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1. Landing preceded by a steady three degree angle approach down to the 50-foot height
point with airspeed at VREF in the landing configuration.
2. Two engine thrust setting during approach was selected to maintain the three degree
approach angle at VREF.
3. Idle thrust was established at the 50-foot height point and throttles remained in that setting
until the airplane had stopped.
4. Rotation to a landing attitude was accomplished at a normal rate.
5. Maximum wheel braking was initiated immediately on nose wheel contact and continued
throughout the landing roll.
6. Testing was conducted with both Anti-skid ON and Anti-skid OFF.
7. Speed brakes were not used.
4-6 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
GENERAL
FAA APPROVED
Configuration U.S.
VARIABLE FACTORS AFFECTING PERFORMANCE
Details of variables affecting performance are given with tables to which they apply. Assumptions
that relate to all performance calculations, unless otherwise stated, are:
• Cabin pressurization.
• Anti-ice off.
• Stall Warning-NORMAL.
• Humidity corrections on thrust have been applied according to the applicable regulations.
• Winds, for which correction information is presented on the charts, are to be taken as the
tower winds 32.8 feet (10 meters) above runway surface. Factors have been applied as
prescribed in the applicable regulations. In the tables, negative represents tailwind and
positive represents headwind.
• Gradient correction factors can be applied to gradients less than or equal to 2 percent
downhill or 2 percent uphill. In the tables, negative represents downhill gradients and positive
represents uphill gradients.
510FM-05 AA 4-7
SECTION IV - PERFORMANCE MODEL 510
GENERAL
FAA APPROVED
U.S. Configuration
DEFINITIONS
(Continued Next Page)
Accelerate-Stop Distance: The distance required to accelerate to V1, and abort the takeoff and
come to a complete stop with maximum braking applied at V1.
Airport Barometric Altitude: Indicated altitude with altimeter set to airport altimeter setting while at
airport elevation.
Altitude: All altitudes used in this manual are pressure altitudes unless
otherwise stated.
Anti-Ice: 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.
Calibrated Airspeed (KCAS): Indicated airspeed (knots) corrected for position error and assumes
zero instrument error.
Climb Gradient: The ratio of the change in height during a portion of a climb, to the
horizontal distance traversed in the same time interval.
Deice Systems: The wing, horizontal stabilizer, and tail deice system comprise the
deice system.
Demonstrated Crosswind: The demonstrated crosswind velocity of 25 knots, measured at 32.8
feet (10 meters) above the runway surface, is the velocity of the
crosswind component for which adequate control of the airplane
during takeoff and landing was actually demonstrated during
certification tests. This is not limiting.
Engine Out Accelerate-Go
Distance:
The horizontal distance from brake release to the point at which the
airplane attains a height of 35 feet above the runway surface, on a
takeoff during which an engine is recognized to have failed at V1 and
the takeoff is continued.
Gross Climb Gradient: The climb gradient that the airplane can actually achieve with ideal
ambient conditions (smooth air).
Gross Takeoff Flight Path: The takeoff flight path that the airplane can actually achieve under
ideal conditions.
Indicated Airspeed (KIAS): Airspeed indicator readings (knots). Zero instrument error is
assumed.
4-8 AA 510FM-07
MODEL 510 SECTION IV - PERFORMANCE
GENERAL
FAA APPROVED
Configuration U.S.
DEFINITIONS (Continued)
(Continued Next Page)
ISA: International Standard Atmosphere.
Landing Distance: The distance from a point 50 feet above the runway surface to the
point at which the airplane would come to a full stop on the runway.
Level Off Altitude: The barometric altitude at which second segment climb ends.
Mach Number: The ratio of true airspeed to the speed of sound.
Net Climb Gradient: The gross climb gradient reduced by 0.8% during the takeoff and
enroute phase.
Net Takeoff Flight Path: Takeoff flight path used to determine obstacle clearance. Uses net
climb gradients to climb to a height of 1500 feet above the runway
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Citation Mustang airplane flight manual 1(124)
