TM 1-1510-224-10
takeoff, or burn off the excess from excess fuel (i.e., not
from reserve fuel) before landing.
(2)
Normal landing
distance
flaps
down.
Enter the graph at 20C, 5998 feet, 15,204 pounds,
0.3% uphill runway gradient, 10 knots headwind
component, and read the following:
Ground Roll ...............................................1857 ft
Total Distance Over 50-Foot Obstacle.........4702 ft
(3)
Abnormal landing distances. The landing
distances for one engine inoperative or flaps retracted
can be determined as shown below.
Landing Distance - One Engine Inoperative - Flaps
Down:
Enter the graph with the normal landing distance
determined in paragraph (2) above and read the
following:
Landing Distance - One Engine Inoperative - Over
50-Foot Obstacle - Flaps Down........................ 5834 feet
Landing Distance - Flaps Up:
Enter the graph with the normal landing distance of
4702 feet as determined in paragraph (2) above and a
landing weight of 15,204 lbs, and read the following:
Flaps-Up Landing Distance Over 50-Foot
Obstacle................................................ 7138 feet
Approach Speed ................................... 136 knots
(4)
Climb balked landing. Enter the graph at
20C, 6400 feet (see note 2 on graph), 15,204 pounds,
and read the following results:
Rate of climb ...................................... 1423 ft/min
Climb Gradient............................................. 9.6%
p.
Enroute Instrument Corrections. Errors are
introduced to measured airspeed and temperature
readings as a result of the aircraft speed. For this
example, it has been assumed that the aircraft is
established in level cruise flight between CZI and CPR.
Pilot's Indicated Airspeed........................158 KIAS
Indicated Pressure Altitude .................. 25,000 feet
Indicated Free Air Temperature.................... -35C
(1)
Airspeed
calibration
normal
system
Graph. Enter the flaps-up graph at the indicated
airspeed value of 158 knots, read up reference line and
trace left to obtain the following results:
Calibrated Airspeed............................... 161 knots
(2)
Altimeter correction normal system Graph.
Enter the flaps-up graph at the indicated airspeed value
of 158 knots, read up to the 25,000-foot reference line
and trace left to obtain the following results:
Altimeter Correction .................................+69 feet
Add this result to the indicated pressure altitude value
of 25,000 feet to obtain the corrected altitude.
Actual Pressure Altitude ...................... 25,061 feet
(3)
Indicated
outside
air
temperature
correction Graph. Enter the graph at the calibrated
airspeed value of 161 knots, read right to the actual
pressure altitude of 25,051 feet and down to obtain the
following result:
Temperature Correction .............................. 5.2C
Compute the free air temperature by subtracting the
temperature correction of 5.2C from the indicated
temperature of -35C to obtain:
Free Air Temperature...............................-40.2C.
Table 7A-5. Example Fuel Flow (Ibs/hr)
WEIGHT
POUNDS
ISA
ISA +5°C
ISA 10°C
16,000
744.0
---
686.0
15,000
745.0
716.25
687.5
14,000
746.0
---
689.0
Total Fuel Flow = 716.25 Ibs/hr
Reserve Fuel = 45 minutes x 716.25 Ibs/hr =537 lbs
BT05788
7A-17
