CAE SimuFlite Citation Bravo, Pilot Training Manual

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4-70
Developed for Training Purposes
Citation Bravo
March 2009
CAE SimuFlite
Obstacle Clearance (continued)
2. Use the climb gradient equation to determine the required climb gradient.
For flaps 0° . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.13%
For flaps 15° . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.51%
3. Use the Second Segment Takeoff Climb Gradient — Percent tables
(
Figure 4-34
and
Figure 4-35
) to determine if the aircraft is within the
maximum takeoff weight for obstacle clearance.
Use the obstacle clearance diagram
(
Figure 4-36
)
for a graphic
example of this problem
.
a. Enter the Second Segment Takeoff Net Climb Gradient – Percent
tables ( flaps 0° and 15° ) for the appropriate takeoff weight ( 14,800
lbs ) from the left at the pressure altitude ( 2,000 ft ), then move right
one column and select the correct temperature row ( 20° ).
b. In this row, move to the wind ( zero ) and read the net climb gradi-
ent ( 6.2% for flaps 0° and 5.3% for flaps 15° ).
In this example, the Second Segment Takeoff Net Climb Gradient
– Percent charts determine that a flaps 0° takeoff must be used to
clear the 325 ft obstacle 4,800 ft from the end of a 5,300 ft runway.
A flaps 15° takeoff results in a 5.3% net climb gradient when a
5.51% gradient is required. A flaps 0° takeoff results in a 6.2% net
climb gradient, when a 6.13% gradient is required.
If a flaps 15° takeoff is required due to a short runway, the aircraft
weight must be reduced below 14,800 lbs to clear the obstacle.
325
5 300

--------------- 100 6.13%
=

 
 
325
5 900

--------------- 100 5.51%
=

 
 