TM 55-1510-221-10
7-7. ACCELERATE-STOP (FLAPS 0%).
Enter the Accelerate-Stop graph at 28ºC, 5233
feet pressure altitude, 13,480 pounds, and 10 knots
head wind component:
Accelerate-Stop Distance
. . . . . . . . . . . . . . . . . . . . . . . .
5050 feet
Takeoff Decision Speed (VR) . . . . . . . . . . . . . . . . . . . . 98 knots
7-8. TAKEOFF DISTANCE (FLAPS 0%).
Enter the graph at 28ºC, 5233 feet pressure alti-
tude, 13,480 pounds, and IO knots head wind com-
ponent:
Ground
Roll
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3420
feet
Total Distance Over 50-foot Obstacle . . . . 5100 feet
Takeoff Speed:
At Rotation
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
100 knots
At
50 Feet
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1 16 knots
7-9. TAKEOFF FLIGHT PATH EXAMPLE.
The following example assumes the aircraft is
loaded so that takeoff weight is 10,000 pounds.
7-10. ACCELERATE-GO DISTANCE OVER 50-
FOOT OBSTACLE (FLAPS 0%).
Enter the graph at 28°C, 5233 feet pressure alti-
tude, 10,000 pounds, and 10 knots head wind com-
ponent:
Total Distance Over 50-foot Obstacle . . . . 5550 feet
Speed at Rotation (VR)
. . . . . . . . . . . . . . . . . . . . . . . . . . . .
93 knots
Speed at 35 Feet Above Runway (Climb Speed) Knots
7-11. TAKEOFF CLIMB GRADIENT - ONE
ENGINE INOPERATIVE (FLAPS 0%).
Enter the graph at 28°C, 5233 feet pressure alti-
tude, and 10,000 pounds:
Climb
Gradient
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5.1%
Climb
Speed
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
101
knots
A 5.1% climb gradient is 51 feet of vertical
height per 1000 feet of horizontal distance.
NOTE
The graphs for take-off climb gradient
assume a zero-wind condition. Climbing
into a head wind will result in higher
angles of climb, and hence better obstacle
clearance capabilities.
Calculations of the horizontal distance to clear
an obstacle 100 feet above the runway surface:
7-4
Horizontal distance used to climb from 50 feet to 100 feet -
(100 - 50) (1000 ÷ 51) = 981 feet
Total Distance = 5500 + 981- 6531 feet
Results are illustrated below:
7-12. FLIGHT PLANNING.
Calculations for flight time, block speed, and
fuel requirements for a proposed flight are detailed
below using the same conditions presented on page
4-3, and a takeoff weight of 12,000 pounds.
Enter ISA CONVERSION graph at the condi-
tions indicated:
DEN-BVL
Pressure Altitude
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
26,000
feet
FAT
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
-20°C
ISA Condition
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ISA +
17°C
BLV-RN0
Pressure Altitude
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26,000 feet
FAT
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
-10°C
IAS Condition
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ISA + 27°C
Enter the TIME, FUEL, AND DISTANCE TO
CLIMB Graph at 28°C to 5233 feet, and to 12,000
pounds, and enter at -10°C to 26,000 feet, and to 12,
000 pounds, and read:
Time to Climb . . . . . . . . . .
30.0-3.1 = 26.9=27 minutes
Fuel Used to Climb . . . . . . . . . . . . . . . . 379.3-60.0=319.3=
320 pounds
Distance Traveled . . . . . .
85.7-8.7=77 nautical miles
Enter the TIME, FUEL, AND DISTANCE TO
DESCEND Graph at 26,000 feet, and enter again at
4732 feet, and read:
Time to Descend
. . . . . .
17.7-3.1= 14.6 = 15 minutes
Fuel Used to Descend . . . . 198.5-50.0=149 pounds
Distance Traveled . . . . . . . . . . . . . . . . . . . . . . . . 86.5- 15.3 =71.2=
71 nautical miles
An estimated average cruise weight of 11,200
pounds was used for this example.
Enter the tables for MAXIMUM ENDURANCE
POWER 1700 RPM for ISA + 10°C ISA + 20°C,
and ISA + 30°C and read the cruise speeds for 26,
000 feet at 12,000 pounds and 11,000 pounds:
Cruise True Airspeed (ISA + 17°C) . . . . . . 169 knots
Cruise True Airspeed (ISA + 27°C) . . . . . . 172 knots
Enter
the
*MAXIMUM
ENDURANCE
POWER 1700 RPM Tables for ISA + 10°C ISA +
2OºC, and ISA + 30°C at 12,000 pounds and 11,000
pounds and interpolate the recommended torque
settings for ISA + 17°C and ISA + 27°C at 11,200
pounds.
ISA + 17°C . . . . . . . . . . . . . . . . . . . . . . . .
40% torque per engine
