TM 55-1510-222-10
Maximum Landing Weight (from LIMITATIONS Section)
...................................................................... 15,200 lbs
Therefore, the Maximum Landing Weight limitation
would be exceeded by 76 pounds. In order to meet the
requirement, off-load 76 pounds of useful load prior to
takeoff, or burn off an additional 76 pounds of excess
fuel (i.e., NOT Reserve Fuel) before landing.
Revised Landing Weight
(15,276 lbs - 76 lbs)........................................ 15,200 lbs
(2) Normal Landing Distance Without Propeller
Reversing - Flaps Down. Enter the graph at 20 DEG C,
5998 feet, 15,200 pounds, zero runway gradient, 10
knots headwind component, and read the following:
Ground Roll ...................................................1740 ft
Total Distance over 50-ft Obstacle.................3350 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-Ft Obstacle - Flaps Down............... 3610 Ft
Landing Distance - Without Propeller Reversing - Flaps
Up. Enter the graph with the normal landing distance
determined in paragraph (2) above and read the
following:
Flaps-Up Landing distance over 50-Ft
Obstacle ...................................................... 4710 Ft
(4) Climb - Balked Landing. Enter the graph at
20°C, 6400 feet (see note 2 on graph), 15,200 pounds,
and read the following results:
Rate of Climb.......................................... 1620 ft/min
Climb Gradient............................................... 12.6%
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...........................162 KIAS
Indicated Pressure Altitude .................... 25,000 Feet
Indicated Free Air Temperature ...................... -24°C
Airspeed Calibration - Normal System. Enter the
Flaps-Up graph at the indicated airspeed value of 162
knots, read up to the reference line and left to obtain the
following result:
Calibrated Airspeed ..................................166 Knots
Altimeter Correction - Normal System. Enter the
Flaps-Up graph at the indicated airspeed value of 162
knots, read up to the seal level and 35,000-foot
reference lines and left to obtain the following results:
Altimeter Correction (Sea Level) .............. + 55 feet
Altimeter Correction (35,000)....................+ 180 feet
Compute the correction value for 25,000 feet using
linear interpolation to obtain the following result:
Altimeter Correction (25,000)....................+ 144 feet
Add this result to the indicated pressure altitude
value of 25,000 to obtain the corrected altitude.
Actual Pressure Altitude.......................... 25,144 feet
Indicated Outside Air Temperature Correction.
Enter the graph at the calibrated airspeed value of 166
knots, read right to the actual pressure altitude of 25,144
feet and down to obtain the following result:
Temperature Correction............................... + 5.6°C
Compute the Free Air Temperature by subtracting
the temperature correction of 5.6'C from the indicated
temperature of-24°C to obtain:
Free Air Temperature.....................................29.6°C
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