Hawker 850XP Pro Line 21 Airplane Flight Manual
Page 12
FAA Approved
Original Issue: Feb 28, 2006
Sub-section - 5.55
GROSS PERFORMANCE
FINAL TAKE-OFF CLIMB GRADIENT
The gross and net gradients of climb for the final take-off configuration are shown on Figure
5.55.3 for varying weight, altitude and air temperature.
Associated Conditions
NOTES:
1. To take account of engine antice bleed, add 10° C to the actual air temperature
before entering the graph.
2. The gradients given are those away from ground effect.
Instructions for Use of Chart
The use of the graph is illustrated by broken arrowed lines.
• Enter with air temperature and move up to the appropriate field pressure altitude.
• Proceed horizontally to the weight grid reference line and then follow the guidelines to
the required airplane weight.
• Move horizontally to the gross gradient reference line and then either continue
horizontally to read gross gradient from the scale at the right, or follow the guidelines
down to the net gradient position before reading net gradient from the scale at the right.
Engines
One engine operating at maximum continuous thrust, the other engine
stopped.
Engine Bleed Air
Air conditioning bleed off; see NOTE 1 for the effect of engine antice
bleed.
Flaps
0°
Landing Gear
Up.
Airspeed
Final take-off climb speed V
FTO
. (See Figure 5.10.1)
For Training Purposes Only
