MODEL 510 SECTION II - OPERATING LIMITATIONS
FAA APPROVED
Configuration U.S.
OPERATING LIMITATIONS
CERTIFICATION STATUS
This airplane is certified in accordance with 14 CFR, Part 23 Normal Category, Part 34 (Fuel Venting
and Exhaust Emissions), Part 36 (Noise Requirements) and Special Conditions as prescribed by the
Administrator.
OPERATIONS AUTHORIZED
This airplane is approved for day and night, VFR and IFR operations, and flight into known icing
conditions when the required equipment is installed as defined within the Kinds of Operations
Equipment List.
This airplane is approved for operations in Reduced Vertical Separation Minimum (RVSM) airspace
when required equipment is maintained in accordance with the airplane Maintenance Manual. This
does not constitute operational approval. Operational approval must be obtained in accordance with
applicable operating rules.
Acrobatic maneuvers, including spins, are prohibited. Intentional stalls are prohibited above 18,000
feet.
WEIGHT LIMITATIONS
Maximum Design Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8730 Pounds
Maximum Design Takeoff Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8645 Pounds
Maximum Design Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8000 Pounds
Maximum Design Zero Fuel Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6750 Pounds
Minimum Weight in RVSM Airspace . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6300 Pounds
Takeoff weight is limited by the most restrictive of the following requirements:
Maximum Certified Takeoff Weight (Flaps - TAKEOFF/APPROACH). . . . . . . . . . . . 8645 Pounds
Maximum Takeoff Weight Permitted by
Climb Requirements. . . . . . . . . . . . . . . . . . . . . . Refer to Section IV, Performance, TAKEOFF
Takeoff Field Length . . . . . . . . . . . . . . . . . . . . . . . . Refer to Section IV, Performance, TAKEOFF
Landing weight is limited by the most restrictive of the following requirements:
Maximum Certified Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8000 Pounds
Maximum Landing Weight Permitted by Climb Requirements
or Brake Energy Limits. . . . . Refer to Section IV, Performance, APPROACH AND LANDING
Landing Distance . . . . . . . . . . . Refer to Section IV, Performance, APPROACH AND LANDING
NOTICE
CERTIFICATION AND OPERATIONAL LIMITATIONS ARE CONDITIONS OF THE TYPE AND
AIRWORTHINESS CERTIFICATES AND MUST BE COMPLIED WITH AT ALL TIMES AS
REQUIRED BY LAW.
510FM-07 AA 2-3
SECTION II - OPERATING LIMITATIONS MODEL 510
FAA APPROVED
U.S. Configuration
CENTER-OF-GRAVITY LIMITATIONS
Center-of-Gravity Moment Envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-1
WEIGHT AND BALANCE DATA
The airplane must be operated in accordance with the approved loading schedule. Refer to the
Model 510 Weight and Balance Manual (510WB-00 or latest revision).
POWERPLANT LIMITATIONS
Engine Type . . . . . . . . . . . . . . . . . . . . . . . . . . . Pratt and Whitney Canada Inc. PW615F-A Turbofan
Engine Operating Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-2
Engine Inter-Turbine Temperature (ITT) Limits. . . . . . . . . . . . . . . . . . . . Refer to Figures 2-3 and 2-4
Engine Overspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figures 2-5 and 2-6
Engine Oil Pressure Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-7
Takeoff/Go-Around Thrust (TO Detent). . . . . . . . . . . . . . . . . . . . . . . . Refer to Figures 4-13 and 4-14
Maximum Continuous Thrust, Single-Engine (CLB Detent) . . . . . . . . Refer to Figures 4-15 and 4-16
Maximum Continuous Thrust, Multi-Engine (CLB Detent) . . . . . . . . . Refer to Figures 4-17 and 4-18
ENGINE START LIMITATIONS
Inter-Turbine Temperature (ITT) Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-3
Maximum Tailwind Component. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10 Knots
Maximum Quartering Tailwind (Within Tailwind Component Limits) . . . . . . . . . . . . . . . . . . . .15 Knots
Maximum Crosswind Component. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .25 Knots
　
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