1. AIRFRAME Objective Know the design and construction features of the airframe and airframe components.

2. The forward section includes crew and passenger/cargo compartment, fuel cell enclosures, and pylon support. The intermediate section provides a deck for engine installation, a heater and electrical equipment compartment, and a baggage compartment. The tailboom includes the tail rotor system, horizontal stabilizer with auxiliary fins, elevator, and vertical fin. The forward section includes crew and passenger/cargo compartment, fuel cell enclosures, and pylon support. The intermediate section provides a deck for engine installation, a heater and electrical equipment compartment, and a baggage compartment. The tailboom includes the tail rotor system, horizontal stabilizer with auxiliary fins, elevator, and vertical fin.

4. The forward portion of the cabin is utilized as the crew compartment. The pilot's station is located on the right side of the crew compartment. The left side of the crew compartment accommodates a passenger or copilot with the installation of the dual controls kit. The windshields are blue tinted acrylic panels and a minimum of structural obstructions give the occupants excellent visibility. Forward cabin doors are provided on both sides for direct access to these two stations. Each door is equipped with a horizontal adjustable window. Crew compartment door locks are provided. CREW COMPARTMENT

6. PASSENGER / CARGO COMPARTMENT The cabin area aft of the crew compartment is utilized as the passenger/cargo compartment. Hinged entrance doors are provided on each side for entrance to the passenger/cargo compartment. Each door is approximately 36 inches wide by 39 inches high. The doors are hinged for forward opening. As a special feature, the left door is hinged at its forward edge, to a secondary (litter) door which in turn is hinged at its forward edge to the helicopter structure. The litter door is 25 inches wide and 39 inches high. The litter door opens only from the outside.

8. Titanium engine pan & fire walls

9. Litter-door hinge points

11. TAILBOOM The tailboom includes a fixed horizontal stabilizer with fixed leading edge slats, a controllable elevator, and a swept-back vertical fin. The horizontal stabilizer is installed on the tailboom and the elevator is installed on the horizontal stabilizer by means of antifriction bearings and bolts. The vertical fin extends from aft end of the tailboom and is canted to relieve tail rotor thrust requirements in forward flight. Auxiliary fins are mounted on the outboard ends of the horizontal stabilizer, and are canted to counteract yaw-roll. A tubular type tail skid is installed on the vertical fin to protect the tail rotor blades in the event of tail-low landings.

12. Tailboom Section

13. Slats Elevator

17. The landing gear assembly consists of two tubular aluminum alloy main skid tubes, two curved tubular aluminum alloy cross tubes, with optional airfoil type fairings on the forward and aft cross tubes. The landing gear is attached to the fuselage structure with four strap assemblies. Provisions are incorporated on the toe of each skid tube for standard tow bar attachment. Two eyebolts are installed on the skid tubes just forward of the aft cross tube for installing ground handling wheels. Each skid tube is provided with five replaceable skid shoes to absorb the wear caused by normal ground contact of the helicopter. A high skid gear kit, a fixed float kit, and an emergency flotation kit are available as optional equipment. The landing gear assembly consists of two tubular aluminum alloy main skid tubes, two curved tubular aluminum alloy cross tubes, with optional airfoil type fairings on the forward and aft cross tubes. The landing gear is attached to the fuselage structure with four strap assemblies. Provisions are incorporated on the toe of each skid tube for standard tow bar attachment. Two eyebolts are installed on the skid tubes just forward of the aft cross tube for installing ground handling wheels. Each skid tube is provided with five replaceable skid shoes to absorb the wear caused by normal ground contact of the helicopter. A high skid gear kit, a fixed float kit, and an emergency flotation kit are available as optional equipment. LANDING GEAR

20. Tow-bar attaching points

21. Dual ground handling wheels can be mounted on each skid tube near the helicopter center of gravity to facilitate handling or movement. The wheels are retract- ed and extended man- ually (hydraulically). Two 10 ply nylon tires with tubes are used on each assembly. GROUND HANDLING WHEELS

27. Fresh air ventilation to the interior is furnished through two large ram air scoops located on the upper nose of the ship, one on each side of the battery access door. Fresh air distributors along the bottom of the front windshield provide ventilation to the cabin in forward flight. The vents are opened or closed by pull handles located on the instrument console. In addition, all doors contain sliding plexiglas windows. An integral blower is a part of the system, and can provide approximately 70 cubic feet per minute during low speed conditions. Fresh air ventilation to the interior is furnished through two large ram air scoops located on the upper nose of the ship, one on each side of the battery access door. Fresh air distributors along the bottom of the front windshield provide ventilation to the cabin in forward flight. The vents are opened or closed by pull handles located on the instrument console. In addition, all doors contain sliding plexiglas windows. An integral blower is a part of the system, and can provide approximately 70 cubic feet per minute during low speed conditions. VENTILATION SYSTEM

28. Vents

29. Snap Vent

32. SERVICING DIAGRAM Tailrotor Gearbox Engine Oil Tank Transmission Reservoir Fuel Cell Filler Cap Fuel Cell Sump Drain Nickle- Cadmium Battery External Power Receptacle (350 To 450 Amps) Hydraulic Reservoir

33. WEIGHT AND CG LIMITS Gross Weight (Internal)4150 Lbs. Gross Weight (External)4250 Lbs. Minimum Cockpit Weight170 Lbs. Floor Loading (Pass/Cargo)75 Lbs. / Sq Ft. Floor Loading (Aft Cargo)86 Lbs. / Sq Ft. Maximum Aft Cargo Weight250 Lbs. Forward CG (Wt Dependent)118.0 - 119.2” Aft CG Limits (Wt Dependent)128.5 - 126.7” Left Lateral CG Limit4.0” Right Lateral CG Limit3.5” LIMITATIONS

34. AIRSPEED Maximum Vne (As Placarded)130 Kts. Maximum Autorotation100 Kts. Doors Off90 Kts. 85 to 100% Torque84 Kts. Engine Air Start52 Kts. Minimum Rate of Descent52 Kts. Maximum Distance69 Kts. Hydraulic Failure61-69 Kts. Complete Loss of Tail Rotor Thrust 52 Kts. ALTITUDE Maximum20,000 Ft. MANEUVERING Aerobatic Maneuvering Prohibited.

35. The gas producer section is comprised of a one stage centrifugal flow compressor directly coupled to a two stage gas producer turbine. The power turbine section is a two stage free turbine which is gas coupled to the gas producer turbine. The engine lubrication system is a circulating dry sump type with an external reservoir and heat exchanger. Pressure and scavenge pumps are mounted within the engine and are driven by the accessory gear box. All engine oil system lines and connections are internal with the exception of the pressure and scavenge lines to the front and rear bearings. POWER PLANT

36. Below the engine a titanium deck acts as a drip pan. This pan is designed to provide sufficient clearance to allow the removal of accessories from the bottom of the engine without removing the engine. Standard day sea level power rating is 650 shp for takeoff (5 minute limit) and 600 shp for continuous operation. In the 206L-3, engine torque is derated to the transmission limits of 435 shp for takeoff and 370 shp for continuous operation. This provides significant reserve power for improved high altitude and hot day performance.

40. COMPRESSOR

42. Chip Plugs

47. ENGINE OIL SYSTEM Capacity: 6.0 U.S. Quarts. The engine oil tank is located under the aft fairing, and access doors are provided for filling and draining the oil tank. A filler cap dip stick is provided to determine the quantity of oil in the tank. An appropriate entry shall be made in the helicopter logbook when oil has been added to the engine, transmission, or tail rotor gearbox. The entry shall show the amount, type and brand name of oil used to prevent inadvertent mixing of oils.

48. Mixing of oils is permitted only within a given group. In any list of oils, there is a group number column. Oil may be mixed with any other oil in its group. For example, an oil in group 4 may be mixed with another brand in group 4. An oil in group 23 may be mixed with any other brand in group 23. Mixing of oils not in the same group is permitted only in an emergency, but shall not exceed 5 hours total operating time. MIL-L-23699 is not approved for use in ambient temperatures below -40 o C (-40 o F). When changing to an oil of a different specification, the system shall be drained and flushed.

49. ENGINE OIL LUBRICATION SYSTEM THER. BEGINS CLOSE 71˚C THER. FULL CLOSED 81˚C BYPASS AT 25PSI PRESS. DIFF

54. END COMPONENTS & SYSTEMS