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6. For landing field length which can be used in showing compliance to Operational
requirements, determine the landing distance from 35 feet AGL to stop, VAPP and SVREF from
Figure S2-2. Increase the landing distance by the appropriate Operational factor. For
runways without an operative visual glidepath reference system, add 250 feet to the above
determined landing distance from Figure S2-2 and increase the total distance by the
appropriate Operational factor. This adjusted distance is from 50 feet AGL to stop. If the
runway has a gradient, apply the appropriate factor from the note below. If the available
runway length is less than the landing field length required, the airplane weight must be
reduced.
NOTE
Multiply landing field length by 1.12 for -1 percent (downhill) runway gradient, by
1.35 for -2 percent (downhill) runway gradient. No adjustment is necessary for a
positive (uphill) runway gradient.
7. For JAR Operations, Figure S2-3 can be used in showing compliance with JAR-OPS 1.515
(Landing - Dry Runways); determine the landing field length from 35 feet AGL to stop, VAPP
and SVREF from Figure S2-3. For runways without an operative visual glidepath reference
system, increase the landing field length by 410 feet. This adjusted distance is from 50 feet
AGL to stop. For landings on wet runways, refer to JAR-OPS 1.520. If the available runway
length is less than the landing field length required, the airplane weight must be reduced.
8. The approach climb gradients and the landing climb gradients are presented in Section IV,
PERFORMANCE, APPROACH AND LANDING.
NOTE
These procedures apply for normal landings at or below 8000 pounds. Performance
above 8000 pounds is provided as additional information for use in an emergency
which requires a landing at a weight in excess of the maximum design landing
weight of 8000 pounds.
S2-10 S2-AA 510FM-S2-00
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 2
FAA APPROVED
Configuration U.S.
MAXIMUM LANDING WEIGHT PERMITTED BY CLIMB
REQUIREMENTS OR BRAKE ENERGY LIMITS - POUNDS
APPROACH FLAPS - 15° LANDING FLAPS - LAND
The maximum allowable landing weight with Stall Warning NORMAL and for brake energy limits is
determined from Figure S2-1 for a given set of conditions.
EXAMPLE:
Ambient Temperature = 5°C From Figure S2-1, Maximum Weight = 7280 POUNDS
Pressure Altitude = 5000 FEET
Wind = -10 KNOTS (TAILWIND)
Runway Gradient = -2% (DOWNHILL)
510FM-S2-02 S2-AA S2-11
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 2
FAA APPROVED
U.S. Configuration
Figure S2-1 (Sheet 1 of 2)*
S2-12 S2-AA 510FM-S2-02
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 2
FAA APPROVED
Configuration U.S.
Figure S2-1 (Sheet 2)*
510FM-S2-02 S2-AA S2-13
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 2
FAA APPROVED
U.S. Configuration
Figure S2-2 (Sheet 1 of 6)*
S2-14 S2-AA 510FM-S2-02
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 2
FAA APPROVED
Configuration U.S.
Figure S2-2 (Sheet 2)*
510FM-S2-02 S2-AA S2-15
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 2
FAA APPROVED
U.S. Configuration
Figure S2-2 (Sheet 3)*
S2-16 S2-AA 510FM-S2-02
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 2
FAA APPROVED
Configuration U.S.
Figure S2-2 (Sheet 4)*
510FM-S2-02 S2-AA S2-17
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 2
FAA APPROVED
U.S. Configuration
Figure S2-2 (Sheet 5)*
S2-18 S2-AA 510FM-S2-02
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 2
FAA APPROVED
Configuration U.S.
Figure S2-2 (Sheet 6)*
510FM-S2-02 S2-AA S2-19
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 2
FAA APPROVED
U.S. Configuration
Figure S2-3 (Sheet 1 of 3)*
S2-20 S2-AA 510FM-S2-02
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 2
FAA APPROVED
Configuration U.S.
Figure S2-3 (Sheet 2)*
510FM-S2-02 S2-AA S2-21
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 2
FAA APPROVED
U.S. Configuration
Figure S2-3 (Sheet 3)*
S2-22 S2-AA 510FM-S2-02
U.S.
MODEL 510
510-0001 AND ON
SUPPLEMENT 3
CITATION PERFORMANCE CALCULATOR (CPCalc)
11 APRIL 2007
REVISION 5 13 NOVEMBER 2008 S3-1
COPYRIGHT © 2007
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
510FM-S3-05
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 3
FAA APPROVED
U.S. Configuration
SUPPLEMENT 3
CITATION PERFORMANCE CALCULATOR (CPCalc)
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Citation Mustang airplane flight manual 2(19)
