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Maximum Ramp Weight
Maximum Take-Off Weight
Maximum Landing Weight
Maximum Zero Fuel Weight
Minimum Flight Weight
- - 36,700 Lb
- - 36,500 Lb
- - 33,000 Lb
- - 28,660 Lb
- - Refer to Center of gravity limits chart
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Loading:
Baggage compartment total / distributed loading
1,600 Lb / 61.4 lb/sq.ft
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Loading:
Payload
5,990 Lb
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Loading:
LH and RH coat compartment distributed loading
81.9 lb/sq.ft
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Va
198 KIAS
Full application of rudder or aileron controls, as well as maneuvers that involve angles-of-attack near the stall must be confined to speeds below VA. Rapidly alternating large rudder applications in combination with large sideslip angles may result in structural failure at any speed.
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Vfe
VFE Slats extended + flaps 10° .............200 KIAS - VFE Slats extended + flaps 20° ......................160 KIAS - VFE Slats extended + flaps 40° ......................160 KIAS
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Max Altitude with flaps or slats extended
20,000 ft
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Windshield Wiper Operating Speed
215 KIAS
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Window Opening Speed
215 KIAS
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Max Tire Operating Speed
195 KIAS
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Maneuvering Flight Load Factors Limit
- - Flaps up ..........................+2.64 to -1.00
- - Flaps down......................+2.00 to 0.00
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Airport pressure altitude
-1,000 ft / +10,000 ft
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Max Operating Altitude
47,000 ft
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Maximum differential pressure
Maximum negative differential pressure
- - Maximum differential pressure.............................9.3 psi
- - Maximum negative differential pressure.............-0.3 psi
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The autopilot is certified to the minimum height as follows:
- Coupled ILS approach:
- Radioaltimeter operative
- Radioaltimeter inoperative
- Cruise
- Non precision approach
- The autopilot is certified to the minimum height as follows:
- - Coupled ILS approach:
- - Radioaltimeter operative.................70 ft
- - Radioaltimeter inoperative............160 ft
- - Cruise.........................................1,000 ft
- - Non precision approach................250 ft
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Maximum engine generator output in flight
Maximum engine generator output on ground
- Maximum engine generator output in flight:
- - Stabilized ...................................400 A
- - Transient (5 sec.)........................800 A
- - Transient (40 sec.)......................600 A
- - Transient (160 sec.)....................500 A
- Maximum engine generator output on ground:
- - Basic generators.... .....................300 A
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Battery temperature
- Amber
- Red
- - Amber light (WARM) at or above.......120 °F
- - Red light (HOT) at or above................160 °F
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Maximum speed with ARTHUR UNIT INOPERATIVE
260 KIAS or MI 0.76
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Maximum altitude for slats / flaps operation
20,000 ft
Above 20,000 ft, do not establish or maintain a configuration with the flaps or the slats extended
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Approved Fuels
- - JET A
- - JET A-1 - Type JP-8
- - JP B
- - JP-4
- - JP-5
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Fuel Temperature
In flight, tank fuel temperature must be maintained at least 3 °C above the freezing point of fuel being used.
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Maximum fuel dissymmetry
2,200 lb
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Maximum fuel feed pressure (pressure fueling system)
50 psi / 3.5 bars
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Fuel Control Computer
The Fuel Quantity Management Computer (FQMC) must be operative for take-off.
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Usable Fuel Quantity
- - LH wing + half center wing box........906 Lb
- 6,070 Gal
- - RH wing + half center wing box........908 Lb
- 6,085 Gal
- - Airplane total capacity........................1,814 Lb
- 12,155 Gal
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Approved Hydraulic Fluids
AIR 3520 or MIL-H-5606
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Brake kinetic energy limit
Brake kinetic energy limit.................15,000 kJ per brake
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Wing Anti-ice
The wing anti-ice should not be used with a Total Air Temperature (TAT) above 10 °C (50 °F).
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IRS Alignment Functionality
between 78°15’ North and 78°15’ South latitude.
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Use of the FMS during approach is forbidden:
If the APPR or GPS APPR annunciation in the PFD is not green 2 NM before the FAF.
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Passenger oxygen mask drop
above 14,500 ft ± 500 ft
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APU maximum operating altitude
35,000 ft
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APU maximum starting altitude
35,000 ft
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APU Maximum N1 speed
110 %
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APU EGT Temperature limit
Starting
974 °C
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APU EGT Temperature limit
Stabilized
746 °C
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APU Maximum generator output:
- Transient
- Stabilized
- Transient:
- - 40 seconds ...................................450 A
- - 180 seconds .................................375 A
- Stabilized:
- - 0 to 10,000 ft................................300 A
- - 10,000 to 25,000 ft........................250 A
- - 25,000 to 35,000 ft........................200 A
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Engine Thrust Ratings
- Take-off
- Maximum continuous
- - Take-off............................................ 5,888 lb
- - Maximum continuous ...................... 5,613 lb
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Engine Rotor Speed Limits:
Maximum / Normal take-off
Maximum continuous
- - Maximum Take-off............N1: 96.7 % N2: 106%
- - Maximum continuous........N1: 96.7 % N2: 104.9%
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Engine Vibration Limits
- - N1 .............................1.0 in./sec.
- - N2 ..............................1.5 in./sec.
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Engine ITT limits:
- Ground start
- Airstart
- Restart max. temperature
- - Ground start.................................815 °C
- -Airstart.........................................890 °C
- -Restart max. temperature.............150 °C
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Engine ITT Limits:
- Max. take-off (APR)
- Normal take-off
- Max. continuous
- - Max. take-off (APR).......890 °C (5 minutes max.)
- - Normal take-off .............864 °C (5 minutes max.)
- - Max. continuous.............861 °C
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Engine ITT Limits:
Windmilling max. temperature
- 970 °C........10 seconds max.
- 1,000 °C.......2 seconds max.
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Engine Starting Time: Ground
- Ground start:
- - start to light-off.....10 seconds max. after reaching 22 % N2
- - light-off to idle......60 seconds max.
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Engine Starting Time: Airstart
- - Assisted...................90 seconds
- - Windmilling...........180 seconds
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Starter Re-engagement Limit
Starter cutout N2: 53.6 %
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Oil Pressure Limits
- - Operating range.........................................60 to 85 psi
- - Transient (3 min. max.)............................85 to 100 psi
- - Minimum (at IDLE)............................................30 psi
- - Cold start: oil T° < 0 °C (2.5 min. max.)...........135 psi
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Oil Temperature Limits
- - Maximum..........................................138 °C
- - Minimum for take-off..........................30 °C
- - Transient: for 3 min................138 to 155 °C
- - Cold start...........................................- 40 °C
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Severe Turbulence Penetration:
- Speed
- Altitude
- 280 KIAS max / MI 0.76 max
- Decrease altitude to increase buffet boundary margin.
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Severe Turbulence Penetration:
- Autopilot Disengaged
- With the autopilot disengaged:
- - Fly attitude,
- - Avoid using the stabilizer trim,
- - Do not chase altitude and speed.
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Excpetions Engine and Wing Icing Operations
climb or cruise when the TAT is below -40 °C (-40 °F).
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A runway is considered contaminated:
- more than 25 % of the surface is covered by either:
- - 3 mm (0.12 in) of standing water, or
- - Slush or loose snow, equivalent to more than 3 mm of water
- - Compacted snow, any depth, or - Ice, any depth.
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Contaminated Runway System limitations:
-Take off
- - Slats-flaps must be in 20° position.
- - If runway contaminated by ice: both reversers must be operative.
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Contaminated Runway System limitations:
- After take off
- - Landing gear retraction ................Delayed 15 seconds
- - IAS < 190 KIAS)........................ Recycle landing gear
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Contaminated Runway System limitations:
- Before Landing
- - Landing gear...............................Down
- - PARK BRAKE..............Pull to second detent for 5 seconds Several times
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Windshear Procedure After V1
- After V1:
- - Check maximum take-off thrust
- - At VR: Perform normal rotation at 3°/sec (maximum 20° pitch angle)
- - Keep take-off configuration, do not retract landing gear, - Fly at stall onset (top of red tape on airspeed indicator)
- - PNF monitors radio-altimeter and announces readings - - Attempt to fly a positive radio-altimeter trend,
- - Allow pitch to increase up to 30° (airspeed / stall onset permitting),
- - When exiting windshear, resume normal operation.
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Windshear Procedure During Approach
- - Disconnect autopilot
- - Level wings
- - Fly pitch angle up to stall onset.
- - Set maximum take-off thrust
- - Retract AIRBRAKES
- - Retract SLATS + FLAPS to 20°.
- At pilot's discretion (considering radio altimeter trend)
- - Retract landing gear.
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Noise Abatement Operational Limitations
- - Maximum pitch........................20°
- - Speed........................................At or above V2 + 10 kt
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Noise Abatement Normal Procedures
- - Take-off with slats/flaps 20°
- - Rotate at 3° per second,
- - Increase the pitch angle up to 20° maximum
- - V2+10.
- - The take-off thrust is maintained up to 1,500 ft AAL, then the thrust is reduced to the MAX CLIMB thrust.
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