OUT OF GROUND EFFECT�
FULL THROTTLE ( OR LIMIT MANIFOLD
 

PRESSURE) AND 104% RPM
GROSS WEIGHT - KGS.
425 450 475 500 525 550 575 600 625
14
13 12
 

PRESSURE ALTITUDE -Hp X 1,000 FT. 

11 10
 
9 8 7 6 5 4 3 2 1 0900 1,000 1,100 1,200 1,300 1,400
GROSS WEIGHT - LBS.
MAX CONT. OR FULL THROTTLE� OGE HOVER CEILING VS. GROSS WEIGHT
the entire flight operation. Being able to hover at the takeoff location with a certain gross weight does not ensure the same performance at the landing point. If the destination point is at a higher density altitude because of higher elevation, temperature, and/or relative humidity, more power is required to hover. You should be able to predict whether hovering power will be available at the destination by knowing the temperature and wind conditions, using the performance charts in the helicopter flight manual, and making certain power checks during hover and in flight prior to commencing the approach and landing. 
 

TAKEOFF PERFORMANCE
If takeoff charts are included in the rotorcraft flight manual, they usually indicate the distance it takes to clear a 50foot obstacle based on various conditions of weight, pressure altitude, and temperature. In addition, the values computed in the takeoff charts usually assume that the flight profile is per the applicable height-velocity diagram.
SAMPLE PROBLEM 3
In this example, determine the distance to clear a 50foot obstacle with the following conditions:
Pressure Altitude..................................5,000 feet
Takeoff Gross Weight.....................2,850 pounds
Temperature .................................................95°F

Using figure 8-4, locate 2,850 pounds in the first column. Since the pressure altitude of 5,000 feet is not one of the choices in column two, you have to interpolate between the values from the 4,000- and 6,000-foot lines. Follow each of these rows out to the column headed by 95°F. The values are 1,102 feet and 1,538 feet. Since 5,000 is halfway between 4,000 and 6,000, the interpolated value should be halfway between these two values or 1,320 feet ([1,102 + 1,538] 4 2 = 1,320).
 
 

CLIMB PERFORMANCE
Most of the factors affecting hover and takeoff performance also affect climb performance. In addition, turbulent air, pilot techniques, and overall condition of the helicopter can cause climb performance to vary.