MODEL 510 SECTION IV - PERFORMANCE
APPROACH AND LANDING
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, Limitations.
3. Determine wind component parallel to active runway from the crosswind component chart
(Figure 4-20).
4. Check the maximum landing weight permitted by climb requirements and brake energy
limits (Figure 4-55 for Stall Warning-NORMAL, Figure 4-56 for Stall Warning-HIGH). If these
limitations restrict the landing weight, fuel must be burned-off prior to landing.
5. Landing with Stall Warning-NORMAL use Figure 4-57 (Flaps 15° approach, Flaps LAND
land). With Stall Warning-HIGH use Figure 4-58 (Flaps 15° approach, Flaps 15° land).
Determine the landing distance, VAPP and VREF from Figure 4-57 (Stall Warning-NORMAL)
or from Figure 4-58 (Stall Warning-HIGH), 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 4-57 (Stall Warning-NORMAL)
or Figure 4-58 (Stall Warning-HIGH) by the appropriate factor shown in the table
below:
• For positive (uphill) runway gradients, use the landing distance obtained from
Figure 4-57 (Stall Warning-NORMAL) or Figure 4-58 (Stall Warning-HIGH).
• For inoperative antiskid system, multiply the Stall Warning-NORMAL landing
distance obtained from Figure 4-57 by 1.39, and reduce weight determined from
Figure 4-55 by 180 lbs when landing on a runway with a downhill gradient. For
Stall Warning-HIGH landing distance with inoperative antiskid system, refer to
ABNORMAL PROCEDURES - ANTISKID FAIL.
6. The approach climb and landing climb gradient tables are presented in Figures 4-59
through 4-64.
NOTE
These procedures apply for normal landings at or below 8000 pounds. Performance
above 8000 pounds is provided as additional information.
510FM-05 AA 4-229
SECTION IV - PERFORMANCE MODEL 510
APPROACH AND LANDING
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 4-55 (Stall Warning-NORMAL) or
Figure 4-56 (Stall Warning-HIGH) for a given set of conditions.
EXAMPLE: Stall Warning-HIGH
Pressure Altitude = 5000 FEET From Figure 4-56, Maximum Weight = 7950 POUNDS
Ambient Temperature = -10°C
Wind = 10 KNOTS (HEADWIND)
Runway Gradient = 1% (UPHILL)
4-230 AA 510FM-05
MODEL 510 SECTION IV - PERFORMANCE
APPROACH AND LANDING
FAA APPROVED
Configuration U.S.
Figure 4-55 (Sheet 1 of 5)*
510FM-05 AA 4-231
SECTION IV - PERFORMANCE MODEL 510
APPROACH AND LANDING
FAA APPROVED
U.S. Configuration
Figure 4-55 (Sheet 2)*
4-232 AA 510FM-05
MODEL 510 SECTION IV - PERFORMANCE
APPROACH AND LANDING
FAA APPROVED
Configuration U.S.
Figure 4-55 (Sheet 3)*
510FM-05 AA 4-233
SECTION IV - PERFORMANCE MODEL 510
APPROACH AND LANDING
FAA APPROVED
U.S. Configuration
Figure 4-55 (Sheet 4)*
4-234 AA 510FM-05
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