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Operating Limitations

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Operating Limitations SECTION I MODEL 680 DESCRIPTION AND SPECIFICATIONS OPERATING LIMITATIONS 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. GENERAL The Limitations presented in this section focus primarily on the operational capabilities of the airplane. Specific system limitations and instrument markings are presented in this section. CERTIFICATION STATUS The Citation Sovereign is certified in accordance with 14 CFR Part 25 (to Amendment 98). WEIGHT LIMITATIONS Maximum Design Ramp Weight . 30,250 Pounds Maximum Design Takeoff Weight . 30,000 Pounds Maximum Design Landing Weight . 27,100 Pounds Maximum Design Zero Fuel Weight . 20,300 Pounds Minimum Flight Weight . 17,345 Pounds Maximum Tailcone Baggage Weight . 1,000 Pounds Takeoff weight is limited by the most restrictive of the following requirements: Maximum Certified Takeoff Weight (Flaps 7° or 15°) . 30,000 Pounds Maximum Takeoff Weight Permitted by Climb Requirements . Refer to Section IV, Performance, TAKEOFF in the AFM Takeoff Field Length . Refer to Section IV, Performance, TAKEOFF in the AFM Landing weight is limited by the most restrictive of the following requirements: Maximum Certified Landing Weight . 27,100 Pounds Maximum Landing Weight Permitted by Climb Requirements or Brake Energy Limit . Refer to Section IV, Performance, TAKEOFF AND LANDING in the AFM Landing Distance . Refer to Section IV, Performance, TAKEOFF AND LANDING in the AFM I68OM-01 Configuration AB 1-11 SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 680 Figure 1-3 1-12 Configuration AA 68OM-00 SECTION I MODEL 680 DESCRIPTION AND SPECIFICATIONS OPERATING LIMITATIONS 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. GENERAL The Limitations presented in this section focus primarily on the operational capabilities of the airplane. Specific system limitations and instrument markings are presented in this section. CERTIFICATION STATUS The Citation Sovereign is certified in accordance with 14 CFR Part 25 (to Amendment 98). WEIGHT LIMITATIONS Maximum Design Ramp Weight . 30,250 Pounds Maximum Design Takeoff Weight . 30,000 Pounds Maximum Design Landing Weight . 27,100 Pounds Maximum Design Zero Fuel Weight . 20,300 Pounds Minimum Flight Weight . 17,345 Pounds Maximum Tailcone Baggage Weight . 1,000 Pounds Takeoff weight is limited by the most restrictive of the following requirements: Maximum Certified Takeoff Weight (Flaps 7° or 15°) . 30,000 Pounds Minimum Certified Takeoff Weight (Flaps 7°) . 27,000 Pounds Maximum Takeoff Weight Permitted by Climb Requirements . Refer to Section IV, Performance, TAKEOFF in the AFM Takeoff Field Length . Refer to Section IV, Performance, TAKEOFF in the AFM Landing weight is limited by the most restrictive of the following requirements: Maximum Certified Landing Weight . 27,100 Pounds Maximum Landing Weight Permitted by Climb Requirements or Brake Energy Limit . Refer to Section IV, Performance, TAKEOFF AND LANDING in the AFM Landing Distance . Refer to Section IV, Performance, TAKEOFF AND LANDING in the AFM I68OM-01 Configuration AC 1-11.1 SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 680 Figure 1-3 1-12 Configuration AA 68OM-00 SECTION I MODEL 680 DESCRIPTION AND SPECIFICATIONS CENTER OF GRAVITY LIMITATIONS Center of Gravity Moment Envelope . Refer to Figure 1-3 WEIGHT AND BALANCE DATA The airplane must be operated in accordance with the approved loading schedule. Refer to Weight and Balance Data Sheet and FAA Approved Citation Sovereign Weight and Balance Manual. PERFORMANCE CONFIGURATION The airplane configuration must be as presented in Section IV, Performance, Standard Performance Conditions of the AFM. POWERPLANT LIMITATIONS Engine Type . Pratt and Whitney Canada Inc. PW306C Turbofan (producing 5770 lbs. thrust at sea level up to 87°F) Figure 1-4 illustrates the engine operating limits for time, temperature, RPM, oil pressure and oil temperature under the selected operating conditions. Figure 1-5 illustrates the engine overtemperature limits. Figure 1-6 illustrates the engine overspeed limits. Continuous static-ground operation of the engine at takeoff thrust is limited to a maximum of two minutes. FADEC (FULL AUTHORITY DIGITAL ENGINE COMPUTERS) Dispatch with an engine FADEC channel inoperative is prohibited. Exceeding the time interval for a cyan ENGINE DISPATCH LIMIT L-R CAS message is prohibited. Both air data systems must be operational for dispatch. 68OM-00 Configuration AA 1-13 SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 680 ENGINE OPERATING LIMITS OPERATING CONDITION OPERATING LIMITS MAX OIL OBSERVED N2 N1 PRESSURE OIL TEMP THRUST TIME LIMIT ITT PSI °C SETTING (MINUTES) °C % % (NOTE 2) 5 TAKEOFF 920 105 105 36 TO 110 16 TO 135 (TO DETENT) (NOTE 1) MAXIMUM CONTINUOUS CONTINUOUS 920 105 105 36 TO 110 16 TO 135 (MCT DETENT) MAXIMUM 920 105 105 36 TO 110 16 TO 135 CRUISE CONTINUOUS (NOTE 3) (CRU DETENT) 5 REVERSE (NOTE 8) 920 105 105 36 TO 110 16 TO 135 THRUST >> 57 (MIN) >> GROUND CONTINUOUS (NOTE 4) 20 TO 110 16 TO 135 IDLE (NOTE 6) 65 (MIN) 16 TO 135 FLIGHT CONTINUOUS >> >> 20 TO 110 IDLE (NOTE 4) (NOTE 6) 950 STARTING >> (SEE FIG >> >> 0 TO 220 -40 (MIN) 1-5) (NOTE 5) (NOTE 3) 950 >> 20 SECONDS (SEE FIG 106 106 0 TO 20 TRANSIENT 1-5) 90 SECONDS >> >> >> 110 TO 220 135 TO 143 Figure 1-4 1. The total time during which takeoff thrust may be used is limited to five minutes per flight. The five 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. 2. The normal differential oil pressure is 36 PSI to 110 PSI. Oil pressure less than 36 PSI but greater than or equal to 20 PSI is acceptable when the throttles are set to less than CRU detent. Operation at a steady state oil pressure below 20 PSI could result in engine damage. 3. After completing a start under cold conditions and achieving a stabilized ground idle, it is acceptable to run the engine up to the CRU detent in order to reduce the time required for the oil to reach the minimum operating temperature of 16°C. 4. Idle speed is a function of ambient pressure. 5. After initiation of the start cycle, oil pressure should indicate a steady increase within 20 seconds of the start of N2 rotation. 6. Oil temperature may be less than 16°C after a start and before oil temperature has stabilized. 7. To preclude low oil pressure, intentional uncoordinated flight of greater than one slip/skid indicator bar width for longer than 20 seconds is prohibited. 8. After two minutes with the thrust reversers deployed, the throttle quadrant solenoid de- energizes and limits thrust reverser lever movement to idle or stowed. Returning the thrust reverser levers to stowed re-energizes the throttle quadrant solenoid. 1-14 Configuration AA 68OM-00 SECTION I MODEL 680 DESCRIPTION AND SPECIFICATIONS OVERTEMPERATURE LIMITS (STARTING) AREA A - NO ACTION REQUIRED AREA B (1) DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (2) PERFORM VISUAL INSPECTION (3) RECORD IN ENGINE LOG BOOK AREA C - REFER TO MAINTENANCE MANUAL Figure 1-5 (Sheet 1 of 2) 68OM-00 Configuration AA 1-15 SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 680 OVERTEMPERATURE LIMITS (EXCEPT STARTING) NOTE Interturbine temperatures shown make no allowance for correction factors or instrument errors but do allow for some typical instrument lag. AREA A - NO ACTION REQUIRED AREA B - IF AT TAKEOFF - NO ACTION REQUIRED - ALL OTHER POWER SETTINGS: (1) DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (2) PERFORM HOT SECTION INSPECTION (3) RECORD IN ENGINE LOG BOOK AREA C - (1) DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (2) PERFORM HOT SECTION INSPECTION (3) RECORD IN ENGINE LOG BOOK AREA D - REFER TO MAINTENANCE MANUAL Figure 1-5 (Sheet 2) 1-16 Configuration AA 68OM-00 SECTION I MODEL 680 DESCRIPTION AND SPECIFICATIONS ENGINE OVERSPEED LIMITS AREA A - NO ACTION REQUIRED AREA B - REFER TO MAINTENANCE MANUAL Figure 1-6 68OM-00 Configuration AA 1-17 SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 680 APPROVED OILS The following oils are approved for use: MOBIL JET OIL II BP TURBO OIL 2380 AEROSHELL TURBINE OIL 500 MOBIL JET OIL 254 ROYCO TURBINE OIL 500 AEROSHELL TURBINE OIL 560 CASTROL 5000 In addition, oils listed for the engine in the latest revision to PW306C Maintenance Manuals (P/N 30B4422) are approved. CAUTION WHEN CHANGING FROM AN EXISTING LUBRICANT FORMULATION TO A “THIRD GENERATION” LUBRICANT FORMULATION (AEROSHELL TURBINE OIL 560 OR MOBIL JET 254), THE ENGINE MANUFACTURER STRONGLY RECOMMENDS THAT SUCH A CHANGE SHOULD ONLY BE MADE WHEN AN ENGINE IS NEW OR FRESHLY OVERHAULED. FOR ADDITIONAL INFORMATION ON USE OF THIRD GENERATION OILS, REFER TO ENGINE MANUFACTURER’S PERTINENT OIL SERVICE BULLETINS. Maximum oil consumption is 1 quart per 8 hour period. When oil consumption is greater than 1 quart per 8 hour period, refer to the aircraft maintenance manual. Oil types or brands may not be mixed unless specifically approved in the PW306C Maintenance Manuals. START CYCLE LIMITATIONS Engine Starter Limitation . The rest periods between engine starts is 2 minutes after the first start attempt, 5 minutes after the second, and 30 minutes after the third. NOTE This limitation is independent of starter power source (i.e., battery, generator assisted cross start, auxiliary power unit, or external power unit) and applies to dry and wet motoring of the engine. Engine Starter Motoring Limitation (not engine start) . Batteries only . 20 seconds Batteries with generator assist . 15 seconds External Power (1000 amps) . 15 seconds External Power (1500 amps) . 7 seconds 1-18 Configuration AA 68OM-00 SECTION I MODEL 680 DESCRIPTION AND SPECIFICATIONS APU Starter Limitation . Three APU start cycles per 30 minutes. Three cycles with a 90-second rest period between cycles is permitted.
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