OPERATING LIMITATIONS TABLE OF CONTENTS

Transcription

1 MODEL 680A OPERATING LIMITATIONS TABLE OF CONTENTS SECTION II - OPERATING LIMITATIONS TABLE OF CONTENTS Page OPERATING LIMITATIONS General Certification Status Weight Limits Center-of-Gravity Limits Weight and Balance Data Performance Configuration Fuel Limits Unusable Fuel Single-Point Refueling Takeoff and Landing Operational Limits Enroute Operational Limits Takeoff/Landing/Enroute Temperature Limits Reduced Vertical Separation Minimum Approved Oils Engine Limits Start Cycle Limits External Power Limits for Starting Minimum Crew Speed Limits Operations Authorized Load Factor Maneuver Limits Maximum Allowable Flight Time to a Suitable Airport Electrical Power Systems Auxiliary Power Unit (APU) Full Authority Digital Engine Control (FADEC) Hydraulic Power System Ice and Rain Protection Operations in Severe Icing Boundary Layer Energizers Cabin Pressurization Limits Passenger Compartment Baggage Compartment EIS and Instrument Markings Supplemental Oxygen System Thrust Reversers Angle-of-Attack and Stick Shaker System Standby Flight Display (Continued Next Page) U.S

2 SECTION II - OPERATING LIMITATIONS TABLE OF CONTENTS TABLE OF CONTENTS (Continued) MODEL 680A Page Garmin G5000 Avionics System - General (Software ) Synthetic Vision Technology (SVT) Automatic Flight Control System (AFCS) G5000 Flight Management System FMS Navigation Operational Capabilities Traffic Collision Avoidance System (TCAS II) Terrain Awareness and Warning System (TAWS-A) SafeTaxi HF Radio Electronic Navigation Charts Radar System Datalink Weather Controller/Pilot Datalink Communications (CPDLC) U.S.

3 MODEL 680A SECTION II - OPERATING LIMITATIONS 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 limits presented in this section focus primarily on the operational capabilities of the airplane. Specific system limits and instrument markings are presented in this section. CERTIFICATION STATUS This Citation Latitude is certified in accordance with 14 CFR Part 25. WEIGHT LIMITS 1. Weight Envelope Refer to Figure Maximum Design Ramp Weight ,050 Pounds 3. Maximum Design Takeoff Weight ,800 Pounds 4. Maximum Design Landing Weight ,575 Pounds 5. Maximum Design Zero Fuel Weight ,200 Pounds 6. Maximum Tailcone Baggage Weight Pounds 7. Takeoff weight is limited by the most restrictive of the following requirements: a. Maximum Certified Takeoff Weight ,800 Pounds b. Maximum Takeoff Weight Permitted by Climb Requirements Refer to Section IV, Performance, TAKEOFF c. Takeoff Field Length Refer to Section IV, Performance, TAKEOFF 8. Landing weight is limited by the most restrictive of the following requirements: a. Maximum Certified Landing Weight ,575 Pounds b. Maximum Landing Weight Permitted by Climb Requirements or Brake Energy Limits Refer to Section IV, Performance, LANDING c. Landing Distance Refer to Section IV, Performance, LANDING U.S

4 SECTION II - OPERATING LIMITATIONS MODEL 680A CENTER-OF-GRAVITY LIMITS Center-of-Gravity Moment Envelope Refer to Figure Figure U.S.

5 MODEL 680A SECTION II - OPERATING LIMITATIONS WEIGHT AND BALANCE DATA The airplane must be operated in accordance with the approved loading schedule. Refer to Weight and Balance Data Sheet and Section VI. PERFORMANCE CONFIGURATION The airplane configuration must be as presented in Section IV, Performance, STANDARD PERFORMANCE CONDITIONS. U.S

6 SECTION II - OPERATING LIMITATIONS MODEL 680A FUEL LIMITS 1. The corresponding electric fuel boost pump must be turned ON when the amber FUEL LEVEL LOW L and/or R CAS message is displayed or at 600 pounds or less of indicated fuel in either tank. 2. Figures , and list the fuel temperature limits for the fuels approved for use in the Citation Latitude. FUEL LIMITS JET A JET A-1. JP-5 & JP-8 JET-B, JP-4 TS-1, RT, NO.3**** MINIMUM FUEL TEMPERATURE -35C -40C ** *** MAXIMUM FUEL TEMPERATURE FOR ENGINE START AND TAKEOFF MAXIMUM OPERATING FUEL TEMPERATURE +57C +57C ** *** +61C +61C ** *** MAXIMUM ALTITUDE FL450 FL450 ** *** MAXIMUM ASYMMETRIC FUEL DIFFERENTIAL FOR NORMAL OPERATIONS* 400 POUNDS 400 POUNDS 400 POUNDS 400 POUNDS * A LATERAL FUEL IMBALANCE OF 800 POUNDS HAS BEEN DEMONSTRATED FOR EMERGENCY RETURN. ** REFER TO FIGURE *** REFER TO FIGURE **** REFER TO THE PW306D1 MAINTENANCE MANUAL FOR INSPECTION AND MAINTENANCE CRITERIA WHEN OPERATING WITH TS-1 FUEL. Figure NOTE Use of fuel additives is not required. Refer to Section III, Operating Information, Anti-Ice Additives and the Maintenance Manual for fuel system additves, concentrations and blending instructions. The fuel tank temperature indication on EIS remains white for all displayed fuel temperatures U.S.

7 MODEL 680A SECTION II - OPERATING LIMITATIONS FUEL LIMITS (Continued) FOREIGN FUELS (TS-1, RT, NO.3) Figure U.S

8 SECTION II - OPERATING LIMITATIONS MODEL 680A FUEL LIMITS (Continued) JET-B/JP-4 Figure U.S.

9 MODEL 680A SECTION II - OPERATING LIMITATIONS UNUSABLE FUEL Unusable fuel is the fuel remaining in the fuel tanks when the fuel quantity indicator reads zero. This fuel is not usable in flight. SINGLE-POINT REFUELING 1. Single-point refueling operations must be accomplished per the procedures contained on the placard installed on the single-point refueling access door. 2. Refueling Pressure Range to 55 PSI 3. Defueling Pressure Range to -10 PSI TAKEOFF AND LANDING OPERATIONAL LIMITS 1. Maximum Altitude Limit < 8000 Feet 2. Maximum Tailwind Component Knots 3. Maximum Ambient Temperature Refer to Figure A satisfactory preflight check of each of the following systems must be accomplished in accordance with Section III, Normal Procedures, prior to takeoff, unless the associated system or component has been deferred per an approved Minimum Equipment List (MEL): a. ANTI-ICE PITOT/STATIC buttons and associated white P/S COLD CAS messages b. Static ports and surrounding fuselage skin c. Pitot Tubes (left, right, and standby) d. Primary stabilizer trim and associated amber AP STAB TRIM INOP CAS message e. GTC Systems Test and Auto Test f. Autopilot engage and disengage check g. Bleed Air Systems h. Crew Oxygen Masks i. ANTI-ICE WING XFLOW button and associated white A/I WING XFLOW OPEN CAS message (for operations in icing conditions) j. Angle of Attack and Stall Warning Systems k. Standby Flight Display Pre-Flight Test l. Rudder Bias System 5. The stabilizer trim must be set for takeoff in accordance with Figure PASS OXY selector must be set to AUTO prior to takeoff if carrying passengers. 7. The autopilot and yaw damper must be disengaged for takeoff and landing. 8. The lavatory doors must be latched open for takeoff and landing. 9. Takeoff and landings are limited to paved runway surfaces. 10. Except where otherwise specified by AFM procedure, speedbrakes must be stowed prior to 500 feet AGL for landing. (Continued Next Page) U.S

10 SECTION II - OPERATING LIMITATIONS MODEL 680A TAKEOFF AND LANDING OPERATIONAL LIMITS (Continued) 11. Takeoff may not be initiated with a red message displayed. Takeoff may not be initiated with an amber message displayed unless the associated system or component has been deferred per an approved Minimum Equipment List (MEL). Takeoff may not be initiated with a white message if the procedure asociated with that message requires MEL action, unless that system or component has been deferred per the MEL. When dispatching in this manner, if the procedure associated with the message includes "Land as soon as practical" as a step, the step may be ignored. 12. Takeoff is prohibited with the following forms of contamination: a. With frost adhering to the following critical areas: (1) Wing Leading Edge (2) Upper Wing Surface (3) Windshield b. With ice, snow or slush adhering to the following critical areas: (1) Wing Leading Edge and Upper Wing Surface (2) Flight Control Surfaces including all hinge gaps (3) Horizontal Stabilizer (4) Vertical Stabilizer (5) Engine Inlets (6) Top of Engine Pylons (7) Top of Fuselage (8) Windshield (9) All Static Ports (10) Angle-of-Attack Vanes (11) Upper surface of nose forward of the windshield NOTE Refer to Section VII, Advisory Information, for information regarding Ground Deicing and Anti-icing procedures. 13. Takeoff is limited to the Flaps 1 configuration when Type II, III, or IV anti-ice fluid has been applied to the airplane. 14. A visual and tactile (hand on surface) check of the wing leading edge and the wing upper surface must be performed to ensure the wing is free from frost, ice, snow, or slush when the outside air temperature is less than +6 C or if it cannot be determined that the wing fuel temperature is above 0 C and: a. There is visible moisture present (rain, drizzle, sleet, snow, fog, etc.); or b. Water is present on the wing upper surface; or c. The difference between the dew point and the outside temperature is 3 C or less; or d. The atmospheric conditions have been conducive to frost formation U.S.

11 MODEL 680A SECTION II - OPERATING LIMITATIONS ENROUTE OPERATIONAL LIMITS 1. Maximum Operating Altitude FL450 NOTE For operations above FL410, the following conditions must be met: Both ENG BLD AIR selectors must be selected to NORM or HP and both engine bleed air sources must be available. The PRESS SOURCE selector must be selected to NORM. 2. Maximum Altitude with Flaps Extended FL Maximum Ambient Temperature Refer to Figure Minimum Ambient Temperature Refer to Figure a. When the airplane has been exposed to prolonged ground temperatures below -30 C, the cabin must be warmed to at least -21 C as indicated on MFD GTC Home > Aircraft Systems > Temp page before flight above FL250 with any occupants in the passenger cabin. U.S

12 SECTION II - OPERATING LIMITATIONS MODEL 680A TAKEOFF/LANDING/ENROUTE TEMPERATURE LIMITS Figure NOTE For operations below -10 C, refer to Section III, Operating Information, Extreme Cold Weather Operations U.S.

13 MODEL 680A SECTION II - OPERATING LIMITATIONS REDUCED VERTICAL SEPARATION MINIMUM This airplane is not approved for operations in Reduced Vertical Separation Minimum (RVSM) airspace. U.S

14 SECTION II - OPERATING LIMITATIONS MODEL 680A This Page Intentionally Left Blank U.S.

15 MODEL 680A SECTION II - OPERATING LIMITATIONS APPROVED OILS 1. 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 PW306D1 Maintenance Manuals (P/N 30B ) are approved. CAUTION When changing from an existing lubricant formulation to a third generation lubricant formulation (Aeroshell Turbine Oil 560 or Mobil Jet Oil 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. 2. Maximum oil consumption is 1 quart per 8 flight hours. 3. Oil types or brands may not be mixed unless specifically approved in the PW306D1 Maintenance Manuals. POWERPLANT LIMITS 1. Engine Type Pratt and Whitney Canada Inc. PW306D1 Turbofan 2. Figure illustrates the engine operating limits for time, temperature, RPM, oil pressure and oil temperature under the selected operating conditions. Figures and illustrate the engine overtemperature limits. Figure illustrates the engine overspeed limits. 3. Continuous ground static operation of the engine at takeoff thrust is limited to a maximum of 2 minutes. 4. Attempting an engine start is prohibited with a tailwind component greater than 10 knots. When starting with a quartering tailwind, the downwind engine must be started first and the airplane turned into the wind prior to starting the second engine. 5. The engine must be operated at idle for at least 2 minutes prior to shutdown. Small thrust increases for taxi are acceptable. 6. To preclude low oil pressure, intentional uncoordinated flight of greater than one slip/skid indicator bar width for longer than 20 seconds is prohibited. U.S

16 SECTION II - OPERATING LIMITATIONS MODEL 680A. OPERATING CONDITION THRUST SETTING TAKEOFF (TO) MAXIMUM CONTINUOUS (MCT) MAXIMUM CRUISE (CRU) REVERSE THRUST TIME LIMIT (MINUTES) 5 (NOTE 1) ENGINE OPERATING LIMITS MAX OBSERVED ITT C N2 % OPERATING LIMITS N1 % OIL PRESSURE PSI (NOTE 2) OIL TEMP C TO TO 135 CONTINUOUS TO TO 135 CONTINUOUS TO 110 GROUND IDLE CONTINUOUS --- FLIGHT IDLE CONTINUOUS --- STARTING --- TRANSIENT 16 TO 135 (NOTE 3) TO TO SECONDS 950 (REFER TO FIGURE ) 950 (REFER TO FIGURE ) 57 (MIN) (NOTE 4) 65 (MIN) (NOTE 4) TO TO TO 220 (NOTE 5) 16 TO 135 (NOTE 6) 16 TO 135 (NOTE 6) -40 (MIN) (NOTE 3) TO SECONDS TO TO 143 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 increased to TO. 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 82% N1. Operation at a steady state oil pressure below 20 PSI can 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 82% N1 to decrease the time required for the oil to reach the minimum operating temperature of 16 C. 4. Idle speed is a function of ambient temperature and pressure. 5. After initiation of the start cycle, oil pressure must indicate an increase within 20 seconds of engine light up indicated by a rise in ITT. 6. Oil temperature may be less than 16 C after a start and before oil temperature has stabilized. Figure U.S.

17 MODEL 680A SECTION II - OPERATING LIMITATIONS OVERTEMPERATURE LIMITS (STARTING) ) AREA A - NO ACTION REQUIRED AREA B - REFER TO MAINTENANCE MANUAL AREA C - REFER TO MAINTENANCE MANUAL Figure U.S

18 SECTION II - OPERATING LIMITATIONS MODEL 680A 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 THRUST SETTINGS - REFER TO MAINTENANCE MANUAL AREA C- REFER TO MAINTENANCE MANUAL AREA D- REFER TO MAINTENANCE MANUAL Figure U.S.

19 MODEL 680A SECTION II - OPERATING LIMITATIONS ENGINE OVERSPEED LIMITS AREA A - NO ACTION REQUIRED AREA B - REFER TO MAINTENANCE MANUAL Figure U.S

20 SECTION II - OPERATING LIMITATIONS MODEL 680A START CYCLE LIMITS 1. Engine Starter Limit 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 The engine starter limit is independent of starter power source (i.e., battery, generator-assisted cross start, auxiliary power unit, or external power) and also applies to dry and wet motoring of the engine. 2. Engine Starter Motoring Limit (not engine start) batteries only seconds Batteries with generator assist seconds External Power (1000 amps) seconds External Power (1500 amps) seconds 3. APU Starter Limit Three APU starts per 30 minutes. Three starts with a 90-second rest period between starts. 4. Battery Start Limit Three engine battery starts per hour. Nine APU battery starts per hour. NOTE If the battery limit is exceeded, ground maintenance procedures are required. Refer to Chapter 24 of the Airplane Maintenance Manual for procedures. Three engine external power starts (available external power current greater than or equal to 1000 amps) are equivalent to one engine battery start. One engine external power start (available external power current less than 1000 amps) is equivalent to one engine battery start. Three generator-assisted cross starts are equivalent to one engine battery start. Three APU battery starts are equivalent to one engine battery start. EXTERNAL POWER LIMITS 1. Maximum Current Amps 2. Maximum Voltage VDC U.S.

21 MODEL 680A SECTION II - OPERATING LIMITATIONS MINIMUM CREW Minimum Flight Crew for All Operations Pilot and 1 Copilot SPEED LIMITS 1. Maximum Operating Mach Number - M MO above 29,833 feet Mach 0.80 (Indicated) 2. Maximum Operating Knots - V MO a feet to 29,833 feet KIAS b. Below 8000 feet KIAS NOTE Speed limits are lower for certain equipment failures and may not be deliberately exceeded unless authorized for flight test or pilot training. 3. Maximum Maneuvering Speed - V A Refer to Figure WARNING Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (e.g., large sideslip angles), as they can result in structural failures at any speed, including below V A. NOTE Full application of rudder and aileron controls, as well as maneuvers that involve angles-of-attack near the stall, should be confined to speeds below maximum maneuvering speed. 4. Maximum Flap Extended Speed - V FE a. Flaps KIAS b. Flaps KIAS c. Flaps FULL KIAS 5. Maximum Landing Gear Operating/Extended Speed - V LE /V LO KIAS NOTE This is the maximum speed at which the landing gear may be lowered or raised as well as the maximum speed with landing gear extended. 6. Maximum Turbulent Air Penetration Speed KIAS/Mach Maximum Speedbrake Extension Speed No Limit 8. Minimum Speedbrake Extended Speed (10 Panels) (except as required by AFM procedure) v REF +15 KIAS 9. Minimum Single Engine Enroute Climb Speed - V FTO KIAS 10. Maximum Tire Ground Speed Knots 11. Minimum Speed For Sustained Flight In Icing Conditions (except takeoff, approach and landing) KIAS 12. Minimum Control Speeds - V MCA, V MCL and V MCG Refer to Section IV, Performance, GENERAL U.S

22 SECTION II - OPERATING LIMITATIONS MODEL 680A MAXIMUM MANEUVERING SPEEDS EXAMPLE: PRESSURE ALTITUDE - 10,000 FEET WEIGHT - 30,800 POUNDS MAXIMUM MANEUVERING SPEED KIAS Figure U.S.

23 MODEL 680A SECTION II - OPERATING LIMITATIONS OPERATIONS AUTHORIZED 1. This airplane is approved for day and night, VFR and IFR operations, and flight into known icing conditions. 2. This airplane is not certified for ditching under 14 CFR Part This airplane is eligible for over-water operations with applicable equipment specified in the appropriate operating rules. LOAD FACTOR 1. Flaps UP G to +2.75G 2. Flaps 1, 2 or FULL G to +2.0G 3. Maximum Duration - Zero G or Less Seconds NOTE These accelerations limit the angle of bank in turns and limit the severity of pull-up maneuvers. 4. Maximum landing sink rate is limited to 600 feet per minute at maximum landing weight or less. MANEUVER LIMITS 1. Aerobatic maneuvers, including spins, are prohibited. 2. Intentional stalls are prohibited above FL180. Intentional full stalls are limited to idle thrust only. 3. Refer to Figure for maximum maneuvering speeds. MAXIMUM ALLOWABLE FLIGHT TIME TO A SUITABLE AIRPORT Flight must remain within 180 minutes of a suitable airport for landing. This limitation is due to: 1. Standby flight instruments back-up battery endurance time. 2. Baggage/cargo compartment fire protection. U.S

24 SECTION II - OPERATING LIMITATIONS MODEL 680A This Page Intentionally Left Blank U.S.

25 MODEL 680A SECTION II - OPERATING LIMITATIONS ELECTRICAL POWER SYSTEMS 1. Generator limits are as listed in Figure STATUS ENGINE LIMIT APU LIMIT Ground 300 Amps 275 Amps Air 300 Amps 275 Amps* > FL Amps Not Applicable *The maximum operating altitude for the APU is FL300. Figure NOTE Transients greater than these numbers are permissible, provided the amber DC GEN AMPS CAS message does not display. 2. The battery temperature indicating system must be operational. a. The minimum battery temperature for APU start is -20 C. b. The minimum battery temperature for engine start is -10 C. 3. If the red BATTERY O'TEMP L and/or R CAS message displays during ground operations, even if it subsequently clears, takeoff is prohibited until proper maintenance procedures have been accomplished. 4. For generator cooling during ground operations, the engine must be operated at idle (small thrust increases for taxi are acceptable) with the generator load less than 75 amps for 4 minutes prior to engine shutdown. Otherwise, a 35-minute cooling period after engine shutdown is required prior to attempting a restart. 5. TRU must be used only in accordance with an applicable AFM procedure. Maximum current limit for each TRU is 100 Amps. AUXILIARY POWER UNIT (APU) 1. The maximum altitude for APU starts is FL The maximum airspeed for APU starts is 305 KIAS. 3. The maximum operating altitude for the APU is FL One APU start attempt is permitted after a dual generator failure. 5. Following shutdown for any reason, an APU restart must not be attempted until 30 seconds after the RPM indicator reads 0%. 6. Applying deice/anti-ice fluid of any type is prohibited when the APU is operating. 7. Unattended operation of the APU is prohibited. 8. Operating the cockpit and cabin temperature controls in MANUAL is prohibited while MAX COOL and APU BLEED AIR are selected ON. A 30-second waiting period is required after selecting MAX COOL to OFF before operating cockpit and cabin temperature controls in MANUAL. 9. For approved oils for use in the APU, refer to Engine Limits, this section. In addition, oils listed in the latest revision of the RE100(CS) Maintenance Manual are approved. 10. The APU compartment must be inspected following an automatic shutdown of the APU. U.S

26 SECTION II - OPERATING LIMITATIONS MODEL 680A FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC) 1. Exceeding the time interval (125 hours) for a white ENG DISPATCH LIM L and/or R CAS message is prohibited. HYDRAULIC POWER SYSTEM 1. The only approved hydraulic fluid for hydraulic power systems is MIL-PRF The use of the auxiliary hydraulic pump is prohibited when the ground operating temperature is below -40 C. 3. The use of the auxiliary hydraulic pump in flight is prohibited. ICE AND RAIN PROTECTION 1. In icing conditions, the airplane must be operated, and its ice protection systems must be used, as described in Section III, Normal Procedures, Anti-ice Systems. Specific operational speeds and performance information must be used where established for such conditions. 2. The ANTI-ICE ENGINE/STAB buttons must be selected ON between the temperatures of +10 C to -35 C when in visible moisture. Use SAT for ground operations and RAT for in flight. 3. ANTI-ICE WING buttons must be selected OFF for operations above FL Except for the ground preflight check, maximum SAT for operation of bleed air anti-ice with the throttles above idle is +20 C. 5. Limit the ground operation of the pitot-static heat to 2 minutes to preclude damage to the pitot tubes and angle-of-attack vanes. 6. Anti-ice systems must not be used to deice surfaces prior to takeoff. CAUTION To prevent possible engine damage from ingestion of ice, do not chip or scrape ice or snow from the engine air inlet. Deice these areas prior to start (refer to Section VII, Advisory Information, Ground Deice/Anti-Ice Operations) U.S.

27 MODEL 680A SECTION II - OPERATING LIMITATIONS OPERATIONS IN SEVERE ICING CONDITIONS WARNING Severe icing can result from environmental conditions outside of those for which the airplane is certified. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) can result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or can result in ice forming aft of the protected surfaces. This ice may not be shed when using the ice protection systems and may seriously degrade the performance and controllability of the airplane. Runback ice extending approximately 12 inches to 18 inches aft of the heated leading edge on the upper surface of the wing is normal in some icing conditions, has been evaluated to verify satisfactory performance and controllability, and is not an indication of severe icing. 1. During flight, severe icing conditions that exceed those for which the airplane is certified must be determined by the following visual cues: a. Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice. b. Accumulation of ice on the upper surface of the wing aft of the protected area extending more than 18 inches aft of the heated leading edge. 2. If one or more of these visual cues exist, immediately request priority handling from Air Traffic Control to facilitate a route or altitude change to exit the icing conditions. NOTE Per FAA Airworthiness Directive , severe icing can be encountered at temperatures as cold as -18 C. U.S

28 SECTION II - OPERATING LIMITATIONS MODEL 680A BOUNDARY LAYER ENERGIZERS All boundary layer energizers (7 per wing) and stall strips (2 per wing) must be present for takeoff. CABIN PRESSURIZATION LIMITS 1. Pressure Differential Digital Display Green Range to 10.2 PSID 2. Pressure Relief Valve (+ 0.15) PSID 3. Pressure Differential Digital Display Red Range PSID U.S.

29 MODEL 680A SECTION II - OPERATING LIMITATIONS PASSENGER COMPARTMENT 1. For taxi, takeoff, and landing, seat backs must be fully upright, head rests extended, seat controls inboard, seat tracked away from the table and then outboard, and passenger seat belts and shoulder harnesses (if installed) must be fastened. 2. The maximum number of occupants in the passenger compartment is The lavatory door must be latched open for taxi, takeoff, and landing. 4. Use of the forward galley ice chest drain is prohibited in flight. BAGGAGE COMPARTMENT 1. The tailcone baggage compartment smoke detection and fire extinguishing systems must be operational if baggage is carried in the compartment. 2. The maximum total weight in the tailcone baggage compartment is 1000 pounds. Total weight includes baggage in the forward and aft compartments plus any on the coat rod. 3. The maximum floor loading distribution is 150 pounds per square foot. U.S

30 SECTION II - OPERATING LIMITATIONS MODEL 680A EIS AND INSTRUMENT MARKINGS ENGINE INDICATION SYSTEM Fan (N1) Indicators Scale markings: red Band % RPM Red Line % RPM or > % for >20 Sec Amber Band.. >105 - <106% RPM for 20 Sec Green Band % RPM Analog Pointer/Digital Readout: Red % RPM or >105% RPM for >20 Sec Amber >105 - <106% RPM for 20 Sec Analog Pointer White % RPM Digital Readout: Green % RPM Inter-Turbine Temperature Indicators - Engine Start Scale Markings: Red Band C Red Line C or > C for >20 Sec Green Band <950 C or 920 C for >20 Sec Analog Pointer/Digital Readout: Red C or >920 C for >20 Sec Analog Pointer: White <950 C Digital Readout: Green <950 C Inter-Turbine Temperature Indicators - Engine Running Scale Markings: Red Band C Red Line C or > C for >20 Sec Analog Pointer/Digital Readout: Red C or >920 C for >20 Sec Amber >920 - <950 C for 20 Sec Analog Pointer: White C Digital Readout: Green C (Continued Next Page) U.S.

31 MODEL 680A SECTION II - OPERATING LIMITATIONS EIS AND INSTRUMENT MARKINGS (Continued) Turbine (N2) RPM Indicators Digital Readout: Red % RPM or >105% RPM for >20 Sec Amber >105 - <106% RPM for 20 Sec Green % RPM Oil Temperature Indicators Digital Readout: Red (max) C or >135 C for >90 Sec Amber (max) >135 - <143 C for 90 Sec Green C C Amber (min) C to <+16 C with TLA 82% N1 Red (min) C to <-40 C -40 C to <+16 C with TLA >82% N1 NOTE Oil temperature must be above 16 C to increase thrust beyond 82% N1. Oil Pressure Indicators - Engine Start Digital Readout: Red >220 PSI Green PSI Oil Pressure Indicators - Engine Running Digital Readout: Red (max) >220 PSI or >110 PSI for >90 Sec Amber (max) > PSI for 90 Sec Green PSI Amber (min) <36 PSI <20 PSI for 20 Sec Red (min) <20 PSI for >20 Sec U.S

32 SECTION II - OPERATING LIMITATIONS MODEL 680A EIS AND INSTRUMENT MARKINGS (Continued) MAIN ELECTRICAL NiCad Battery Voltage Digital Display: Amber < 23 Volts, > 32 Volts Green Volts NiCad Battery Current Digital Display: Amber (except during engine or APU start) Amps, 200 Amps or < 0 Amps for > 30 Sec Green > -200 Amps to < +200 Amps NiCad Temperature Digital Display: Red > 63 C Amber < -20 C Green C to +63 C Left and Right Electrical Systems Generator Voltage Digital Display: Amber < 23 Volts, > 30 Volts Green Volts Generator Current Digital Display - Engine Start Below FL350: Amber > 450 Amps for > 30 Sec or > 300 Amps for > 120 Sec Green Amps Above FL350: Amber > 450 Amps for > 30 Sec or > 275 Amps for > 120 Sec Green Amps Generator Current Digital Display - Engine Running Below FL350: Amber > 300 Amps for > 20 Sec Green Amps Above FL350: Amber > 275 Amps for > 120 Sec Green Amps APU Current Digital Display - APU Start Amber > 450 Amps for > 30 Sec or > 275 Amps for > 120 Sec Green Amps APU Current Digital Display - APU Running....Amber > 275 Amps for > 20 Sec Green Amps TRU Ammeter Digital Display: Amber > 100 Amps Green Amps (Continued Next Page) U.S.

33 MODEL 680A SECTION II - OPERATING LIMITATIONS EIS AND INSTRUMENT MARKINGS (Continued) FLIGHT CONTROLS In flight, the scale marking, pointer and digits of all trim displays (stabilizer, rudder and aileron) will be white. Stabilizer Trim Display - On Ground Scale Marking Green Band to -5.1 Travel See Normal Procedures, Figure for the specific trim setting required for takeoff. Pointer Amber Outside Green Band White Inside Green Band Digital Display Amber Outside Green Band White Inside Green Band Rudder Trim Display - On Ground Scale Marking Green Band Travel Pointer Amber Outside Green Band White Inside Green Band Aileron Trim Display - On Ground Scale Marking Green Band Travel Pointer Amber Outside Green Band White Inside Green Band Wing Display Speedbrake Display Amber Sensor Fault or Panel Position Does Not Match Handle Position White Panels Deployed as Commanded (Continued Next Page) U.S

34 SECTION II - OPERATING LIMITATIONS MODEL 680A EIS AND INSTRUMENT MARKINGS (Continued) SYSTEMS Airspeed Indicator: Red Line KIAS/Mach KIAS (below 8000 feet) 250 KIAS (Flaps 1) 210 KIAS (Gear Down) 200 KIAS (Flaps 2) 175 KIAS (Flaps FULL) Brake and Gear Pneumatic Pressure Indicator: Per Placard According to Temperature Cabin Differential Pressure Digital Display: Red > 10.2 PSI Green PSI Fuel Quantity Digital Display Wing Tanks: Amber < 500 Pounds Green Pounds Total: Amber < 1000 Pounds Green Pounds Hydraulic Pressure Digital Display: Amber (max) > 3300 PSI Green PSI Amber (min) < 2300 PSI Hydraulic Reservoir Volume Digital Display:....Amber < 120 CU IN Green CU IN Nosewheel Steering Accumulator Pressure Indicator: Per Placard According to Temperature Oxygen Pressure Indicator/Digital Display:.....Red > 2000 PSI White (max) > PSI Green PSI White (min) < 1600 PSI Amber < 400 PSI U.S.

35 MODEL 680A SECTION II - OPERATING LIMITATIONS SUPPLEMENTAL OXYGEN SYSTEM 1. Smoking is prohibited when oxygen is being used, or following use of passenger oxygen until all masks have been re-installed in their canisters. 2. Service oxygen system with Aviator s Breathing Oxygen per MIL-O The use of medical oxygen is not approved. 3. The following airplane certification requirements are in addition to the requirements of applicable operating rules. The most restrictive requirement (certification or operating) must be observed. a. Crew oxygen masks are not approved for sustained operation at a cabin altitude greater than 40,000 feet. b. Passenger oxygen masks are not approved for sustained operation at a cabin altitude greater than 25,000 feet. c. The pressure-demand crew oxygen masks must be properly stowed in their containers to qualify as a quick-donning mask. d. For airplanes equipped with the EROS MLD oxygen masks, crew members must familiarize themselves with proper use of the smoke goggle clip-on procedure. THRUST REVERSERS 1. A satisfactory preflight check of the thrust reversers must be accomplished in accordance with Section III, Normal Procedures on the first flight of the day and on any flight that is predicated on the use of the thrust reversers for performance or the first flight after any maintenance action has been performed on the airplane. 2. Reverse thrust must be decreased to the idle reverse position at 65 KIAS on landing roll. 3. Deployment of the thrust reversers for more than 30 seconds with the APU operating is prohibited. 4. Static ground operation of the engines is limited to IDLE if the thrust reversers are deployed. 5. The use of thrust reversers is prohibited during touch-and-go landings. 6. The use of thrust reversers to back the airplane is prohibited. ANGLE-OF-ATTACK AND STICK SHAKER SYSTEM 1. The angle-of-attack indicating system may be used as a reference, but does not replace the airspeed display in the PFD as a primary instrument. 2. The angle-of-attack system can be used as a reference for approach speed (V REF ) at all airplane weights, CG locations, and flap positions. V REF is indicated by approximately 0.6 on the AOA gauge and by the green circle on the pilot s and copilot s airspeed indicators. STANDBY FLIGHT DISPLAY 1. The L3 Communications Avionics Systems Pilot s Guide for the Electronic Standby Instrument System Model GH , Part Number Release 1.2 or later applicable revision, must be available to the flight crew. 2. The standby flight display (including pre-flight test, attitude, heading, altitude, and airspeed) must be functioning prior to takeoff. U.S

36 SECTION II - OPERATING LIMITATIONS MODEL 680A GARMIN G5000 AVIONICS SYSTEM SOFTWARE - GENERAL (Software ) 1. The Garmin G5000 Integrated Avionics System Pilot s Guide for the Cessna Citation Latitude, part number Rev A or later applicable revision, must be available to the flight crew. 2. Takeoff with a display unit in reversionary mode is prohibited. 3. Taxiing the airplane is prohibited until AHRS alignment is complete. 4. Attitude pitch limit indicator (PLI) must not be used as a sole means of stall avoidance. 5. If the electronic cabin briefer system is used, it must contain FAA approved operating procedures. It is the operator s responsibility to make sure the briefer contents reflect current Airplane Flight Manual revisions and any applicable operating requirements. 6. Category II ILS approaches are not authorized. 7. For continuous ground operation with electrical power on when ambient temperatures are at or above ISA +26 C, conditioned air must be supplied to the cabin with APU or engine bleed air and the cabin door must be kept closed except for passenger boarding. 8. During initial electrical power on: a. Ground operations with electrical power on when ambient temperatures are at or above ISA +31 C are limited to 30 minutes. Landing, taxi, shutdown, and quick turn are allowed if accomplished within 45 minutes. b. Ground operations with electrical power on when ambient temperatures are at or above ISA +36 C are prohibited. Landing, taxi, shutdown, and quick turn are allowed if accomplished within 45 minutes. 9. Prior to the FAF, make sure that the ILS or VOR auto-selected course (as appropriate) matches the final approach course on the published approach. 10. After making a modification to the flight plan waypoints or VNAV constraints, the flight plan must be reviewed to verify all waypoints and constraints are correct. 11. Use of autopilot or flight director coupled LDA approaches with a GS is prohibited. SYNTHETIC VISION TECHNOLOGY (SVT) 1. SVT is provided as a situational awareness tool and must not be used for tactical navigation around terrain, obstacles or traffic. 2. Airplane navigation must not be predicated solely on SVT runway presentation graphics. Approach path angle and distance must be confirmed by other sources. 3. SVT airport surface markings and features may not always agree with the actual surface markings and prevailing NOTAMs in effect for the particular airport. SVT must not be used as the sole means of navigation on the airport surface. 4. TCAS intruder traffic that is below 500 feet AGL may not appear on SVT or may only partially appear U.S.

37 MODEL 680A SECTION II - OPERATING LIMITATIONS AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) 1. Autopilot: a. One pilot must remain seated, with the seatbelt fastened, during all autopilot operations. b. Autopilot operation is prohibited when any comparison monitor message is displayed and appropriate sensor reversion has not been selected. c. Autopilot Minimum Use Height: (1) Enroute and Descent feet AGL (2) Precision Approach (ILS/LPV) feet AGL (3) Non-precision Approach feet AGL (4) Takeoff, Climb, and Missed Approach feet AGL 2. Autothrottle: a. Autothrottle must not be armed or used during taxi operations; arm only when cleared for takeoff. b. Autothrottle operation is prohibited when any comparison monitor message is displayed and appropriate sensor reversion has not been selected. c. Autothrottle HOLD mode must be displayed prior to 65 KIAS during takeoff. d. Autothrottle engagement above 65 KIAS on ground or below 400 feet AGL is prohibited. e. Autothrottle must be disengaged prior to 50 feet AGL for touch and go landings. f. Autothrottle must be disengaged prior to landing with Flaps not in the FULL position. g. When using autothrottle on approach the selected airspeed must be set to V REF + 3 knots or greater. G5000 FLIGHT MANAGEMENT SYSTEM 1. Navigation using the FMS is limited to areas where charted information uses the world geodetic system 1984 (WGS-84) ellipsoid coordinate datum or equivalent. 2. Other navigation equipment (i.e., VOR, DME) appropriate to the intended route must be installed and operable, as required by the operating rules applicable to the specific type of operation except when SBAS coverage is available or GNSS is otherwise approved as the primary navigation sensor. 3. RAIM availability must be verified prior to conducting operations with an operational requirement for a predeparture GNSS integrity coverage check except when SBAS coverage is confirmed to be available. 4. Use of the FMS as a primary navigation source is prohibited in DR modes or when EPE exceeds RNP, except when executing a missed approach from an RNP approach procedure following loss of GNSS navigation. 5. IFR enroute and terminal navigation is prohibited unless the pilot verifies the currency of the database or verifies each selected waypoint for accuracy by reference to current data. 6. For RNP navigation, the FMS database must incorporate the current update cycle. 7. The use of manually inserted runway coordinates is limited to VFR operations. 8. The fuel quantity, fuel required, fuel remaining and gross weight estimate performance functions of the FMS are supplemental information only and must be verified by the flight crew. (Continued Next Page) U.S

38 SECTION II - OPERATING LIMITATIONS MODEL 680A G5000 FLIGHT MANAGEMENT SYSTEM (Continued) FMS NAVIGATION OPERATIONAL CAPABILITIES The Garmin G5000 multi-sensor navigation system is compliant with TSO-C115c and applicable sections of AC20-138C. When receiver autonomous integrity monitoring (RAIM)/Fault Detection and Exclusion (FDE) availability must be verified prior to flight, this check can be accomplished using the on board RAIM prediction tool or other approved FDE program. This airplane complies with the criteria of AMC for RNP approaches to LNAV/VNAV minima. (EASA CM - AS 002 Issue: 01) (Continued Next Page) U.S.

39 MODEL 680A SECTION II - OPERATING LIMITATIONS FMS NAVIGATION OPERATIONAL CAPABILITIES (Continued) The FMS equipment as installed has been found to comply with the requirements established for the following navigation specifications. This does not constitute an operational approval, where required. Navigation Specification Oceanic and Remote Areas of Operation (Class II Navigation). North Atlantic (NAT) Minimum Navigation Performance Specifications (MNPS) RNAV-10 RNP-10 Operational Requirements/ Authorizations GNSS FDE availability must be verified prior to flight. Maximum predicted FDE unavailability is 25 minutes. No time limit using GNSS as the primary navigation sensor. GNSS FDE availability must be verified prior to flight. Maximum predicted FDE unavailability is 25 minutes. No time limit using GNSS as the primary navigation sensor. GNSS FDE availability must be verified prior to flight. Maximum predicted FDE unavailability is 25 minutes. Required Equipment Two FMSs installed, operating and receiving usable navigation information from each of the dual GNSS sensors (or one FMS and one GNSS sensor for those routes requiring only one long range navigation sensor). Two FMSs installed, operating and receiving usable navigation information from each of the dual GNSS sensors (or one FMS and one GNSS sensor for those routes requiring only one long range navigation sensor). Two FMSs installed, operating and receiving usable navigation information from each of the dual GNSS sensors. Reference Guidance Meets the applicable requirements of AC20-138C, AC90-100A, AC91-70, FAA Order Meets the applicable requirements of AC20-138C, AC91-70, AC Meets the applicable requirements of AC20-138C FAA Order B. EPE does not exceed RNP. No time limit using GNSS as the primary navigation sensor. (Continued Next Page) U.S

40 SECTION II - OPERATING LIMITATIONS MODEL 680A FMS NAVIGATION OPERATIONAL CAPABILITIES (Continued) Navigation Specification B-RNAV/RNAV-5 RNP-5. RNP-4 Oceanic and Remote Area Operations. Operational Requirements/ Authorizations EPE does not exceed RNP. No time limit using GNSS as the primary navigation sensor. GNSS FDE availability must be verified prior to flight. Maximum predicted FDE unavailability is 25 minutes. Required Equipment At least one FMS is receiving usable navigation information from one or more of the following sensors: 1. Multiple DMEs, or 2. GNSS sensor. Two FMSs installed, operating and receiving usable navigation information from each of the dual GNSS sensors. Reference Guidance Meets the applicable requirements of AC20-138C, AC90-96A, AC90-100A, EASA AMC Meets the applicable requirements of AC20-138C, FAA Order EPE does not exceed RNP. RNAV-2 RNAV-1 P-RNAV RNAV Routes (DPs, STARS, Q and T Routes) RNP-2 RNP-1 No time limit using GNSS as the primary navigation sensor. GNSS sensor is required for takeoff in P-RNAV airspace. GNSS FDE availability must be verified prior to flight for DPs that require GNSS. EPE does not exceed RNP. No time limit using GNSS as the primary navigation sensor. At least one FMS is receiving usable navigation information from one or more of the following sensors: 1. Multiple DMEs, or 2. GNSS sensor (required for takeoff in P-RNAV airspace and some DPs). Meets the applicable requirements of AC20-138C, AC90-105, AC90-96A, AC90-100A, JAA TGL 10. (Continued Next Page) U.S.