Limitations Cit-X

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jmilton
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170431
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Limitations Cit-X
Updated:
2013-03-19 09:57:54
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Citation limitations
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Citation X Limitations
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  1. OPERATIONS AUTHORIZED
    No intentional stalls are permitted above _______ feet.
    • OPERATIONS AUTHORIZED
    • No intentional stalls are permitted above 18,000 feet.
  2. MINIMUM CREW
    Minimum Flight Crew for All Operations ........... PILOT AND COPILOT
  3. BELTED TOILET SEAT
    During Taxi, Takeoff and Landing when the belted toilet seat is occupied, the aft divider sliding doors must be ________.
    During Taxi, Takeoff and Landing when the belted toilet seat is occupied, the aft divider sliding doors must be LATCHED OPEN.
  4. WEIGHT LIMITATIONS
    Maximum Design Ramp Weight......................................... ? Maximum Certified Takeoff Weight................................... ? Maximum Certified Landing Weight ................................. ? Maximum Design Zero Fuel Weight ................................. ?
    Maximum Design Ramp Weight...................... 36,000 LBS Maximum Certified Takeoff Weight ................. 35,700 LBS Maximum Certified Landing Weight................ 31,800 LBS Maximum Design Zero Fuel Weight ................ 24,400 LBS
  5. BALLAST FUEL
    Ballast fuel is fuel that remains within the wing fuel tanks which cannot be used without causing the aft center-of- gravity limit to be exceeded. Ballast fuel is ___________.
    • BALLAST FUEL
    • Ballast fuel is fuel that remains within the wing fuel tanks which cannot be used without causing the aft center-of- gravity limit to be exceeded. Ballast fuel is nonusable fuel.
  6. TAKEOFF AND LANDING OPERATIONAL LIMITS Maximum Altitude Limit for Takeoff and Landing............ ? Maximum Tailwind Component for Takeoff and Landing. ? Maximum Crosswind Component Slats Asymmetry for Takeoff and Landing ........................................................ ? Minimum Altitude for In-flight Use of Speed Brakes for Takeoff and Landing ......................................................... ?
    TAKEOFF AND LANDING OPERATIONAL LIMITS Maximum Altitude Limit for Takeoff and Landing ... 14,000 FEET Maximum Tailwind Component for Takeoff and Landing ................................................................ 10 KNOTS Maximum Crosswind Component Slats Asymmetry for Takeoff and Landing ........................... 10 KNOTS Minimum Altitude for In-flight Use of Speed Brakes for Takeoff and Landing................ 500 FEET AGL
  7. TAKEOFF AND LANDING OPERATIONAL LIMITS Maximum Asymmetric Fuel Imbalance .............................. ? Emergency Asymmetric Fuel Imbalance ............................ ? Minimum Wing Fuel Per Tank for Takeoff........................ ? Takeoff in high idle is ____________.
    Maximum Asymmetric Fuel Imbalance.................. 400 LBS Emergency Asymmetric Fuel Imbalance................ 800 LBS Minimum Wing Fuel Per Tank for Takeoff............ 500 LBS Takeoff in high idle is prohibited (except touch and go).
  8. SPEED LIMITATIONS Maximum Operating MACH — (MMO) Above 30,650 Feet .............................................. ? (MMO) with Mach Trim Off ........................................ ? Maximum Operating KNOTS — (VMO) 8000 Feet to 30,650 Feet ......................................... ?
    Maximum Operating KNOTS — (VMO) Below 8000 Feet....................................................... ?
    • Maximum Operating MACH — (MMO) Above 30,650 Feet ................................................ 0.92 MACH (Indicated)
    • (MMO) with Mach Trim Off ......... 0.82 MACH (Indicated)
    • Maximum Operating KNOTS — (VMO) 8000 Feet to 30,650 feet ......................................350 kias
    • Maximum Operating KNOTS — (VMO) Below 8000 Feet ......................................................... 270 KIAS
  9. SPEED LIMITATIONS
    Maximum Altitude for Extension of Flaps and Landing Gear................ ?
    Maximum Slat Extended Speed............................................................ ?
    Maximum Flap Extended Speed — VFE, Flaps — 5° Position................................................................................ ?
    MaximumFlapExtendedSpeed—VFE,Flaps 15°Position.....?
    Maximum Flap Extended Speed Flaps — FULL Position ..?
    Maximum Landing Gear Operating/Extended Speed — VLO/VLE............................................................... ?
    • Maximum Altitude for Extension of Flaps and Landing Gear ............................................................... 18,000 FEET Maximum Slat Extended Speed ......................250 Kias Maximum Flap Extended Speed — VFE, Flaps — 5° Position...............................................................  250 KIAS Maximum Flap Extended Speed — VFE, Flaps — 15° Position................................................................. 210 KIAS
    • Maximum Flap Extended Speed Flaps — FULL Position.......                                .................          180 KIAS
    • Maximum Landing Gear Operating/ Extended Speed — VLO/VLE ........................................................... 210 KIAS
  10. SPEED LIMITATIONS
    Maximum Turbulent Air Penetration Speed ....................... ? Maximum Speed Brake Extension Speed.......................... ? Minimum Speed Brake Extension Speed........................... ? Minimum Single Engine Enroute Climb Speed .................. ? Maximum Tire Ground Speed ............................................
    • Maximum Turbulent Air Penetration Speed ............................. 300 KIAS/0.9 MACH
    • Maximum Speed Brake Extension Speed .......... NO LIMIT Minimum Speed Brake Extension Speed......................................... VREF +15 KIAS Minimum Single Engine Enroute Climb Speed ........................................................ 190 KIAS Maximum Tire Ground Speed.......................... 182 KNOTS
  11. ENROUTE OPERATIONAL LIMITS
    Maximum Operating Altitude ............................................. ?
    Maximum Operating Altitude .......................... 51,000 FEET
  12. LOAD FACTORS
    Maximum Landing Load Factor ......................................... ? The Maximum Landing Load Factor Represents Landing at a Sink Rate, at Touchdown .............................. ?
    Maximum Landing Load Factor ........ +3.5G at 31,800 LBS The Maximum Landing Load Factor Represents Landing at a Sink Rate, at Touchdown........ 600 FEET PER MINUTE
  13. CABIN PRESSURE LIMITATIONS
    Maximum Cabin Pressure Differential ............................. ?
    CABIN PRESSURE LIMITATIONS Maximum Cabin Pressure Differential...................... 9.7 PSI
  14. ENGINE AIR TURBINE STARTER
    LIMITATIONS

    The Engine Air Turbine Starter may be operated
    ______________.

    DO NOT ENGAGE THE AIR TURBINE
    STARTER ABOVE ............................................................... ?
    • The Engine Air Turbine Starter may be operated three consecutive normal starts followed by 25 minutes cooling. One 30 second motoring cycle is equivalent to one normal start.
    • DO NOT ENGAGE THE AIR TURBINE STARTER ABOVE.......................................... 25% N2 RPM
  15. GENERATOR LIMITATIONS

    Main Generator Amp Limit (each) Up to 41,000 Feet............................................................... ?
    Main Generator Amp Limit (each) Above 41,000 Feet ............................................................. ?
    Main Generator Amp Limit (each) Up to 41,000 Feet ....................................... 400 AMPERES Main Generator Amp Limit (each) Above 41,000 Feet...................................... 300 AMPERES
  16. ENGINE OPERATING LIMITATIONS
    Continuous engine ground static operation up to and including __________ at takeoff thrust.
    Continuous engine ground static operation up to and including 5 minutes at takeoff thrust.
  17. ENGINE OPERATING LIMITATIONS
    Engine Operating Limits for TO/MC................................. ? ITT Limits for TO/MC........................................................ ? Oil Temp Limit for TO/MC................................................ ?
    Engine Operating Limits for TO/MC................. 5 MINUTES ITT Limits for TO/MC................................................. 888°C Oil Temp Limit for TO/MC ...................... 127°C MAXIMUM
  18. ENGINE OPERATING LIMITATIONS
    CRU (Cruise) detent should be set within ___ minutes after level off from top-of-climb.
    During cold day starts, oil pressure may exceed 95 PSIG. Engine speed should not be advanced above ____ until oil pressure no longer exceeds 95 PSIG.
    Once the oil pressure is below 95 PSIG, engine speed can be advanced but should not exceed ____ until the engine fuel temperature is within normal limits, >/= 4°C.
    • CRU (Cruise) detent should be set within 10 minutes after level off from top-of-climb.
    • During cold day starts, oil pressure may exceed 95 PSIG. Engine speed should not be advanced above idle until oil pressure no longer exceeds 95 PSIG.
    • Once the oil pressure is below 95 PSIG, engine speed can be advanced but should not exceed 40% N1 until the engine fuel temperature is within normal limits, >/= 4°C.
  19. ENGINE OPERATING LIMITATIONS FADEC Automatic Overspeed Shutdowns are Set at ........ ? Minimum Fan Speed for Takeoff ....................................... ? When the Engine is Running, the FADEC Will Automatically Shut the Engine Down at ...................... ?
    • FADEC Automatic Overspeed Shutdowns are Set at............................................... 105% N1 AND 105.6% N2
    • Minimum Fan Speed for Takeoff ............................... 73.6% N1
    • When the Engine is Running, the FADEC Will Automatically Shut the Engine Down at........................................................ 54% N2 OR BELOW
  20. ENGINE OPERATING LIMITATIONS
    Minimum Oil Pressure BELOW 88% N2.......................... ?
    A cautionary oil pressure range is from_________. Maximum Oil Pressure ....................................................... ? Windmilling Airstart ITT Limit........................................... ?
    • ENGINE OPERATING LIMITATIONS
    • Minimum Oil Pressure BELOW 88% N2 ............. 34 PSIG
    • A cautionary oil pressure range is from >/= 34 to <50 PSI. Maximum Oil Pressure......................................... 155 PSIG (not to exceed 2 minutes)
    • Windmilling Airstart ITT Limit ................................ 888°C
  21. FUEL LIMITATIONS
    Minimum Fuel Temperature for Start, Takeoff and Enroute (Fuel Tank Temperature) .................... ?
    Maximum Fuel Temperature for Start, Takeoff and Enroute (Fuel Tank Temperature) .................... ?
    Minimum Fuel Temperature (Engine), Engine Operating .. ?
    Takeoff with Engine Fuel Temperature below +4°C or above 98.9°C is __________.
    • Minimum Fuel Temperature for Start,
    • Takeoff and Enroute (Fuel Tank Temperature) ......... –37°C

    • Maximum Fuel Temperature for Start,
    • Takeoff and Enroute (Fuel Tank Temperature) ......... +52°C

    • Minimum Fuel Temperature (Engine),
    • Engine Operating ........................................................ +4°C

    Takeoff with Engine Fuel Temperature below +4°C or above 98.9°C is Not Permitted. 
  22. SINGLE POINT REFUELING
    Maximum Refueling Pressure............................................. ? Maximum Defueling Pressure ............................................ ?
    Maximum Refueling Pressure ................................ 55 PSIG Maximum Defueling Pressure .............................. –10 PSIG
  23. FUEL TRANSFER/CROSSFEED LIMITATIONS
    Center tank to wing transfer must be initiated prior to ____ lbs per side wing fuel. Maximum Lateral Fuel Imbalance (intentional)........................... ?
    An imbalance of ____ pounds has been demonstrated for emergency return.
    Simultaneous use of crossfeed and center-to-wing tank transfer is prohibited when the wing fuel quantity is ____________ per side.
    • Center tank to wing transfer must be initiated prior to 3100 lbs per side wing fuel.
    • Maximum Lateral Fuel Imbalance (intentional)........ 400 pounds
    • An imbalance of 800 pounds has been demonstrated for emergency return.
    • Simultaneous use of crossfeed and center-to-wing tank transfer is prohibited when the wing fuel quantity is 2900 lbs or less per side.
  24. APU LIMITATIONS
    DO NOT APPLY EXTERNAL AIRPLANE DEICING FLUID WHEN ___________________.
    Maximum APU starter duty cycles are ___ consecutive successful starts at ___ minute intervals.
    A ___ hour off time must be observed for additional successful starts.
    • DO NOT APPLY EXTERNAL AIRPLANE DEICING FLUID WHEN THE APU IS OPERATING.
    • Maximum APU starter duty cycles are six consecutive successful starts at ten minute intervals.  
    • A one hour off time must be observed for additional successful starts.
  25. APU LIMITATIONS
    Unsuccessful APU start attempts: Battery – _________________________________
    Generator/GPU – __________________________
    • Unsuccessful APU start attempts:
    • Battery – Two cycles, 30 seconds each/30 minutes off/ Two cycles, 30 seconds each/One hour off (check batteries)
    • Generator/GPU – Two cycles, 15 seconds each/ 20 minutes off/Two cycles, 15 seconds each (maximum four cycles per hour)
  26. BATTERY LIMITATIONS
    If the airplane will be cold soaked (parked) below –20°C (–4°F), the batteries should be _____________. Batteries colder than –20°C may be inert and will not discharge or charge.
    If a ground external power unit is used for APU start _____.
    • If the airplane will be cold soaked (parked) below –20°C (–4°F), the batteries should be removed and stored in a warm environment. Batteries colder than –20°C may be inert and will not discharge or charge.
    • If a ground external power unit is used for APU start no battery cycle is counted.
  27. PNEUMATIC CART

    If a ground pneumatic cart is being used for engine start,
    it must be capable of maintaining a minimum air pressure
    of ______, as displayed in the EICAS, prior to initiating the
    start.
    If a ground pneumatic cart is being used for engine start, it must be capable of maintaining a minimum air pressure of 30 PSI, as displayed in the EICAS, prior to initiating the start.
  28. BAGGAGE COMPARTMENT
    Maximum Operating Altitude ________ with the baggage compartment unpressurized.
    Use of the baggage compartment is ________ with the cabin unpressurized.
    The baggage compartment smoke detection system must be operational _____________________________________. ____________ may not be carried in the baggage compartment.
    • Maximum Operating Altitude 41,000 Feet with the baggage compartment unpressurized.
    • Use of the baggage compartment is not authorized with the cabin unpressurized.
    • The baggage compartment smoke detection system must be operational if baggage is to be carried in the compartment.
    • Live animals may not be carried in the baggage compartment.
  29. BAGGAGE COMPARTMENT
    When the baggage compartment is not pressurized __________.
    Maximum Weight of Baggage in the Baggage Compartment...................................................... ?
    Maximum Floor Loading Distribution ............................... ?
    Maximum Weight in the Ski Holding Compartment ......... ?
    • When the baggage compartment is not pressurized the number of flights must be logged.
    • Maximum Weight of Baggage in the Baggage Compartment.......................................... 700 LBS Maximum Floor Loading Distribution..................... 170 LBS PER SQUARE FOOT Maximum Weight in the Ski Holding Compartment............................................. 75 LBS
  30. COCKPIT AND CABIN PAC SELECTOR SWITCHES Operation in HIGH mode is not approved for takeoff, landing or flight above _______.
    Operation in HIGH is not approved above _______ when the isolation valve is open and either left or right engine bleed air switch is OFF.
    Single PAC operation above _______ is prohibited.
    • Operation in HIGH mode is not approved for takeoff, landing or flight above 45,000 feet.
    • Operation in HIGH is not approved above 25,000 feet when the isolation valve is open and either left or right engine bleed air switch is OFF.
    • Single PAC operation above 41,000 feet is prohibited.
  31. PAC HIGH PRESSURE BLEED AIR

    Operation of the cabin and cockpit PACs in high pressure bleed air, HP BLEED SELECT switch to HP, (PAC HP VLV OPEN L-R message on) is not approved for _______________.

    Operation of the cabin and cockpit PACs in high pressure bleed air (PAC HP VLV OPEN message on) is prohibited when any of the following systems are on: ____________.

    The PAC BLEED SELECT switch must be positioned to NORM or HP above __________ . 
    • Operation of the cabin and cockpit PACs in high pressure bleed air, HP BLEED SELECT switch to HP, (PAC HP VLV OPEN L-R message on) is not approved for normal takeoff and landing operations.
    • Operation of the cabin and cockpit PACs in high pressure bleed air (PAC HP VLV OPEN message on) is prohibited when any of the following systems are on: engine anti-ice, slat anti-ice or horizontal stabilizer anti-ice.
    • The PAC BLEED SELECT switch must be positioned to NORM or HP above 41,000 feet.
  32. OXYGEN MASKS
    Crew oxygen masks are not approved for sustained operation at a cabin altitude greater than _______.
    Passenger oxygen masks are not approved for sustained operation at a cabin altitude greater than _______.
    The use of _______ oxygen is not approved.
    • Crew oxygen masks are not approved for sustained operation at a cabin altitude greater than 40,000 feet. Passenger oxygen masks are not approved for sustained operation at a cabin altitude greater than 25,000 feet.
    • The use of medical oxygen is not approved.
  33. STANDBY INSTRUMENTS The standby____________________________ must be operational.
    The standby power preflight check must be accomplished ____________.
    Standby airspeed indicator. Airspeeds on this placard, above 24,000 feet, are approximately _______.
    • The standby attitude indicator, airspeed/altimeter, and HSI instruments must be operational.
    • The standby power preflight check must be accomplished prior to each flight.
    • Standby airspeed indicator. Airspeeds on this placard, above 24,000 feet, are approximately 0.82 Mach.
  34. ENGINE SYNC
    The use of engine synchronization is prohibited _________.
    The use of engine synchronization is prohibited during takeoff and landing, single engine operation, or FADEC ADC or N1 reversionary operation.
  35. STALL WARNING
    Both stall warning systems, the auto-slat system, and the minimum speed system must be verified to be operational by a _____________.
    Both stall warning systems, the auto-slat system, and the minimum speed system must be verified to be operational by a satisfactory preflight test as contained in Section III.
  36. FLIGHT CONTROL SYSTEMS Both upper and ______ lower yaw damper channels must be operational for dispatch.
    ______ rudder limiters must be operational.
    The Mach trim system must be operational for speeds above ______.
    Except as required by Abnormal or Emergency Procedures, the A and B hydraulic systems may not be intentionally _______ (Pump A and/or Pump B switches to UNLOAD) in flight above _____ feet MSL altitude.
    • Both upper and either lower yaw damper channels must be operational for dispatch.
    • Both rudder limiters must be operational.
    • The Mach trim system must be operational for speeds above Mach 0.82.
    • Except as required by Abnormal or Emergency Procedures, the A and B hydraulic systems may not be intentionally unloaded (Pump A and/or Pump B switches to UNLOAD) in flight above 15,000 feet MSL altitude.
  37. THRUST REVERSERS

    Thrust reversers are restricted to ground operations on
    ______ surfaces only.

    Use of Thrust Reversers is prohibited during ___________.

    Reverse thrust must be reduced to idle reverse (detent) at
    ______ during landing rollout. 
    • Thrust reversers are restricted to ground operations on paved surfaces only.
    • Use of Thrust Reversers is prohibited during touch-and-go landings.
    • Reverse thrust must be reduced to idle reverse (detent) at 65 KIAS during landing rollout.
  38. THRUST REVERSERS

    During single engine reversing, either with nosewheel steering inoperative or on a slippery runway, thrust must be reduced to idle reverse (detent) by _____ during landing rollout.

    Thrust Reversers must not be used to back the aircraft during_____ operations.

    THRUST REVERSERS SHOULD NOT BE DEPLOYED UNTIL_____________. AIRPLANE PITCH UP MAY OCCUR. 
    During single engine reversing, either with nosewheel steering inoperative or on a slippery runway, thrust must be reduced to idle reverse (detent) by 70 KIAS during landing rollout.

    • Thrust Reversers must not be used to back the aircraft
    • during taxi operations.

    THRUST REVERSERS SHOULD NOT BE DEPLOYED UNTIL THE NOSE WHEEL IS ON THE GROUND.  AIRPLANE PITCH UP MAY OCCUR. 
  39. ICING LIMITATIONS

    Except for the ground preflight check, maximum SAT for
    operation of bleed air anti-ice above idle is ____.

    Minimum speed/configuration for sustained flight in icing is
    __________ except for approach and landing. 
    • Except for the ground preflight check, maximum SAT for
    • operation of bleed air anti-ice above idle is +20°C.

    • Minimum speed/configuration for sustained flight in icing is
    • 200 KIAS/slats up except for approach and landing. 
  40. PRIMUS 2000 AND AUTOPILOT

    One pilot must remain in his seat with seat belt and shoulder
    harness fastened during __________.
    PFD data must be displayed in the __________ display unitsfor dispatch.
    Autopilot Minimum Use Height During Cruise ................. ?
    Autopilot Minimum Use Height During Precision Approach (Category 1 ILS) ................................. ? 
    • One pilot must remain in his seat with seat belt and shoulder harness fastened during all autopilot operations.
    • PFD data must be displayed in the No. 1 and No. 5 display units for dispatch.
    • Autopilot Minimum Use Height During Cruise ............................................ 1000 FEET AGL
    • Autopilot Minimum Use Height During Precision Approach (Category 1 ILS).......... 170 FEET AGL
  41. PRIMUS 2000 AND AUTOPILOT
    Autopilot Minimum Use Height During Nonprecision Approach............................................................................ ? Autopilot coupled operation with _____________ IRS is prohibited. Autopilot coupled ILS approaches with _____ are prohibited.
    • Autopilot Minimum Use Height During Nonprecision Approach................... 400 FEET AGL
    • Autopilot coupled operation with single operational or displayed IRS is prohibited.
    • Autopilot coupled ILS approaches with flaps up are prohibited.
  42. IRS
    alignment procedures are only approved for latitudes between ___.25° North and ___.25° South.
    Movement of airplane is prohibited until ______ (2.5 minutes to 17 minutes, depending on latitude).
    During ATT alignment in flight, after an IRS FAIL, the Autopilot/Flight Director must be disconnected until the _______ on the FMS Control Display Unit (CDU).
    Once an IRS is placed in ATT mode, this IRS can no longer be used _________.
    • IRS alignment procedures are only approved for latitudes between 78.25° North and 78.25° South.
    • Movement of airplane is prohibited until the IRS ground alignment is complete (2.5 minutes to 17 minutes, depending on latitude).
    • During ATT alignment in flight, after an IRS FAIL, the Autopilot/Flight Director must be disconnected until the failed IRS aligns and the heading is initialized on the FMS Control Display Unit (CDU).
    • Once an IRS is placed in ATT mode, this IRS can no longer be used as a navigation sensor during the flight.
  43. PULSELITE SYSTEM
    The Pulselite System must be OFF and remain OFF during the following night ground and night flight operations: ____.
    The Pulselite System must be OFF and remain OFF during the following night ground and night flight operations: Taxi, takeoff and landing approach at 300 feet AGL and below.
  44. EICAS AND INSTRUMENT MARKINGS
    APU DC AMPS (Gage) Red Line ................................... ?
    Fuel Quantity Digital Indication (Wing Tanks).......Amber...................................................... ? Digital Ammeter Indication (EICAS) SL to FL410 Green Range.................................................. ?
    Digital Ammeter Indication (EICAS) above FL410............ ?
    • APU DC AMPS (Gage) Red Line................................. 300 Fuel Quantity Digital Indication (Wing Tanks).......Amber ............................................................................ < 500 LBS
    • Digital Ammeter Indication (EICAS) SL to FL410 Green Range........................................................ 0 TO 400 AMPS
    • Digital Ammeter Indication (EICAS) above FL410 ........ Green Range: 0 TO 300 AMPS
  45. EICAS AND INSTRUMENT MARKINGS
    Left and Right Oil Pressure Indication Green Range...................................................... ?
    Left and Right Oil Quantity Indication Amber Range..................................................... ?
    Left and Right Oil Temperature Indication Green Range...................................................... ?
    • Left and Right Oil Pressure Indication Green Range .................................. 50 TO 95 PSI
    • Left and Right Oil Quantity Indication Amber Range................... >/= 8.0 QUARTS LOW
    • Left and Right Oil Temperature Indication Green Range ................................... 21 TO 127°C
  46. ICING LIMITATIONS

    During flight, severe icing conditions that exceed those for which
    the airplane is certified shall be determined by the following visual
    cues:
    Unusually extensive ice accumulation on the ________ and ________ in areas not normally observed to collect ice.
    Accumulation of ice on the upper surface of the __________ aft of the protected area.
    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.
    ICING LIMITATIONS

    • During flight, severe icing conditions that exceed those for which
    • the airplane is certified shall be determined by the following visual
    • cues:
    • Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice 
    • Accumulation of ice on the upper surface of the wing aft of the protected area.
    • 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.
  47. FLIGHT CONTROL SYSTEMS

    The following flight control hydraulic systems must be ________to be operational
    by a satisfactory preflight test as contained in Section III:

    1. “A” and “B” hydraulic systems. (Proper hydraulic pressure, no CAS
    message.)
    2. The “ ” system auxiliary pump. (Proper pressure with “A” & “B”
    Systems off, setting brake.)
    3. The “B-to-A” power transfer system. (Proper pressure cycling after RH
    engine start.)
    4. “B” system rudder standby hydraulic system. (Absence of CAS
    messages after RH engine start.)
    5. _______system. (Absence of CAS messages or monitor annunciators.)
    FLIGHT CONTROL SYSTEMS

    • The following flight control hydraulic systems must be verified to be operational
    • by a satisfactory preflight test as contained in Section III:
    • “A” and “B” hydraulic systems. (Proper hydraulic pressure, no CAS
    • message.)
    • The “A” system auxiliary pump. (Proper pressure with “A” & “B”
    • Systems off, setting brake.)
    • The “B-to-A” power transfer system. (Proper pressure cycling after RH
    • engine start.)
    • “B” system rudder standby hydraulic system. (Absence of CAS
    • messages after RH engine start.)
    • 5. PCU monitor system. (Absence of CAS messages or monitor annunciators.)

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