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SUPPLEMENT 6
FAA APPROVED
Configuration U.S.
Figure S6-2 (Sheet 1 of 6)
510FM-S6-00 S6-AA S6-9
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 6
FAA APPROVED
U.S. Configuration
Figure S6-2 (Sheet 2)
S6-10 S6-AA 510FM-S6-00
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 6
FAA APPROVED
Configuration U.S.
Figure S6-2 (Sheet 3)
510FM-S6-00 S6-AA S6-11
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 6
FAA APPROVED
U.S. Configuration
Figure S6-2 (Sheet 4)
S6-12 S6-AA 510FM-S6-00
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 6
FAA APPROVED
Configuration U.S.
Figure S6-2 (Sheet 5)
510FM-S6-00 S6-AA S6-13
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 6
FAA APPROVED
U.S. Configuration
Figure S6-2 (Sheet 6)
S6-14 S6-AA 510FM-S6-00
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 6
FAA APPROVED
Configuration U.S.
PROCEDURES FOR USE OF APPROACH AND LANDING
PERFORMANCE TABLES
1. Determine gross weight of airplane at the time of arrival at the destination airport.
2. Obtain airport information; i.e., active runway, available runway length, ambient temperature
(TEMP), altitude, wind, icing conditions and runway gradient if applicable. Determine that
the temperature is within the ambient temperature limits found in Section II, OPERATING
LIMITATIONS.
3. Determine the wind component parallel to the active runway from the Crosswind
Component chart in Section IV, PERFORMANCE, STANDARD CHARTS.
4. Check the maximum landing weight permitted by climb requirements and brake energy
limits from Figure S6-3. If these limitations restrict the landing weight, fuel must be burnedoff
prior to landing.
5. Determine the landing distance, VAPP and VREF from Figure S6-4, then apply the
appropriate factors from the note below. If the available runway length is less than the
landing distance required, the airplane landing weight must be reduced.
NOTE
• Multiply the landing distance obtained from Figure S6-4 by the appropriate factor
shown in the table below:
• For positive (uphill) runway gradients, use the landing distance obtained from
Figure S6-4.
6. The Approach Gross Climb Gradient - Percent and Landing Gross Climb Gradient - Percent
tables 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.
510FM-S6-00 S6-AA S6-15
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 6
FAA APPROVED
U.S. Configuration
MAXIMUM LANDING WEIGHT PERMITTED BY CLIMB
REQUIREMENTS OR BRAKE ENERGY LIMITS
The maximum allowable landing weight is determined from Figure S6-3 for a given set of conditions.
EXAMPLE:
Pressure Altitude = 4000 FEET From Figure S6-3, Maximum Weight = 7920 POUNDS
Ambient Temperature = 35°C
Wind = 10 KNOTS (HEADWIND)
Runway Gradient = 1% (UPHILL)
S6-16 S6-AA 510FM-S6-00
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 6
FAA APPROVED
Configuration U.S.
Figure S6-3 (Sheet 1 of 2)
510FM-S6-00 S6-AA S6-17
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 6
FAA APPROVED
U.S. Configuration
Figure S6-3 (Sheet 2)
S6-18 S6-AA 510FM-S6-00
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 6
FAA APPROVED
Configuration U.S.
Figure S6-4 (Sheet 1 of 6)
510FM-S6-00 S6-AA S6-19
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 6
FAA APPROVED
U.S. Configuration
Figure S6-4 (Sheet 2)
S6-20 S6-AA 510FM-S6-00
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 6
FAA APPROVED
Configuration U.S.
Figure S6-4 (Sheet 3)
510FM-S6-00 S6-AA S6-21
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 6
FAA APPROVED
U.S. Configuration
Figure S6-4 (Sheet 4)
S6-22 S6-AA 510FM-S6-00
MODEL 510 SECTION V - SUPPLEMENTS
SUPPLEMENT 6
FAA APPROVED
Configuration U.S.
Figure S6-4 (Sheet 5)
510FM-S6-00 S6-AA S6-23
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 6
FAA APPROVED
U.S. Configuration
Figure S6-4 (Sheet 6)
S6-24 S6-AA 510FM-S6-00
U.S.
MODEL 510
510-0001 AND ON
SUPPLEMENT 7
HONEYWELL KTA 870
TRAFFIC ADVISORY SYSTEM (TAS)
3 JULY 2007
REVISION 1 21 NOVEMBER 2008 S7-1
COPYRIGHT © 2008
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
510FM-S7-01
.
SECTION V - SUPPLEMENTS MODEL 510
SUPPLEMENT 7
FAA APPROVED
U.S. Configuration
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Citation Mustang airplane flight manual 3(7)
