Page 18
FAA Approved
Original Issue:
Feb 28
, 2006
Sub-section - 5.55
GROSS PERFORMANCE
Hawker 850XP Pro Line 21 Airplane Flight Manual
GO-AROUND CLIMB GRADIENT
The gross gradient of climb for the go-around configuration is shown on Figure 5.55.5 for varying
weight, field pressure altitude and air temperature.
Associated Conditions
NOTE: To take account of engine antice bleed, add 10°
C to the actual air temperature
before entering the graph.
Instructions for Use of Chart
The use of the graph is illustrated by the 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
appropriate airplane weight.
• Continue to the right to meet the flap correction grid reference line and then either continue
horizontally to read the flaps 45° gross gradient from the scale at the right or follow the
guidelines to the flaps 25° position before reading the gross gradient from the scale at the
right.
Engines
Both engines operating at maximum take-off thrust with APR OFF.
Engine Bleed Air
Air conditioning bleed off; see NOTE for the effect of engine antice
bleed.
Flaps
45° or 25°
Landing Gear
Down
Airspeed
Flaps 45°: not greater than V
REF
Flaps 25°: not greater than V
REF
+ 5 knots.
For Training Purposes Only
