves, at an average passenger and baggage weight of 191 segments. lbs. (86.5 kg.). The Series 400 is an updated version of the Series 300 Twin Otter. The changes made in developing the Series 400 were 1. General Description selected to take advantage of newer technologies that permit more reliable and economical operations. Aircraft dimensions, Aircraft Dimensions construction techniques, and primary structure have not Overall Height 21 ft. 0 in (6.40 m) changed. Overall Length 51 ft. 9 in (15.77 m) Wing Span 65 ft. 0 in (19.81 m) The aircraft is manufactured at Viking Air Limited facilities in Horizontal Tail Span 20 ft. 8 in (6.29 m) Alberta and British Columbia, Canada. The Type Certificate (A- 82 from Transport Canada) is held by Viking Air Limited. Cabin Dimensions The aircraft is optimized for quick turnaround between cycles, Length 18 ft. 5 in (5.61 m) featuring double swing out doors at the aft passenger entrance Height 4 ft. 11 in (1.50 m) with direct access through the cabin to the rear baggage Width 5 ft. 9 in (1.75 m) compartment for quick loading. A separate avionics-dedicated battery also allows the cockpit screens to remain live during short Left Side cabin doors turns. The avionics have been adapted for VFR operations and 50 in x 56 in (1.27 m x 1.42 m) feature a Honeywell “Super-Lite” integrated suite. Avionics upgrade options available for IFR operation as outlined in Section Right side cabin door 20. 30 in x 45 in (0.76 m x 1.16 m) With the 400S specification, particular attention has been paid to the unique challenge corrosion causes in water-based operations; corrosion-resistant packages for the airframe, power 2. Design Weights & Capacities plant and fuel systems have been incorporated as standard equipment, along with additional draining, sealing, battery Max. Takeoff Weight 12,500 lbs. (5,670 kg.) relocation, and prevalent use of corrosion-resistant materials Max. Landing Weight 12,300 lbs. (5,579 kg.) throughout. The airframe has a corrosion prevention primer Equipped Weight Empty 7,915 lbs. (3,590 kg.) applied, and electrical connectors and sensors exposed to water Fuel Capacity 378 US Gallons (1,432 l) have been upgraded. Note: The “400S Seaplane” is a marketing definition for branding purposes only and does not constitute a new Type Design. Information contained within this report is proprietary to Viking Air Limited and provided for reference purpose only. Provision of this information does not constitute any form of contractual commitment between Viking Air Limited and the recipient. No warranty or representation is made to the accuracy or applicability of the information contained herein, and data is subject to change without notice. DOCUMENT REVISION: 02-02-16 TECHNICAL SPECIFICATIONS & STANDARD EQUIPMENT LIST 3. General Arrangement Note: The “400S Seaplane” is a marketing definition for branding purposes only and does not constitute a new Type Design. Information contained within this report is proprietary to Viking Air Limited and provided for reference purpose only. Provision of this information does not constitute any form of contractual commitment between Viking Air Limited and the recipient. No warranty or representation is made to the accuracy or applicability of the information contained herein, and data is subject to change without notice. DOCUMENT REVISION: 02-02-16 TECHNICAL SPECIFICATIONS & STANDARD EQUIPMENT LIST 4. Performance The following performance data is intended to demonstrate the aircraft's capability in a typical flight profile. SFAR23 Takeoff and Landing Distances Takeoff dist. to 50 ft. (15.2m) at MTOW 2,247 ft. (685 m) Landing dist. from 50 ft. (15.2m) at MLW 1,741 ft. (531 m) ISA+10 Maximum Cruise Speeds, TAS 2,000 ft. 153 kt 4,000 ft. 154 kt 8,000 ft. 156.5 kt Enroute Rate of Climb at Sea Level Both engines at max climb power 1,347 ft./min Service Ceiling (Rate of Climb 100 ft/mm) Both engines max climb power 22,000 ft. (6,706 m) One engine max cont. power 4,500 ft. (1,372 m) Payload Range (incl. two pilots totaling 380 lbs.) Payload for 50nm range 3,636lbs. (1,649 kg.) Payload for 100nm range 3,429lbs. (1,555 kg.) Payload for 150nm range 3,245lbs. (1,472 kg.) Payload for 200nm range 3,039lbs. (1,378 kg.) Performance Assumptions Used All takeoff distances are based on both engines operating at takeoff power throughout. The takeoff and landing distances are given at sea level, zero wind and calm water surface. Payload range data is based on the following assumptions: o Cruise at maximum cruise power at 8,000 ft. (2,438 m) for both 150 nm and 225 nm segments, and at 5,000 ft. (1,524 m) for both 50 nm or 100 nm segments, o Climb at maximum power and descent at 500 feet / minute, o Taxi, takeoff and landing fuel allowance of 35 lbs. (16 kg.), o Fuel reserve of 300 lbs. (136 kg.); and o Fuel consumption based on engine manufacturer's specifications. Operational Empty Weight is 8,305 lbs. (3,767 kg.) and assumes a standard aircraft fitted with 17 commuter seats operating with a crew of 2 at 190 lbs. (86.2 kg.) each. All performance data assumes ISA+10 conditions. Note: The “400S Seaplane” is a marketing definition for branding purposes only and does not constitute a new Type Design. Information contained within this report is proprietary to Viking Air Limited and provided for reference purpose only. Provision of this information does not constitute any form of contractual commitment between Viking Air Limited and the recipient. No warranty or representation is made to the accuracy or applicability of the information contained herein, and data is subject to change without notice. DOCUMENT REVISION: 02-02-16 TECHNICAL SPECIFICATIONS & STANDARD EQUIPMENT LIST 5. Fuselage Two plug-type emergency exits are provided in the main cabin: one in each side panel at the forward end of the cabin. A single With the exception of the conical nose section, the fuselage swing-out exit door is located on the right side of the aft cabin primary structure is of an all-metal conventional construction with section. frames, stringers, and skin all made of aluminum alloy. Eight acrylic plastic windows are installed on the right side of the The external surfaces of the standard aircraft are primed with a cabin: one in the forward emergency exit, one in the right cabin chromated epoxy primer and are ready for paint application. The door, and six in the side panel. Seven similar windows are airframe has a corrosion prevention primer applied. installed on the left side of the cabin: one in the forward The fuselage is comprised of five permanently attached sections: emergency exit, one on the cabin door and five in the side panel. the nose section; the flight compartment; the fuselage forward The complete main cabin has a total usable volume of cabin; the fuselage rear cabin; and the rear fuselage. 3 approximately 384 cubic feet (10.9 m ). Nose Section The nose section, manufactured in three sections, consists of a Rear Fuselage Section nose cap, center, and rear sections. The main center section is a The rear fuselage section, which contains the rear baggage carbon fibre composite assembly with a foam core, and forms the compartment, extends aft in a gradual taper from the frame nose compartment. The upward and outward-opening nose forward of the left door surround. A cargo net arrangement compartment access door, located on the left side of the nose separates the main passenger cabin from the baggage section, is equipped with a prop rod to hold the door open and compartment. two latches, the forward of which can be locked externally by key. Flight Compartment Section 6. Wings The flight compartment extends from the forward bulkhead aft to The wing consists of the left and right mainplanes, which are a flight compartment / cabin bulkhead and consists of a rectangular in plan form and of constant section. Each mainplane conventional skin and stringer frame bulkhead structure. Two is attached to the fuselage structure, at roof level, by two bolts forward, outward-opening doors, one on the left and one on the through fork and lug fittings at the front and rear spars, and is right, are provided for external access to the flight compartment. supported by a lift strut having single bolt attachments at each Bird impact-resistant plastic windshield panels are standard. end. A double-slotted, full-span flap/aileron system is installed Access to the flight compartment from the cabin is provided by a at each mainplane trailing edge.
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