TM 1-1510-224-10
Crosswind Component ............................... 12 knots
e.
Takeoff Weight.
The
following
examples
illustrate the use of graphs which may restrict takeoff
weight.
NOTE
Do not exceed the maximum takeoff
weight limitation of 16,500 pounds.
(1)
Maximum takeoff weight as limited by tire
speed. Enter the graphs at 150C, 3499 ft, 10 knots
headwind component, and read:
Flaps Up...... Exceeds Structural Limit of 16,500 lbs
Flaps Approach. Exceeds Structural Limit of 16,500
lbs
(2)
Maximum
takeoff
weight
to
achieve
positive one-engine-inoperative climb at liftoff. Enter the
graphs at 3499 feet pressure altitude, 15C, and read:
Flaps Up ................................................ 16,500 lbs
Flaps Approach ...................................... 16,500 lbs
(3)
Maximum enroute weight for 50-ft/ minute
one-engine-inoperative
climb.
To
determine
the
maximum takeoff weight, the weight of the fuel used to
reach the MEA is added to the maximum enroute weight
obtained from the Service Ceiling - One Engine
Inoperative graph (fig. 7A-38). Use the Time, Fuel, and
Distance to Cruise Climb graph (fig. 7A-39) to determine
the weight of the fuel used to climb. Use the Cruise
Power tables to determine the weight of the fuel used to
cruise to each MEA.
Enter the Service Ceiling - One Engine Inoperative
graph (fig. 7A-38) at the conditions for each enroute
MEA. For example, enter the graph at the highest MEA
altitude of 9000 feet, and trace right; enter again at the
MEA FAT of -4C, and trace up. Read the maximum
enroute weight at the MEA at the intersection of the
tracings.
Maximum enroute weight for 50-ft/min one-engine-
inoperative climb:
8000 ft, 0C
Exceeds Structural Limit of 16,500 lbs
9000 ft, -4C
Exceeds Structural Limit of 16,500 lbs
7600 ft, 0C
Exceeds Structural Limit of 16,500 lbs
Since these weights are all greater than the
maximum takeoff weight limitation of 16,500 lbs, there is
no
additional
limitation
to
meet
enroute
weight
requirements. Anytime the value is less than 16,500 lbs,
add the fuel required to climb, plus any fuel used in
cruise before reaching each MEA, to determine the
maximum
allowable
takeoff
weight
to
meet
the
requirement for each route segment of the trip.
f.
Minimum Static Takeoff Power (Ice Vanes
Retracted). Enter the graph at 150C FAT and 3499 feet
pressure altitude:
Minimum Static Takeoff Power.................... 93.5%
g.
Takeoff Speeds. Tables are provided for
takeoff decision speed (V1), rotation speed (VR), takeoff
safety speed (V2), and all-engines takeoff safety speed
(V50.)
In order to determine the takeoff speeds for 15C
FAT, 3499 feet pressure altitude, and 16,000 pounds
takeoff weight, enter the tables at 2000 ft and 4000 ft
pressure altitude, 10C and 20C FAT, and 16,000
pounds takeoff weight, then interpolate to find the actual
values for the specified conditions:
V1 .....116 KTS (flaps up), 108 KTS (flaps approach)
VR.....124 KTS (flaps up), 113 KTS (flaps approach)
V2 .....128 KTS (flaps up), 114 KTS (flaps approach)
V50....140 KTS (flaps up), 126 KTS (flaps approach)
h.
Minimum Field Length. The following example
illustrates the use of graphs which may restrict takeoff
weight due to field length available under existing
conditions.
(1)
Takeoff distance. Enter the graphs at
15C, 3499 feet pressure altitude, 16,000 pounds, 1.9%
downhill runway gradient, and 10 knots headwind
component, and obtain the following results:
Ground Roll (flaps up) .........................................3602 ft
Takeoff Distance (flaps up) ..................................5167 ft
Ground Roll (flaps approach................................2960 ft
Takeoff Distance (flaps approach)........................4150 ft
(2)
Accelerate-stop
distance.
Enter
the
graphs at 15°C, 3499 feet pressure altitude, 16,000
pounds, 1.9% downhill runway gradient, and 10 knots
headwind component, and obtain the following results:
Accelerate-Stop Distance (flaps up) .....................5924 ft
Accelerate-Stop Distance (flaps approach)...........5047 ft
(3)
Accelerate-go distance. Enter the graphs
at 15°C, 3499 feet pressure altitude, 16,000 pounds,
1.9% downhill runway gradient, and 10 knots headwind
component, and obtain the following results:
Accelerate-Go Distance (flaps up)...................... 7419 ft
Accelerate-Go Distance (flaps approach)............ 5389 ft
The minimum recommended runway length is the
longest of the distances determined above for the
selected flap
7A-11
