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APPENDIX H
INTERMEDIATE FLIGHT PREPARATION WORKBOOK
Engine Loss
The loss of an engine will significantly degrade climb performance and lower the performance
ceilings of the aircraft. Time to climb, fuel to climb, and distance in climb will all increase and
performance ceiling will be lowered.
Cruise Definitions
VMO
Maximum Operating Speed
Maximum Operating Mach number
MMO
MCRT
Maximum Cruise Thrust Limit
Best Endurance
The speed for minimum fuel flow in level flight (approximately 0.5 AOA
units)
Maximum Range The level flight speed at which the maximum value of nautical air miles per
pound of fuel is obtained (approximately 0.18 AOA units)
Long Range
The level flight speed above the speed for maximum range speed at which
99% of maximum range is obtained
H104. FACTORS AFFECTING RANGE PERFORMANCE
Outside Air Temperature Specific
OAT variations from the ICAO standard day have no effect on range when less-than-rated power
is required. However, cruise time and fuel flow will be modified slightly because TAS and
engine fuel consumption vary with temperature at a given M. These relationships are true
whether cruising at maximum range (climbing flightpath) or constant altitude. For maximum
range cruise where rated power is required (such as 1-engine operation), an increase in
temperature means a reduction in range, altitude, M, time, and an increase in fuel flow. For
constant altitude cruise at rated power, an increase in temperature reduces the maximum
allowable weight and M that can be flown at that altitude. The effects of temperature on cruise
range, altitude, miles per pound of fuel and mission time are shown as curves of specified
temperature departure from the ICAO standard day.
Wind
When winds are calm, GS equals TAS. When flying into a headwind, GS equals TAS less the
headwind component. When flying with a tailwind the reverse is true. Additionally, wind
affects maximum range values as a result of changes in maximum range TAS. When striving for
maximum range, it is advantageous to reduce the time of exposure to a headwind component and
increase the time of exposure to a tailwind component. This is accomplished by varying the
H-6 T-1A PERFORMANCE MANUAL EXTRACTS


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