TM 1-1510-262-10
av. Range Proile-Normal Cruise Power at 1500 RPM.
(1) Description. The Range Proile-Normal Cruise Power at 1500 RPM graph (Fig. 7-63) depicts range at
normal cruise power.
(2) Purpose. This graph is used to determine range in nautical miles for various fuel loads and fuel tank
combinations, given pressure altitude in feet and true airspeed in knots. Range allows for start, taxi, and runup;
includes cruise climb and descent; and allows for 45 minutes reserve fuel at maximum range power. At 16,620
pounds ramp weight the maximum zero-fuel weight limitation of 13,100 pounds would be exceeded at fuel loading
less than 3520 pounds.
aw. Maximum Range Power at 1500 RPM.
(1) Description. The Maximum Range Power at 1500 RPM tables (Fig. 7-64 through 7-71) show fuel low,
airspeed, and torque for various light conditions.
(2) Purpose. These tables are used to determine fuel low per engine, total fuel low, indicated airspeed,
and true airspeed, given pressure altitude in feet, indicated free air temperature and free air temperature in degrees
Celsius, aircraft weight in pounds, and torque per engine in percent. During operation with ice vanes extended,
torque will decrease by approximately 10%. Fuel low will decrease by approximately 5%, and true air speed will be
reduced by approximately 10 knots.
ax. Range Proile Maximum Range Power at 1500 RPM.
(1) Description. The Range Proile Maximum Range Power at 1500 RPM graph (Fig. 7-72) depicts range
at maximum range power.
(2) Purpose. This graph is used to determine range in nautical miles for various fuel loads and fuel tank
combinations, given pressure altitude in feet and true airspeed in knots. Range allows for start, taxi, and runup;
includes cruise climb and descent; and allows for 45 minutes reserve fuel at maximum range power. At 16,620
pounds ramp weight, the maximum zero fuel weight limitation of 13,100 pounds would be exceeded at fuel loading
less than 3520 pounds.
ay. Loiter Power at 1700 RPM.
(1) Description. The Loiter Power at 1700 RPM tables (Fig. 7-73 through 7-80) show fuel low, airspeed,
and torque for various light conditions.
(2) Purpose. These tables are used to determine fuel low per engine, total fuel low, indicated airspeed,
and true airspeed, given pressure altitude in feet, indicated free air temperature and free air temperature in degrees
Celsius, aircraft weight in pounds, and torque per engine in percent. During operation with ice vanes extended,
torque, fuel low, and true airspeed will remain approximately unchanged.
az. Endurance Proile-Loiter Power.
(1) Description. The Endurance Proile-Loiter Power at 1700 RPM graph (Fig. 7-81) depicts endurance at
loiter power allowing fuel for start, taxi, runup, cruise climb and descent, and 45 minutes fuel reserve.
(2) Purpose. This graph is used to determine endurance in hours for various fuel loads and fuel tank
combinations, given pressure altitude in feet and true airspeed in knots. Endurance allows for start, taxi, and runup;
includes cruise climb and descent; and allows for 45 minutes reserve fuel at maximum range power. At 16,620
pounds ramp weight, the maximum zero fuel weight limitation of 13,100 pounds would be exceeded at fuel loading
less than 3520 pounds.
ba. Range Proile-Full Main Tanks.
(1) Description. The Range Proile-Full Main Tanks graph (Fig. 7-82) depicts range, allowing fuel for start,
taxi, runup, cruise climb and descent, and 45 minutes fuel reserve.
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