TM 1-1510-262-10
Table 7-1.
Route Segment Data
2
AVERAGE
MAG-
AVERAGE
WIND AT
FAT AT
ALTIMETER
ROUTE
NETIC
MAGNETIC
DISTANCE
FL 250
FL 250
MEA
FAT AT
SETTING
SEGMENT
COURSE
VARIATION
NM
DIR KNOTS
C
FEET
MEA C
IN.HG
91
-40
8000
0
29.97
BIL-SHR
117
15E
010/45
3
57
-40
9000
-4
29.60
SHR-CZI
139
14E
350/65
69
-30
7600
0
29.48
CZI-CPR
161
13E
310/50
3
Source: DOD Low Altitude Enroute Chart L-9, 9 Jan 1992.
2
3 Includes
distance between airport and VORTAC, per DOD US IFR SUPPLEMENT, 9 JAN 1992.
BT06334
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 15C, 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 max-
imum 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. 7-38). Use the Time, Fuel, and Distance to
Cruise Climb graph (Fig. 7-39) 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. 7-38) 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.
7-14
