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19-22).
NOTE
Approved points are located inside
the envelope below the Maximum
Landing Weight line.
19-22 510OM-00
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510OM-00 19-23
CITATION MUSTANG OPERATING MANUAL
Figure 19-17. Example Aircraft Weighing Form—U.S. Units
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Figure 19-18. Example Weight-and-Balance Computation Form—U.S. Units
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CITATION MUSTANG OPERATING MANUAL
Figure 19-19. Example Center-of-Gravity Limits Envelope Graph—U.S. Units
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Figure 19-20. Example Aircraft Weighing Form—Metric Units
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CITATION MUSTANG OPERATING MANUAL
Figure 19-21. Example Weight-and-Balance Computation Form—Metric Units
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Figure 19-22. Example Center-of-Gravity Limits Envelope Graph—Metric Units
CITATION MUSTANG OPERATING MANUAL
Flight Planning and Performance
MODEL 510
510-0001 AND ON
MEMBER OF GAMA
19 JANUARY 2007 COPYRIGHT © 2006
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
510OM-00 ORIGINAL
CITATION MUSTANG OPERATING MANUAL
ii 510OM-00
TABLE OF CONTENTS
PAGE
DEFINITIONS………………………………………………………………………. 1
CLIMB……………………………………………………………………………….. 3
CRUISE……………………………………………………………………………... 9
MULTI-ENGINE…..………………………………………………….……………… 10
SINGLE-ENGINE…………………………………………………………...……….. 38
DRIFTDOWN………………………………………………………………………. 45
DESCENT………………………………………………………………………….. 47
HOLDING…………………………………………………………………………… 51
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510OM-00 1
DEFINITIONS
Altitude: All altitudes used in this manual are pressure altitudes unless
otherwise stated
Anti-Ice systems: The engine anti-ice system is the only anti-ice system that affects
performance in this section. Performance, when referred to ANTI-ICE
ON, is based on the above system being operated.
Additionally, windshield, pitot-static and angle-of-attack anti-ice
systems are anti-ice systems which do not affect performance.
Deice Systems: The wing, horizontal stabilizer, and tail deice system comprise the
deice system.
FAA: Federal Aviation Administration
Hr: Hour
Ind Mach: The displayed Mach number value that includes position error. Zero
instrument error is assumed.
ISA: International Standard Atmosphere in which:
a. The air is a dry perfect gas;
b. The temperature at sea level is 15°C;
c. The pressure at sea level (standard datum plane) is 29.92
inches mercury;
d. The temperature gradient from sea level to the altitude at
which the temperature is –56.6°C will be –1.98°C per 100
feet.
KIAS: Airspeed indicator reading (knots) that includes position error. Zero
instrument error is assumed.
KTAS: True airspeed expressed in knots
Lb: Pound
Lb/hr: Pounds-per-hour
M or Mach: Mach number. The ratio of true airspeed to the speed of sound.
N1 Low pressure turbine speed. The fan is attached to the low pressure
turbine.
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TEMP Ambient air temperature. The free air static temperature, obtained
　
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