IGE Hover Ceiling
Rolls-Royce 250-C47B Engine at Takeoff Power
Basic Inlet Installed

NOTE: Takeoff and landing has not been demonstrated and is not approved above 17,000 feet / 5182 meters density altitude

OGE Hover Ceiling
Rolls-Royce 250-C47B Engine at Takeoff Power
Basic Inlet Installed

NOTE: Takeoff and landing has not been demonstrated and is not approved above 17,000 feet / 5182 meters density altitude.

Service Ceiling
Rolls-Royce 250-C47B Engine at Maximum Continuous Power
Basic Inlet Installed

Take Off and Landing Limitation
Optional 5250 lb / 2381 kg Internal Gross Weight Kit
Rolls-Royce 250-C47B Engine at Takeoff Power
Basic Inlet Installed

NOTE: Takeoff and landing with optional 5250 lb / 2381 kg internal gross weight has not been demonstrated and is not approved above 11,000 feet / 3353 meters density altitude.

FUEL FLOW VS AIRSPEED
ISA & ISA+20°C
ROLLS-ROYCE 250-C47B ENGINE
BASIC INLET INSTALLED
LOW SKID GEAR WITHOUT FAIRINGS
WITH PLUS ENGINE DATA*

For particle separator installed; increase fuel .ow two (2) lb/hr [one (1) kg/hr]
For cross tube fairings; increase airspeed three (3) knots [.ve (5) km/hr]
Notes:  The best allowable Cruise Speed is either Long Range Cruise Speed [LRC], or when speed is limited by Maximum Continuous Cruise Power [MCP] or VNE , the maximum speed permitted.
*  Plus engine data is shown where there is a signi.cant difference between minimum speci. cation engine power (a “zero” engine) and either maximum continuous power or the engine mechanical power limit. This data is provided to assist planning of operations where fast cruise speed is desired, but the continuous operation limits of 93.5% Torque and / or 727 °C engine MGT are observed. The maximum attainable fast cruise speed will be determined by speci.c engine health (power assurance), and operational limit (torque, MGT, NG or VNE, whichever occurs .rst).
Plus engine percent can be determined during the engine power assurance check by setting the mgt and recording torque. The difference between the recorded torque and the minimum chart value is the plus percent factor.
Fuel Flow vs Airspeed
Pressure Altitude = Sea Level
OAT = +15°C

The data set forth on this document are general in nature and may vary with conditions. For performance data and operating limitations for any speci.c .ight mission, reference must be made to the approved . ight manual.

Fuel Flow vs Airspeed
Pressure Altitude = 2000 FT
OAT = +11°C

Fuel Flow vs Airspeed
Pressure Altitude = 4000 FT .OAT = +7°C

Fuel Flow vs Airspeed
Pressure Altitude = 6000 FT
OAT = +3°C