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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
Maximum Time to Light-off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Seconds
Maximum Time to Stabilized Idle (Ground or In-Flight/Starter Assist) . . . . . . . . . . . . . . . 45 Seconds
Maximum Time to Stabilized Idle (In-Flight/Windmilling) . . . . . . . . . . . . . . . . . . . . . . . . . 90 Seconds
NOTE
Time to light-off is defined as the time after the throttle lever is moved from CUTOFF
to IDLE detent and an increase in ITT is observed.
Minimum Engine Oil Temperature (as indicated on EICAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . -40°C
NOTE
• If engine oil temperature is below -40°C (-40°F), the engine must be preheated
prior to conducting a start.
• If the battery has been cold soaked for 2 hours or longer at ambient surface
temperature of -18°C (0°F) or lower, it must be preheated to above -18°C (0°F)
prior to start.
• The Engine Indicating System may take up to 10 minutes to become usable after
power is applied when cold soaked below -40°C (-40°F).
Maximum Temperature For Engine Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-13
Maximum Airport Elevation For Ground Battery Start. . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,000 Feet
Maximum Airport Elevation For Ground Power Unit Start . . . . . . . . . . . . . . . . . . . . . . . . 14,000 Feet
Minimum Battery Voltage For Battery Start. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 Volts
2-4.1 AC 510FM-07
MODEL 510 SECTION II - OPERATING LIMITATIONS
FAA APPROVED
Configuration U.S.
CENTER-OF-GRAVITY LIMITATIONS
Figure 2-1
510FM-06 AA 2-5
SECTION II - OPERATING LIMITATIONS MODEL 510
FAA APPROVED
U.S. Configuration
ENGINE OPERATING LIMITS
Figure 2-2
NOTE
1. The total time during which takeoff thrust may be used is limited to 5 minutes per
flight. The 5-minute time limit commences when the throttle is first advanced to the
TO detent. This time may be extended to 10 minutes for one engine inoperative
operation. The takeoff thrust (N1) for the airplane is defined in Figures 4-13 and 4-
14 and is more limiting than engine rotational limits and must be observed.
Performance data including VMCA and VMCG in Section IV, is based on use of the
appropriate takeoff thrust setting.
2. Maximum continuous thrust (CLB detent) for the airplane is defined by Figures
4-15 and 4-16 (single-engine) and Figures 4-17 and 4-18 (multi-engine). These
thrust settings (N1) are more limiting than engine rotational limits and must be
observed. Performance data in Section IV is based on the use of the appropriate
maximum continuous thrust setting.
3. Oil temperature must be above 22°C for at least 5 minutes before takeoff. Once oil
temperature is +10°C or warmer, it is acceptable to increase power-up to the CRU
detent to decrease the time required to warm the oil to 22°C.
4. Idle speed is a function of ambient pressure and temperature.
5. After initiation of the start cycle, oil pressure should indicate a steady increase
within 20 seconds of the start of N2 rotation.
OPERATING
CONDITION OPERATING LIMITS
　
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