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

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.

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. central doorway in the flight compartment / cabin bulkhead. Each wing structure is a box of constant section, manufactured

from high strength aluminum alloy, and consists of main and rear Forward & Rear Cabin Sections spars, a short front spar at the root end, and top and bottom skin The forward fuselage section extends from the flight compartment panels. / cabin bulkhead to a frame forward of the left door surround, and the rear section extends from this frame aft to the rear baggage Both mainplane leading edges are hinged between the fuselage compartment. These sections form one large main cabin section. and nacelle to permit access for servicing. Access is also provided to the mainplane interior for the maintenance of flap and The cabin section consists of floor, side and roof panel aileron control systems. Five hinge arms are provided on each assemblies. The roof panels are stiffened by longitudinal mainplane rear spar to carry the flap/aileron system. stringers, with the exception of the center portion which is a honeycomb core sandwich panel. The wing tips, which are removable for servicing and maintenance, have internal lightning protection bonding strips The left cabin entrance comprises two swing out door sections. that are secured to each wing structure to provide a ground for The doors can be locked and unlocked externally and internally. electrical discharge. Electrical wiring to each wing tip is routed through conduit tubing for protection.

7. Empennage 9. Powerplants The tail group is comprised of a horizontal stabilizer, an elevator, The aircraft is equipped with two 680-shaft horsepower PT6A-27 a vertical stabilizer, and a rudder. engines, flat rated to 620 horsepower. The engines use a single line fuel delivery system that feeds 14 nozzles from the same Horizontal Stabilizer manifold. Purolator fuel filters are provided. An engine wash The horizontal stabilizer is a one-piece unit, consisting of front spray ring is provided as standard in each nacelle. and rear full span spars and full span top and bottom skin/stringer panels. Hinge arms extending rearward from the rear spar carry The powerplants are configured with a water operation package the elevator. which consists of platinum coated CT blades on the engine and stainless steel engine control cables. The intake deflector is Elevator removed for weight saving. The elevator consists of left and right-hand units, joined at the center by a torque tube. Each elevator unit is of a conventional Fire detecting and extinguishing systems are installed in both all-metal construction, comprising two span-wise spars with engine nacelles to provide warning of fire and the means to intersecting chord-wise ribs, covered with swaged skin panels to extinguish a fire. provide torsional strength. The elevator is aerodynamically and Engine/Propeller Controls mass balanced to meet flutter criteria, mass balancing being The engine and propeller controls are mounted in the overhead achieved by attaching lead weights to the outboard horns. The left console in the flight compartment, and consist of power levers, elevator unit incorporates a pilot-operated trim tab, and the right propeller levers, and engine fuel levers. elevator unit incorporates a wing flap/elevator interconnect tab.

Power Levers Vertical Stabilizer The power levers move in slots in a quadrant labelled THROTTLE, The vertical stabilizer is of conventional form, consisting of front Each power lever controls engine gas generator speed in the and rear spars connected by ribs and covered by vertical forward and reverse power ranges and propeller blade angle in skin/stringer panels. The rear spar is provided with two hinge the beta range. brackets for rudder attachment (a third rudder hinge attachment is located on the rear fuselage structure). Propeller Levers

Rudder Two propeller levers are located side by side in the overhead The rudder consists of a main spar and ribs covered with swaged console, and they move in slots in a quadrant labelled PROP skin panels. The leading edge of the rudder is faired with a RPM. symmetrical D-shaped nose. The rudder is aerodynamically and Engine Fuel Levers mass balanced as required to meet control force and flutter The fuel levers move in slots in a quadrant in the overhead criteria, with mass balancing achieved by attaching lead weights console. The quadrant is labelled FUEL. Each lever is connected to the rib of the rudder horn. Two tabs are provided on the rudder to the engine fuel shut-off valve on the Fuel Control Unit (FCU) trailing edge; the upper trim tab is operated manually by the pilot, which controls the delivery of fuel to the engine. while the lower is a variable mechanically-geared assist tab.

10. Propellers 8. Float Landing Gear The two propellers are Hartzell HC-B3TN-3D, metal, The purchased aircraft is configured for operation on composite counterweight, three-bladed, fully feathering, reversible, and floats. The aircraft will be delivered at the factory on a standard speed governed units. Each propeller is 8 feet 6 inches (2.6 m) wheel gear provided on loan from Viking. Floats will be shipped in diameter and has a blade angle range of –15° (full reverse) to separately to customer location, with the customer responsible +87° (feathered), and a low pitch pickup setting of +17°. Each for installation of the floats and the safe return shipment of the is controlled in the constant speed range and when feathered by loaned wheel gear system back to Viking. the propeller lever through a propeller governor on the propeller reduction gearbox. The power lever is connected to the propeller

reverse cam mechanism for control of the propeller in the beta Fuel System (+17° to –15°) range. Fuel is contained in forward and aft fuselage tanks located in the lower fuselage beneath the cabin floor. A filler neck and cap for Each propeller system includes propeller blade latches which each tank is provided on the left side of the fuselage. Each tank permit engine starting and stopping when propeller blades are at consists of four interconnected flexible rubber cells, one of which the zero thrust position. Each propeller system incorporates a is a collector cell into which fuel is transferred from the other propeller overspeed governor and an automatic feathering cells through a boost pump operated ejector. The fuel is delivered system. by boost pumps to the engines.

Propeller Autofeather System The fuel system is equipped with a water operation package An automatic propeller feathering system is provided which incorporating a fuel control unit purge valve, additional water automatically feathers the propeller of an underpowered engine drain valves, additional fuel galley sealing, corrosion resistant when a decrease in torque to below approximately 20 PSI is fuel line coating and a corrosion protection upgrade to the boost detected. pumps. Hinged fuel caps are also incorporated.

Ventilation System 11. Systems In keeping with the reduced-weight, short segment profile of the

Electrical Systems 400S, a simplified ventilation system is provided, consisting of The electrical system is a 28 volt, direct current, single wire two fans in the forward cabin, a blower in the aft cabin, and snap air vents in cockpit and aft cabin windows. installation with the airframe used as ground return. The aircraft is entirely 28 volt powered. There are no inverters or fuses. A dedicated supply hose connected to the fresh air intake plenum

Primary DC power is supplied by two engine-driven starter- supplies outside air to the main avionics bay. generators. A 48-amp-hour battery provides power when the Hydraulic System generators are inoperative. Electrical power is distributed through The hydraulic system operates the wing flaps. The main a multiple bus system consisting of left, right, hot battery, and components of the system are an electric motor-driven pump, an battery/external power busses. emergency hand pump, a reservoir, a flap actuator, and a flap The main battery has been relocated to the nose compartment to selector. The hydraulic bay door seal has been upgraded for limit exposure to potential corrosion and to shift the center of additional corrosion protection in water based operations. gravity forward. A separate avionics-dedicated battery is provided to allow screens to remain powered during quick-turn Stall Warning System commercial operations. The stall warning system consists of two lift detecting vanes and switches (which are connected in parallel) located on the left An external power receptacle is located on the fuselage in front of wing leading edge. the LH cockpit door, and is covered by a spring-loaded access panel. Flight Controls The flight controls are conventionally operated through pulley and Lighting cable systems and mechanical linkage by a control column, All interior and exterior lighting is provided by LED (light emitting control wheel and rudder pedals. The control column is of a dual diode) arrays. All LED lamps are ‘high reliability’ specification. Y configuration located on the aircraft centerline with a control The 400S differs from the standard Series 400 by excluding wing wheel pivoted at the upper end of each arm. The ailerons lower inspection lights, cabin reading lights and over-exit lights for with the wing flaps and their degree of movement, including weight saving purposes. degree of differential movement, increases proportionately with

Rain Protection flap deflection. The ailerons move differentially at any flap A windshield wiper system is installed to provide rain protection position. The left elevator, rudder and left aileron are equipped for the windshield. with flight adjustable trim tabs, and the right elevator with a trim

® tab that is interconnected with the flaps. A geared tab (a servo Primus Apex Super-Lite Avionics Suite tab) is installed on each aileron and on the rudder. ® The aircraft is equipped with a Honeywell Primus Apex Super- The flight controls are upgraded to stainless steel for additional Lite ‘glass cockpit’ fully integrated avionics system corrosion protection for water operations. interconnected via various data buses. The integrated design approach provides a consistent display format across all of the Wing Flap System instrument panel display units and display controllers. The wing flaps consist of inboard and outboard fore flaps and an inboard trailing flap on each wing. Each aileron is hinged to its Cockpit Layout corresponding outboard fore flap. The wing flaps are operated All cockpit controls, switches, and displays are readily accessible hydraulically by an actuator in the cabin roof through a system of to the pilot for single pilot operation. There is a single overhead push-pull rods, levers, and bellcranks, and can be selected to any panel located directly above the left pilot windshield that contains desired setting within a range of 0° to 37° by a flap selector lever. controls for engine starting, ignition, DC electrical, and landing A flap-elevator interconnect tab on the right elevator is linked to lights. Circuit breaker panels are located on the left wall of the the flap control system and operates simultaneously with the flight compartment and at the base of the instrument panel flaps to provide compensating longitudinal trim. pedestal. All aircraft system controls and switches are located on

two sub-panels, directly below the two primary flight displays. ® 12. Flight Deck & Primus Apex Super-Lite Instrument Panel Description Avionics Suite The left display unit (DU) is the pilot’s primary flight display (PFD). The situational awareness and multi-function displays Base Specification (MFD) are located in the center. The right DU is the co-pilot’s The standard aircraft includes the following avionics: PFD. These display panels are installed in a single-piece, shock  Left and right pilot Primary Flight Displays (PFD) and PFD mounted instrument panel. controllers  Upper and lower center Multi-Function Displays (MFD) with To the right of the pilot’s PFD is the Electronic Standby Instrument System (ESIS), the main function of which is to display altitude, controller and keyboard attitude, heading, and airspeed in the event of a total failure of the  Display reversion control panel primary avionics system or a total electrical failure. The ESIS is  Flight Director panel powered by a dedicated battery that is entirely independent of the  Flight Management System (FMS) main DC electrical system.  Air Data Attitude Heading Reference System (ADAHRS) A chronometer is located inboard of the co-pilot’s PFD. The clock  Dual multi-mode digital radios (MMDR) occupies a 3 ATI standard space.  Dual audio panel  Single GPS installation The PFD control panels are directly inboard of each PFD. The flight guidance control panel is directly above the multifunction  Single Mode S diversity (EHS) transponder display.  Dual magnetometer  Single DME Fuel system controls and switches are located directly below the  Single Radar Altimeter ESIS on the left side of the instrument panel. Engine fire control switches are mounted outboard of the flight guidance control  One Magnetic Standby Compass panel.  406 MHz ELT with navigation interface  One chronometer The MFD controller, the display reversion control panel, and dimming control for the instrument panel are located on the aft  Two 14V convenience outlets in flight compartment face of the center control yoke.  Electronic Standby Instrument System (ESIS)

The lower sub-panel on the left side contains all switches for The FMS shows information on the PFD and upper MFD for: internal and external lighting. The lower right sub-panel contains  Flight planning switches for certain emergency and configuration functions.  Navigation  Situational awareness Engine fire detection indication and control switches are mounted outboard of the flight guidance control panel, at the top center of  Flight performance data the instrument panel. Dimming controls for instrument panel lighting are mounted forward of the multifunction controller on APEX Super-Lite Avionics System Functionality the control yoke. The Apex system connects to and controls the following stand- alone Honeywell equipment: Primary Flight Display  Air Data Attitude Heading Reference System (ADAHRS) The Primary Flight Display (PFD) provides all the essential flight  Dual Multi-Mode Digital Radios (MMDR) data to the pilot. The PFD displays attitude, heading, airspeed and  Single Global Positioning System (GPS) altitude in the left 2/3 window.  Single Mode S Transponder  Dual magnetometers Attitude information is displayed on the electronic Attitude  Single DME Direction Indicator (ADI) and heading and course information on  Single Radar Altimeter the electronic Horizontal Situation Indicator (HSI). ADAHRS Situational Awareness & Systems Multifunction Display The aircraft is equipped with an Air Data and Attitude Heading (MFD) Reference System (ADAHRS). The system provides primary The situational awareness formats (primarily mapping) with attitude, heading and air data parameters to the Modular Avionics various other system displays (primarily the flight plan) in Unit (MAU). dedicated windows. The MFD display can also be used for the aircraft systems displays, for control of the various components Multi-Mode Digital Radios of the avionics system, and for the display of CAS (Crew Alerting Two Multi-Mode Digital Radio (MMDR) integrated transceivers System) messages. are installed in the nose avionics bay comprising one transmitter and six receivers. The single transmitter is a 2,280 channel, 16 Flight Management System (FMS) Watt, double sideband amplitude modulation communication The Flight Management System (FMS) provides flight planning transmitter capable of 8.33 or 25 kHz channel spacing operation. capability, navigation information and flight performance data to the pilot. The FMS is capable of managing flight planning details Global Positioning System from aircraft take-off to touchdown including predictions of fuel A Global Positioning System (GPS) sensor is installed in the nose and time. avionics bay. The receiver uses 24 channels grouped in 3 hardware groups each consisting of 8 channels. One group is The FMS uses two navigation databases, which contain used for navigation at any given time. The GPS sensor unit worldwide or regional data, namely a custom database which calculates and outputs navigation data, satellite measurement contains flight plans and pilot defined waypoints and an aircraft data, Receiver Autonomous Integrity Monitoring (RAIM) and database consisting of aircraft specific parameters used in FMS Predictive RAIM (PRAIM). performance calculations. Mode S Transponder The FMS uses information from the databases stored in memory A Mode S transponder is installed behind the primary PFD and information from the GPS and ADAHRS to calculate and controller. The transponder provides Air Traffic Control Radar display navigational and flight planning information. Beacon System (ATCRBS), Mode-S. Flight planning information can be entered by the pilot using the MF Controller keyboard.

Dual Magnetometers 13. Interior Two magnetometers are mounted in the vertical stabilizer and A lightweight interior package is standard fitment to all aircraft. provide information to the ADAHRS in magnetic heading mode. This commuter interior complies with FAR 23.853 at amendment 23-49 flammability specifications. Single Distance Measuring Equipment (DME) One DME transceiver is installed in the nose avionics bay. The Seating maximum range of the DME transceiver is 389 nautical miles. Seventeen upholstered seats are fitted as standard in the cabin, with provisions for under seat stowage of hand baggage. Single Radar Altimeter The radar altimeter system measures the aircraft height Above The seating configuration can be adapted to 15 or 19 seat interior Ground level (AGL). The digital readout for radio altitude is configuration. Passenger seats can be removed and re-installed displayed in white text in a black box in the lower center part of when necessary for the transportation of cargo. The seats are the attitude display on the PFD. The radar altitude display is secured to the Douglas track that is attached to the floor rails and removed at altitudes greater than 2,500 feet. When altitude is cabin side rails, and optional coin matting can be installed to less than 550 feet, the lower portion of the PFD altitude tape will protect the composite floor panels. show a yellow cross hatched box to indicate ground proximity. All passenger seats are equipped with lap type safety belts.

Additional Flight Deck Systems

Electronic Standby Instrument System (ESIS) An Electronic Standby Instrument System (ESIS) is installed and displays altitude, attitude, airspeed, and magnetic heading. The ESIS is completely independent from the APEX Super-Lite system.

Magnetic Standby Compass An illuminated magnetic standby compass is mounted at the top of the windshield center post. 14. Cargo and Baggage Loading

The rear baggage compartment has a usable volume of 88 cubic Emergency Locator Transmitter (ELT) 3 feet (2.5 m ), and can carry up to 500 pounds (225 kg), of which An ELT is installed in the empennage connected to an antenna on a maximum of 150 pounds (68 kg) may be loaded on the rear top of the fuselage just forward of the vertical stabilizer. It baggage compartment aft shelf extension. transmits on the international distress frequencies of 121.5, 243.0 and 406 MHz. Baggage tie-down rings are provided for the baggage compartment. Clock Cargo nets separate the rear baggage compartment from the An illuminated quartz chronometer is located on the instrument passenger cabin. The rear baggage compartment is accessed panel, to the right of the upper multifunction display. A setting through the main passenger access door for ease of loading. knob is provided beside the clock face. Note: the 400S is not equipped with a separate rear cargo door.

Intercom An intercom for communication between the pilots is standard. The intercom system is voice activated, and no transmit switch is 15. Exterior Finishing provided on the control wheel for the intercom. The basic aircraft specification is unpainted allowing for a range of optional exterior paint schemes to be added upon request.

16. Additional Loose Equipment 18. Documentation & Technical Publications

 LCD Screen Cleaner & Microfiber Cloth Viking Publications:  Fuel Dipstick Gauge  Canadian Technical Log Books (hard copy)  Pilot Operating Handbook (hard copy & digital subscription)  Gust Lock  Emergency & Abnormal Procedures Quick Reference Handbook  Cowl Plugs (2) (hard copy) (digital subscription)  Electronic Noise Cancelling Headsets (2)  Aircraft Maintenance Manual  Wiring Diagrams Manual (digital subscription)  Propeller Restraining Device (2)  Electrical Load Analysis (hard copy in acceptance binder)  Engine Exhaust Cover (4)  Ground Handling Manual (digital subscription)  Structural Repairs Manual (digital subscription)  Pitot Tube Cover (2)  Illustrated Parts Catalogue (digital subscription)  Keys for Aircraft Doors (8)  DHC-6 Corrosion Prevention & Control Program (digital  External Tie Down Rings (3) subscription)  Inspection Requirements Manual (IR & IC) (digital subscription)  Equipment Bag  Structural Components Service Life Limits (digital subscription)  Maintenance Laptop and Computer Case  Avionics Airworthiness Limitations Manual (digital subscription)  Master Minimum Equipment List (TCCA website)

Pratt & Whitney PT6A-27 Publications: 17. Emergency Equipment  Engine Technical Log Book (hard copy)  Engine Specific Operating Instructions (in POH) First Aid Kit  Engine Maintenance Manual (digital subscription) A first aid kit is located on the aft side of the forward cabin wall.  Engine Illustrated Parts Catalogue (digital subscription)  Engine Service Bulletins and Information Letters (web access)

Portable Fire Extinguishers Hartzell Propeller Publications: A handheld fire extinguisher is located on the aisle floor beside  Propeller Owner’s Manual (hard copy) Co-pilot's seat in the flight compartment. A secondary handheld  Propeller Service Bulletins & Information Letters (web access) fire extinguisher is located in the cabin, forward of the main passenger access door. Honeywell Avionics Publications:  Pilot Operating Guide Emergency Exits  Installation Manual (digital subscription) Two plug-type emergency exits are provided in the passenger  Illustrated Parts Catalogue (digital subscription) cabin, one on each side of the cabin at the forward end. Each is  Service Bulletins, Info Letters & Subscriptions (web access) secured in the closed position by two plates on the lower edge of the door and by the hatch release mechanism on the upper edge Manuals for any applicable STCs: of the door; each is jettisoned by detaching the cover over the  Supplementary Maintenance Manual release mechanism, pulling down the release handle (which then  Supplementary Flight Manual becomes detached), and then pushing the door outward.  Supplementary Parts Catalog

In addition, one (1) year digital subscriptions are provided by Aircraft Technical Publishers (ATP) as well as AVTRAK. ATP provides an on-line resource/portal to the technical publications.

19. Aircraft Limited Warranty 2nd Distance Measuring Equipment (DME) A second DME transceiver can be installed in the nose avionics 400S Factory Warranty bay. The transceiver is as described in Section 12 above. For new aircraft, Viking provides a 12 month or 500 flight hour, (whichever occurs first) limited warranty policy which covers Cockpit Voice Recorder (CVR) non-conformance to technical specifications for the aircraft and A four channel Honeywell AR 120 cockpit voice recorder with any defects in material and/or workmanship under normal use 120-minute recording capacity can be fitted. The CVR is and service. Viking’s warranty policy is administered through integrated with the Apex system and captures radio Viking’s Global Customer Support group. Individual (third party) communication, intercom communication, and input from a flight component warranties are transferred to the customer upon compartment area microphone that is mounted in the center of delivery. the flight compartment, directly below the glare shield. The CVR uses flash memory modules to record data, and has no moving parts. It is equipped with an underwater location beacon. P&WC PT6A-27 Engine Warranty

Pratt & Whitney Canada’s (P&WC) standard warranty is 1000 Flight Data Recorder (FDR) flight hours from date of delivery. A Honeywell 246 words per second flight data recorder with 25 hour recording capacity can be fitted. The FDR uses flash memory Honeywell Avionics Warranty modules to record data, and has no moving parts. It is equipped Honeywell’s standard warranty policy is 3 years. Additional with an underwater location beacon. warranty periods are available for an additional cost. Services are provided via Honeywell’s Global Customer Support Center. TCAS I or II Traffic Advisory System An optional TCAS display can be integrated into the Apex system, Hartzell Propeller Warranty and TCAS alerts are voiced through the aural warning system. The Hartzell Propeller’s standard warranty covers one year or 1,000 system uses a processor, two directional antennas (upper and flight hours upon installation on the aircraft (whichever occurs lower) and a configuration module. Aural alerts are provided first). through the audio panel and from there onward to the crew headsets. TCAS II provides traffic advisories (TA), and resolution advisories (RA) whereas TCAS I provides TA but not RA.

20. Optional Equipment Customer Paint Scheme A variety of customer paint options can be offered on request. Avionics Upgrade Package ® The 400S can be equipped with a Honeywell Apex “Super-Lite” 19 Seat and 15 Seat Interiors optimized integrated avionics suite, per the standard The aircraft can be fitted with an optional 19 seat interior. configuration with the addition of the following: An optional 15 seat interior is available to provide additional  Weather radar (WX) cargo carrying capacity on the rear RHS of the cabin by removing  Class A Terrain Awareness and Warning System (TAWS) the 6th row of double seats and connecting a cargo net to removable stanchions. This allows flexible quick change th nd capability to 17 seats. A removable partition behind the 5 row 2 GPS of seating blocks passenger view and ensures safe stowage. A second independent Global Positioning System (GPS) sensor can be installed in the nose avionics bay. The sensor is as VHF Marine Radio described in Section 12 above. A VHF-FM transceiver is available for communication with marine vessels or land based stations.

Bleed Air Heating and Cooling System An optional heating and cooling system utilizing bleed air from the engines and ram air from a scoop intake in the fuselage provides heated, ram, or mixed air to maintain temperatures in the cabin and flight compartment.

Heated air is circulated through ducts beneath the flooring to outlets at the base of the cabin walls and the flight compartment floor. Two tubes deliver heated air to the windshield defrost outlets. The same ducts circulate cooling ram air or a mixture of heated air and ram air in the cabin and flight compartment.

Two additional tubes deliver unconditioned ram air to the air gaspers located on each outboard side of the instrument panel. Additional ducts deliver ram air to the cabin through individual passenger air gaspers located in the cove molding ducts on each side of the cabin upper walls.

Passenger Life Vest Provisions This comprises the Installation of pouches affixed to the underside of the cabin seats for housing life vests. Life vests are not included.

Coin Mat Flooring Heavy duty coin mat flooring can be installed to protect the composite floor panels from exposure to salt and/or sand when operating in a saline environment.