CAE SimuFlite Citation Bravo, Pilot Training Manual

Page: 319 / 718

Flight Planning
Citation Bravo
Developed for Training Purposes
4-67
September 2005
CAE SimuFlite
Takeoff Correction Factors
Takeoff Field Length – Feet, with Flaps 0°
2% ADD 4 KTS 1.50** ADD 4 KTS 1.50**
UPHILL
1% ADD 2 KTS 1.25 ADD 2 KTS 1.25
UPHILL
1% SUBTRACT 1.0 ADD 1 KT 1.03
DOWNHILL 3 KTS
2% SUBTRACT 1.0 ADD 1 KT 1.03
DOWNHILL 6 KTS
SHADED NON-SHADED
RUNWAY MULTIPLY MULTIPL Y
GRADIENT V
1
* DISTANCE BY V
1
* DISTANCE BY
2% ADD 4 KTS 1.75** ADD 4 KTS 1.75**
UPHILL
1% ADD 2 KTS 1.35 ADD 2 KTS 1.35
UPHILL
1% SUBTRACT 1.0 ADD 1 KT 1.05
DOWNHILL 3 KTS
2% SUBTRACT 1.0 ADD 1 KT 1.05
DOWNHILL 6 KTS
SHADED NON-SHADED
RUNWAY MULTIPLY MULTIPL Y
GRADIENT V
1
* DISTANCE BY V
1
* DISTANCE BY
V
1
- KIAS NO CORRECTION
TAKEOFF FIELD LENGTH - FEET MULTIPLY DISTANCE BY 1.25**
CORRECTION FACTORS – ANTI-ICE ON
V
1
- KIAS NO CORRECTION
TAKEOFF FIELD LENGTH - FEET MULTIPLY DISTANCE BY 1.30**
CORRECTION FACTORS – ANTI-ICE ON
Takeoff Field Length – Feet, with Flaps 15°
* If the adjusted V
1
is greater than V
R
, the value of V
R
must be used for V
1
.
** Takeoff prohibited for corrected takeoff field lengths greater than 11,000 ft.
4-32
Obstacle Clearance
Assume that an engine fails at V
1
and the takeoff is to be
continued. Whether an obstacle in the flight path can becleared
becomes critical.
In this example, an obstacle 325 ft high is 4,800 ft from the
departure end of the runway.
To determine obstacle clearance, climb gradients must be
addressed. Climb gradients are the mathematical relationship of
vertical distance (i.e., “rise”) divided by the horizontal distance
(i.e., “run”) and expressed in percent.
For example, if an aircraft climbs 50 ft for every 1,000 ft
covered horizontally, it has a 5.0% climb gradient.
. %
The point at which the aircraft reaches 35 ft above the runway
surface is called “reference zero.” Reference zero has two factors:
its distance from brake release (i.e., takeoff field length) and its
height above the runway surface (i.e., 35 ft)
(
Figure 4-33
).
Shortly after reaching reference zero, the gear completes retrac-
tion. The first segment of climb is from reference zero to gear
retraction. The second segment is from gear retraction to 400 ft
AGL. If the pilot holds V2 during the first and second climb
segments, the manufacturer guarantees a known climb gradient
(net climb gradient) for that weight, pressure altitude, and tem-
perature.
1. Compare the known climb gradient with the required climb gra-
dient. The required gradient is that needed to clear the obstacle.
With an engine failure at V
1
and flaps 0°, the aircraft is
35
ft AGL at 4,800 ft from brake release (i.e., takeoff field
length), which is 500 ft from the end of the runway (5,300
minus 4,800 equals 500).
With an engine failure at V
1
and flaps 15°, the aircraft is
35 ft AGL at 4,200 ft from brake release (i.e., takeoff field
length), which is 1,100 ft from the end of the runway (5,300
minus 4,200 equals 1,100).
Because the obstacle is 4,800 ft from the departure end of the
runway, the distance to the obstacle from reference
zero is
5,300 ft with 0° flaps (4,800 plus 500 equals 5,300).
With flaps 15°, the obstacle is 5,900 ft from reference zero
(4,800 plus 1,100 equals 5,900).
50
100
---------- 100 
5.0 =
4-68