SPECIFICATIONS:  

 

 

Aircraft Dimensions
Wing span 49' 10"
Length 35' 9"
Height 10' 6"
Track 9' 10"
Wing area 306.77 sq. ft.
Aspect ratio 7.96

 

Weight and Balance
Empty weight 2,800 lb.
Maximum Takeoff Weight (MTOW) 4,850 lb.
Maximum Landing Weight 4,850 lb.

 

Engine
The engine is a Pratt & Whitney Canada PT6A-27 free turbine turboprop corresponding to manufacturer specification No. 583
Normal Speed - Gas Generator 38,100 RPM
Normal Speed - Power Turbine 33,000 RPM
Normal Speed - Propeller Shaft 2,200 RPM
Fuel ASTM-D_1655 Jet A, Jet A-1 and Jet B

 

Propeller
Manufacturer Hartzell Propeller, Inc.
Hub Model HC-B3TN-3D
Blade Model T-10178 C

 

Altitude Limits
Maximum Operating Altitude 25,000 ft..
Service Ceiling 28,000 ft.

 

Temperature Limits
Maximum 50 oC
Minimum -50 oC

 

Airspeed Limitations
VA Maneuvering Speed (4,850 lbs) 112 KIAS
VA Maneuvering Speed (4,000 lbs) 107 KIAS
VA Maneuvering Speed (3,300 lbs) 101 KIAS
VMO Maximum Operating Speed 151 KIAS
VNO Max Structural Cruising Speed 122 KIAS
VNE Never Exceed Speed 144 KIAS
VS Stalling Speed (max weight, flaps up) 54 KIAS
VSO Stalling Speed in Landing Configuration 47 KIAS
VX Best Angle-of-Climb Speed (sea level) 72 KIAS
VY Best Rate-of-Climb Speed (sea level) 77 KIAS
  Maximum Glide Speed (4,850 lbs) 85 KIAS

 

Maximum Flap Placard Speeds
Flaps degrees KIAS
12 99
18-24 94
Full flaps 88

 

  Performance Clean Wing
  Max. Level Speed   125 KTAS   sea level
  Best Rate of Climb   935 ft / min   at 5000 ft


 

  Range 10'000 ft, ISA, no reserve   Speed   Range   Time
  Internal fuel only   116 KTAS   500 nm   4.33 hr
  With aux. tanks (2 x 64 US gal)   112 KTAS   870 nm   7.58 hr

 

Engine Rating - Maximum Power
Takeoff 550 SHP
Continuous 550 SHP up to 43 oC OAT
Climb-cruise 550 SHP at sea level, 15 oC OAT, max. ITT 695 oC.

 

Airframe Systems
Air Conditioning

Cabin heating is achieved by mixing ram air with engine bleed air in variable proportions for temperature control.

 

The cabin ventilating system consists of ram air inlet, a booster fan, and two fresh air nozzles under the instrument panel.

Electrical Power

Electrical power is provided by a 28 V DC negative ground system. The system incorporates a generator busbar, a battery busbar, and electrical hotbus bar.

 

The primary source of power is a 28 V DC, 200 A engine driven starter/generator.

Fuel System Fuel is contained in two integral fuel tanks with a total usable capacity of 174 US gallons. The fuel quantity/fuel flow indicator is located on the main instrument panel, along with the other engine instrumentation.

Two auxiliary fuel tanks with a capacity of 64 gallons each may be added via the Load Manager.

Ice Protection Ice protection consists of an electrical heating system for the pitot tube, static ports, and the fuel control unit. Prop heating elements are also provided.

The deice controls are located directly underneath the ECS controls. See the ECS checklist.

Indicating and Warning System A central warning system provides indicators for emergency conditions. These are located on the main annunciator panel, directly underneath the engine instruments. See the Panel instructions.

Additionally, master caution and warning indicators will illuminate when critical situations occur. See the Panel instructions.