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CJ3 > Limitations > Flashcards

Limitations Flashcards

1
Q 
WEIGHT LIMITATIONS
Maximum design ramp weight - ?
Maximum design takeoff weight - ?
Maximum design landing weight - ?
Maximum design zero fuel weight - ?
A

WEIGHT LIMITATIONS
Max design ramp weight - 14,070 pounds
Max design takeoff weight - 13,870 pounds
Max design landing weight - 12,750 pounds
Max design zero fuel weight - 10,510 pounds

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2
Q

ENGINE OPERATING LIMITS
Time limit (minutes)
TAKEOFF - ?

The engine should not be operated above 80% N2 until oil temperature is above - ?

A

ENGINE OPERATING LIMITS
Time limit (minutes)
TAKEOFF - nominally limited to 5 minutes duration may be used for up to 10 minutes for one engine inoperative operations

The engine should not be operated above 80% N2 until oil temperature is above +10C (+50F)

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3
Q

ENGINE START LIMITATIONS (GROUND)

ENG CTRL SYS FAULT L/R annunciators - ?
Maximum tailwind component - ?
Maximum crosswind component - ?
Maximum time to light-off - ?
Minimum engine oil temperature (indicated on EIS) - ?
A

ENGINE START LIMITATIONS (GROUND)

ENG CTRL SYS FAULT L/R annunciators - extinguished
Maximum tailwind component - 10 kts
Maximum crosswind component - 10 kts
Minimum time to light-off - 10 seconds
Minimum engine oil temperature (indicated on EIS) - -40C

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4
Q

ENGINE START LIMITATIONS (GROUND)

Maximum airport elevation for ground:
Battery start - ?
External power start - ?
Minimum battery voltage for battery start - ?
Min/max external power current capacity for start - ?

A

ENGINE START LIMITATIONS (GROUND)

Maximum airport elevation for ground:
Battery start - 14,000’
External power start - 14,000’
Minimum battery voltage for start - 24 VDC
Min/max external power current capacity for start - 800/1100 AMPS

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5
Q

ENGINE START LIMITATIONS (GROUND)

If engine oil temperature is below ____, the engine must be preheated prior to conducting a start.

If the battery has been cold soaked for 2 hrs or longer at ambient surface temperature of ___ or lower, it must be preheated to above -18C (0F) prior to start.

The Engine Indicating System (EIS) may take __ minutes to become usable after power is applied when cold soaked below -10C (+14F)

A

ENGINE START LIMITATIONS (GROUND)

If engine oil temperature is below -40C (-40F), the engine must be preheated prior to conducting a start.

If the battery has been cold soaked for 2 hrs or longer at ambient surface temperature of -18C (0F) or lower, it must be preheated to above -18C (0F) prior to start.

The Engine Indicating System (EIS) may take 1 to 6 minutes to become usable after power is applied when cold soaked below -10C (+14F)

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6
Q

STARTER CYCLE LIMITS

Three engine starts per __. Three cycles of operation with a __ rest period between cycles is permitted.

A

STARTER CYCLE LIMITS

Three engine starts per 30 minutes. Three cycles of operation with a 60 second rest period between cycles is permitted.

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7
Q

BATTERY LIMITATIONS

The battery temperature warning system must be operational for all __ and __ operations.

Battery cycle limitations: __ engine starts per hour.

Three generator assisted cross starts are equal to __ battery start.

If an external power unit is used for start, __ battery cycle is counted.

A

BATTERY LIMITATIONS

The battery temperature warning system must be operational for all ground and flight operations.

Battery cycle limitations: 3 engine starts per hour.

Three generator assisted cross starts are equal to 1 battery start.

If an external power unit is used for start, no battery cycle is counted.

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8
Q

GROUND OPERATION LIMITATIONS

Maximum generator current (per generator) - ?

Limit ground operation of pitot/static heat to __ minutes to preclude damage to the pitot tubes and AOA vane.

Ground operation at >75% N2 engine RPM with engine, wing, and/or windshield anti-ice on is limited to __ minutes. Do not operate with the wing anti-ice on more than __ minute after the WING ANTI-ICE L/R annunciators have extinguished.

A

GROUND OPERATION LIMITATIONS

Maximum generator current (per generator) - 200 Amps

Limit ground operation of pitot/static heat to 2 minutes to preclude damage to the pitot tubes and AOA vane.

Ground operation at >75% N2 engine RPM with engine, wing, and/or windshield anti-ice on is limited to 2 minutes. Do not operate with the wing anti-ice on more than 1 minute after WING ANTI-ICE L/R annunciators have extinguished.

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9
Q

GROUND OPERATION LIMITATIONS

Ambient surface temperature must be obtained from the __ display at the bottom of each __, with either or both engines operating, or from an appropriate ground station. The SAT display is unreliable on the ground.

A

GROUND OPERATION LIMITATIONS

Ambient surface temperature must be obtained from the RAT display at the bottome of each PFD, with either or both engines operating, or from an appropriate ground station. The SAT display is unreliable on the ground.

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10
Q

FUEL LIMITATIONS

Fuel boost pumps - ON; when FLUEL LOW LEVEL L and/or R caution lights illuminate or at __ pounds or less indicated fuel.

Maximum approved fuel imbalance is __ lbs. A fuel imbalance of __ lbs. has been demonstrated for emergency return.

EGME/DIEGME additive is __ for use, but not required, at a concentration not to exceed 0.15% volume.

A

FUEL LIMITATIONS

Fuel Boost Pumps - ON; when FUEL LOW LEVEL L and/or R caution lights illuminate or at 210 lbs or less indicated fuel.

Maximum approved fuel imbalance is 200 lbs. A fuel imbalance of 600 lbs. has been demonstrated for emergency return.

EGME/DIEGME additive is approved for use, but not required, at a concentration not to excee 0.15% volume.

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11
Q

UNUSABLE FUEL LIMITATIONS

Fuel remaining in the fuel tanks when the fuel quality indicator reads zero is ___ in flight.

A

UNUSABLE FUEL LIMITATIONS

Fuel remaining in the fuel tanks when the fuel quantity indicator reads zero is not useable in flight.

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12
Q

SPEED LIMITATIONS

Maximum Operating Limit Speeds
Mmo (+29,300’) - ?
Vmo (8,000-29,300’) - ?
Vmo (-8,000’) - ?

Minimum Flap Extended Speed - Vfe
TAKEOFF AND APPROACH position (15 deg) - ?
LAND position (35 deg) - ?
Maximum speed with flaps failed to Ground Flaps (55 deg) - ?

A

SPEED LIMITATIONS

Maximum Operating Limit Speeds
Mmo (+29,300’) - 0.737 Mach (indicated)
Vmo (8,000-29,300’) - 278 KIAS
Vmo (-8,000’) - 260 KIAS

Maximum Flap Extended Speed - Vfe
TAKEOFF AND APPROACH position (15 deg) - 200 KIAS
LAND position (35 deg) - 161 KIAS
Maximum speed with flaps failed to Ground Flaps (55 deg) - 140 KIAS

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13
Q

SPEED LIMITATIONS

Maximum Landing Gear
Extended Speed - Vle - ?
Operating Speed - Vlo (extending) - ?
Operating Speed - Vlo (retracting) - ?

A

SPEED LIMITATIONS

Maximum Landing Gear
Extended Speed - Vle - 200 KIAS
Operating Speed - Vlo (extending) - 200 KIAS
Operating Speed - Vlo (retracting) - 200 KIAS

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14
Q

SPEED LIMITATIONS

Maximum speed brake operation speed - Vsb - ?
Maximum autopilot operation speed - ?
Minimum speed for sustained flight in icing conditions (except takeoff, approach, and landing) - ?

A

SPEED LIMITATIONS

Maximum speed brake operation speed - Vsb - No limit
Maximum autopilot operation speed - 278 KIAS or 0.737 Mach
Minimum speed for sustained flight in icing conditions (except takeoff, approach, and landing) - 180 KIAS

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15
Q

GROUND FLAPS LIMITATIONS

Intentional selection of Ground Flaps in flight is ___.
The ground flaps position is not locked out in flight. Selection of ground flaps will significantly increase __ and ___.

A

GROUND FLAPS LIMITATIONS

Intentional selection of Ground Flaps in flight is prohibited.

The ground flaps position is not locked out in flight. Selection of ground flaps will significantly increase drag and sink rate.

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16
Q

TAKEOFF AND LANDING OPERATIONAL LIMITS

Maximum altitude limit - ?

A

TAKEOFF AND LANDING OPERATIONAL LIMITS

Maximum altitude limit - 14,000’

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17
Q

TAKEOFF AND LANDING OPERATIONAL LIMITS

Maximum tailwind component - ?
Minimum ambient temperature - ?
Cabin temperature must be held at or above 0C (+32F) for a minimum of __ minutes prior to takeoff after a prolonged ground cold soak period (2 hours or longer) at ambient temperatures of -10C (+14F) or colder.

A

TAKEOFF AND LANDING OPERATIONAL LIMITS

Maximum tailwind component - 10 Kts
Minimum ambient temperature - -54C (-65F)
Cabin temperature must be held at or above 0C (+32F) for a minimum of 20 minutes prior to takeoff after a prolonged ground cold soak period (2 hours or longer) at ambient temperatures of -10C (+14F) or colder.

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18
Q

TAKEOFF AND LANDING OPERATIONAL LIMITS

The autopilot and yaw damper must be __ for takeoff and landing.

Engine synchronizer must be __ for takeoff and landing.

Takeoff is prohibited if the __ system is inoperative.

Cabin must be ___ for takeoff and landing.

Take offs and landings are limited to __ runway surfaces.

A

TAKEOFF AND LANDING OPERATIONAL LIMITS

The autopilot and yaw damper must be OFF for takeoff and landing.

Engine synchronizer must be OFF for takeoff and landing.

Takeoff is prohibited if the antiskid system is inoperative.

Cabin must be depressurized for takeoff and landing.

Takeoffs and landings are limited to paved runway surfaces.

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19
Q

TAKEOFF AND LANDING OPERATIONAL LIMITS

Speed brakes must be retracted prior to __ feet AGL before landing.

Extending Ground Flaps during touch and go landings is ___.

The GROUND ILDE switch must be in the __ position when conducting touch and go landings. For normal takeoff operations, the GROUND IDLE switch bust be in the ___ position.

A

TAKEOFF AND LANDING OPERATIONAL LIMITS

Speed brakes must be retracted prior to 50’ AGL before landing.

Extending Ground Flaps during touch and go landings is prohibited.

The GROUND IDLE switch must be in the HIGH position when conducting touch and go landings. For normal takeoff operations, the GROUND IDLE switch must be in the NORMAL position.

20
Q

TAKEOFF AND LANDING OPERATIONAL LIMITS

Installed main gear tires must be of the same __.

Maximum tire ground speed - ?

A

TAKEOFF AND LANDING OPERATIONAL LIMITS

Installed main gear tires must be of the same brand.

Maximum tire ground speed - 165 Kts

21
Q

ENROUTE OPERATIONAL LIMITS

Maximum operating altitude - ?
Maximum generator current
Up to 41,000’ (per generator) - ?
Above 41,000’ (per generator) - ?

Maximum altitude for extension of flaps and/or landing gear - ?

Maximum operating altitude with inoperative Yaw Damper - ?

A

ENROUTE OPERATIONAL LIMITS

Maximum operating altitude - 45,000’

Maximum generator current
Up to 41,000’ (per generator) - 300 Amps
Above 41,000’ (per generator) - 250 Amps

Maximum altitude for extension of flaps and/or landing gear - 18,000’

Maximum operating altitude with inoperative Yaw Damper - 30,000’

22
Q

CABIN PRESSURIZATION LIMITATIONS

Normal cabin pressurization limitations - ?

A

CABIN PRESSURIZATION LIMITATIONS

Normal cabin pressurization limitations - 0.0 to 8.9 PSI +/- 0.1 PSI differential

23
Q

ICING LIMITATIONS

Icing conditions may exist when the indicated RAT in flight is ___ or below, and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet, or ice crystals).

Icing conditions on the ground exist when the OAT or indicated RAT is ___ or below and, where surface snow, slush, ice or standing water may be ingested by the engines, or freeze on engine nacelles, or engine sensor probes.

A

ICING LIMITATIONS

Icing conditions may exist when the indicated RAT in flight is +10C (+50F) or below, and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet, or ice crystals).

Icing conditions on the ground exist when the OAT or indicated RAT is +10C (+50F) or below and, where surface snow, slush, ice or standing water may be ingested by the engines or freeze on engine nacelles, or engine sensor probes.

24
Q

ICING LIMITATIONS

Minimum airspeed for sustained flight in icing conditions (except approach and landing) is __ KIAS

In icing conditions, operating the airplane at other than flaps __ for an extended period of time (except approach and landing) is prohibited.

Minimum engine N2 speed for effective wing anti-icing - ?

A

ICING LIMITATIONS

Minimum airspeed for sustained flight in icing conditions (except approach and landing) is 180 KIAS.

In icing conditions, operating the airplane at other than flaps 0 for an extended period of time (except approach and landing) is prohibited.

Minimum engine N2 speed for effective wing anti-icing - 75% N2

25
Q

ICING LIMITATIONS

Minimum temperature for operation of tail deicing boots (indicated RAT) - ?

The WING/ENGINE ANTI-ICE switches must be ___ or ___ for operations with indicated RAT of +10C (+50F) or below when flight free of visible moisture cannot be assured. Failure to observe this limitation may result in ENG CTRL SYS FAULT L/R annunciations due to ice accumulation on the engine __ probe.

A

ICING LIMITATIONS

Minimum temperature for operation of tail deicing boots (indicated RAT) - -35C (-31F)

The WING/ENGINE ANTI-ICE switches must be ENG ON or WING/ENG for operations with indicated RAT of +10C (+50F) or below when flight free of visible moisture cannot be assured. Failure to observe this limitation may result in ENG CTRL SYS FAULT L/R annunciations due to ice accumulation on the engine PT2/TT2 probe.

26
Q

ICING LIMITATIONS

__ wing icing inspection lights must be operative prior to flight into known or forecast icing conditions at night.

Severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues:

1. Unusually extensive ice accumulation on the \_\_ and \_\_ in areas not normally observed to collect ice.
2. Accumulation of ice on the upper surface of the wing that extends more than \_\_ aft of the heated leading edge.
A

ICING LIMITATIONS

All wing icing inspection lights must be operative prior to flight into known or forecast icing conditions at night.

Severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues:

1. Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice.
2. Accumulation of ice on the upper surface of the wing that extends more than 12 to 18 inches after of the heated leading edge.
27
Q

ICING LIMITATIONS

If one or more of these visual cues exist (from previous card):

  1. Use of the autopilot is ___.
  2. Immediately request priority handling from ATC to facilitate a route or altitude change to __ the icing conditions.
  3. Leave flaps in current position, do not extend or retract,
  4. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties.
  5. If unusual or uncommanded roll control movement is observed, reduce ___.
A

ICING LIMITATIONS

If one or more of these visual cues exist (from previous card):

  1. Use of the autopilot is prohibited.
  2. Immediately request priority handling from ATC to facilitate a route or altitude change to exit the icing conditions.
  3. Leave flaps in current position, do not extend or retract.
  4. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties.
  5. If unusual or uncommanded roll control movement is observed, reduce AOA.
28
Q

ICING LIMITATIONS

Since the autopilot, when installed and operating, may __ tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when:

  1. Unusual __ trim is required while the airplane is in icing conditions
  2. Autopilot trim warnings are encountered while the airplane is in icing conditions.
A

ICING LIMITATIONS

Since the autopilot, when installed and operating, may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when:

  1. Unusual lateral trim is required while the airplane is in icing conditions.
  2. Autopilot trim warnings are encountered while the airplane is in icing conditions.
29
Q

ICING LIMITATIONS

Takeoff is limited to the __ configuration per Section II, Takeoff and Landing Operational Limitis when Type II, III, or IV anti-ice fluid has been applied to the airplane.

Takeoff performance is degraded when Type II, III, or IV anti-ice fluid has been applied to the airplane. The fluid that remains on the airplane during takeoff causes the elevator forces at rotation and the takeoff distance to increase. Determine the normal flaps up takeoff field length and apply any adjustments to speed and field length required by runway gradients or runway contamination; then multiply the resulting takeoff field length by the appropriate factor from the following table to determine the takeoff field length with Type II, III, IV anti-ice fluid applied to the airplane:

FLAPS UP TAKEOFF FIELD LENGHT/FACTOR
Dry Runway/?
Wet Runway/?
Contaminated Runway/?

A

ICING LIMITATIONS

Takeoff is limited to the flaps up configuration per Section II, Takeoff and Landing Operational Limits when Type II, III, or IV anti-ice fluid has been applied to the airplane.

Takeoff performance is degraded when Type II, III, or IV anti-ice fluid has been applied to the airplane. The fluid that remains on the airplane during takeoff causes the elevator forces at rotation and the takeoff distance to increase. Determine the normal flaps up takeoff field lenght and apply any adjustments to speed and field lenght required by runway gradients or runway contamination; then multiply the resulting takeoff field lenght by the appropriate factor from the following table to determine the takeoff field lenght with Type II, III, IV anti-ice fluid applied to the airplane:

FLAPS UP TAKEOFF FIELD LENGHT/FACTOR
Dry Runway - 1.30
Wet Runway - 1.30
Contaminated Runway - 1.15

30
Q

ICING LIMITATIONS

Takeoff is prohibited with the following forms of contamination:
1. With frost adhering to the following critical areas:
A. ____
B. Upper wing surface
C. Windshield

  1. With ice, snow, or slush adhering to the following critical areas:
    A. ___
    B. Flight control surface including all hinge gaps
    C. H stab, V stab
    D. Engine inlets
    E. Top of engine pylons
    F. Top of fuselage
    G. All static ports
    H. AOA vanes
    I. Windshield
    J. Upper surface of nose forward of the windshield
A

ICING LIMITATIONS

Takeoff is prohibited with the following forms of contamination:
1. With frost adhering to the following critical areas:
A. Wing leading edge
B. Upper wing surfaces
C. Windshield

  1. With ice, snow, or slush adhering to the following critical areas:
    A. Wing leading edge and upper wing surface
    B. Flight control surfaces including all hinge gaps
    C. H stab, V stab
    D. Engine inlets
    E. Top of engine pylons
    F. Top of fuselage
    G. All static ports
    H. AOA vanes
    I. Windshield
    J. Upper surface of nose forward of the windshield
31
Q

ICING LIMITATIONS

  1. A visual and ____ check of the wing leading edge and 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 then __ or if it cannot be determined that the wing fuel temperature is above 0C (32F) and any of the following conditions exist:

A. There is visible moisture present (RA, DZ, sleet, SN, FG, etc); or
B. Water is present on the upper wing surface: or
C. The difference between the dew point and the outside air temperature is 3C (5F) or less: or
D. The atmospheric conditions have been conducive to frost formation.

A

ICING LIMITATIONS

  1. A visual and tactile (hand on surface) check of the wing leading edge and 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 10C (50F) or it cannot be determined that the wing fuel temperature is above 0C (32F) and any of the following conditions exist:

A. There is visible moisture present (RA, DZ, sleet, SN, FG, etc): or
B. Water is present on the upper wing surface: or
C. The difference between the dew point and the outside air temperature is 3C (5F) or less; or
D. The atmospheric conditions have been conducive to frost formation.

32
Q

AUTO PILOT LIMITATIONS

The autopilot minimum engage height, during climb following takeoff or go-around, is __ feet AGL.

The autopilot minimum use height is:
A. ILS approach (CAT 1) __ feet AGL
B. Non-precision approaches __ feet AGL
C. Cruise __ feet AGL

A

AUTO PILOT LIMITATIONS

The autopilot minimum engage height, during climb following takeoff or go-around, is 350’ AGL

The autopilot minimum use height is:
A. ILS approach (CAT 1) 180’ AGL
B. Non-precision approaches 350’ AGL
C. Cruise 1000’ AGL

33
Q

FUEL LIMITS

Total fuel - ?

A

FUEL LIMITS

Total fuel - 4710 Lbs (703 US Gal)

34
Q

Maximum operating oil consumption (per engine) - ?

A

Maximum operating oil consumption (per engine) - 0.023 gal/hr

35
Q

ENGINE LIMITATIONS

ITT - During start - ?
ITT - Takeoff - ?
ITT - Flight -
ITT - Time to light off, start sequence - ?

A

ENGINE LIMITATIONS

ITT - During start - 1000 C (15 seconds only)
ITT - Takeoff - 877 C Max (5 min 2 engines, 10 min 1 engine)
ITT - Flight - 840 C Max continuous
ITT - Time to light off, start sequence - 10 sec

36
Q

ENGINE LIMITATIONS

N1 - Max takeoff and flight - ?
N2 - Starting - ?
N2 - Start sequence ends - ?

A

ENGINE LIMITATIONS

N1 - Max takeoff and flight - 102.8%
N2 - Starting - 8%
N2 - Start sequence ends - 45%

37
Q

ENGINE LIMITATIONS

N2 - Ground Idle - ?
N2 - Flight idle - ?
N2 - Anti-ice idle - ?
N2 - Max continuous - ?

A

ENGINE LIMITATIONS

N2 - Ground idle - 53.4 +/- 2.5%
N2 - Flight idle - 60.7 +/- 2.5%
N2 - Anti-ice idle - 70%
N2 - Max continuous - 100%

38
Q

HOT BATTERY BUS

A

HOT BATTERY BUS

Voltmeter
ELT
Emer battery pack (2G lateral load for Emer Exit Lights)
Emer Lights
Lights (baggage/exit)
39
Q

EMER BATTERY BUS

A

EMER BATTERY BUS

Comm 1
Nav 1, DME 1
ADF 1 (if installed)
Transponder 1
Audio Panels 1 and 2
RTU 1 (stby HSI), RTU 2
FMS 2 (GPS 500)
AHRS 2
ADC 2
Stby ADC
L and R Stby N1
RIU L-R
Co-Pilot's P/S heat
Stby P/S heat
Stby Flight Display (internal battery 88 min)
Voltmeter
Flap control
Landing gear control/and Hydraulic control
Landing gear monitor (lights/horn)
Flood lights
40
Q

DUAL GENERATOR FAILURE

Battery switch ON, battery power will last - ?

A

DUAL GENERATOR FAILURE

Battery switch ON, battery power will last - 10 min

41
Q

Battery switch EMER, battery power will last - ?

A

Battery switch EMER, battery power will last - minimum of 30 minutes

42
Q

Do not turn battery switch ON and OFF too quickly (less than ?) so as not to interrupt a FADEC self test

A

Do not turn battery switch ON and OFF too quickly (less than 20 sec) so as not to interrupt a FADEC self test

43
Q

DEPARTURE

Prior to takeoff, the following systems must be operational and must have satisfactorily completed the preflight check in Section III, Normal Procedures:

A

DEPARTURE

Prior to takeoff, the following systems must be operational and must have satisfactorily complete the preflight check in Section III Normal Procedures:

  1. The AOA and Stall Warning system
  2. Electric Elevator Trim
  3. Rudder Bias System
  4. Flap System
  5. Flight Controls
44
Q

Channels _ and _ of the L and R ____s must be verified operational prior to takeoff

A

Channels A and B of the L and R FADECs must be verified operational prior to takeoff

45
Q

Takeoff is prohibited with:

  1. __ ___ SYS FAULT L/R caution light illuminated
  2. Anti-Skid ____
A

Takeoff is prohibited with:

  1. ENG CTRL SYS FAULT L/R caution light illuminated
  2. Anti-Skid inoperative
46
Q

LANDING AND SHUTDOWN

  1. Engine ITT must stabilize at minimum value for - ?
  2. Engine Anti-Ice must be __ for __ minutes prior to shutdown. (A FADEC fault can occur if you do not allow the _____ probes to cool off)
A

LANDING AND SHUTDOWN

  1. Engine ITT must stabilize at minimum value for 2 minutes
  2. Engine Anti-Ice must be OFF for 2 minutes prior to shutdown. (A FADEC fault can occur if you do not allow the PT2/TT2 probes to cool off)

CJ3 (5 decks)

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