DA-2000

Card Set Information

Author:
falconflyer
ID:
169336
Filename:
DA-2000
Updated:
2012-09-08 11:12:33
Tags:
falcon
Folders:

Description:
Limitations
Show Answers:

Home > Flashcards > Print Preview

The flashcards below were created by user falconflyer on FreezingBlue Flashcards. What would you like to do?


  1. 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
  2. Loading:

    Baggage compartment total / distributed loading
    1,600 Lb / 61.4 lb/sq.ft
  3. Loading:

    Payload
    5,990 Lb
  4. Loading:

    LH and RH coat compartment distributed loading
    81.9 lb/sq.ft
  5. 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.
  6. Vfe
    VFE Slats extended + flaps 10° .............200 KIAS - VFE Slats extended + flaps 20° ......................160 KIAS - VFE Slats extended + flaps 40° ......................160 KIAS
  7. Max Altitude with flaps or slats extended
    20,000 ft
  8. Vlo
    Vmo
    • 190 KIAS
    • MI 0.70
  9. Vle
    Mle
    • 245 KIAD
    • MI 0.75
  10. Vmca
    90 KIAS
  11. Vmcl
    90 KIAS
  12. Vmcg
    98 KIAS
  13. Windshield Wiper Operating Speed
    215 KIAS
  14. Window Opening Speed
    215 KIAS
  15. Max Tire Operating Speed
    195 KIAS
  16. Maneuvering Flight Load Factors Limit
    • - Flaps up ..........................+2.64 to -1.00
    • - Flaps down......................+2.00 to 0.00
  17. Va
    198 KIAS
  18. Airport pressure altitude
    -1,000 ft / +10,000 ft
  19. Runway slope
    ±2.0 %
  20. Tailwind component
    10 kt
  21. Max Operating Altitude
    47,000 ft
  22. Maximum differential pressure
    Maximum negative differential pressure
    • - Maximum differential pressure.............................9.3 psi
    • - Maximum negative differential pressure.............-0.3 psi
  23. 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
  24. 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
  25. Battery temperature
    - Amber
    - Red
    • - Amber light (WARM) at or above.......120 °F
    • - Red light (HOT) at or above................160 °F
  26. Maximum speed with ARTHUR UNIT INOPERATIVE
    260 KIAS or MI 0.76
  27. 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
  28. Approved Fuels
    • - JET A
    • - JET A-1 - Type JP-8
    • - JP B
    • - JP-4
    • - JP-5
  29. Fuel Temperature
    In flight, tank fuel temperature must be maintained at least 3 °C above the freezing point of fuel being used.
  30. Maximum fuel dissymmetry
    2,200 lb
  31. Maximum fuel feed pressure (pressure fueling system)
    50 psi / 3.5 bars
  32. Fuel Control Computer
    The Fuel Quantity Management Computer (FQMC) must be operative for take-off.
  33. 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
  34. Approved Hydraulic Fluids
    AIR 3520 or MIL-H-5606
  35. Brake kinetic energy limit
    Brake kinetic energy limit.................15,000 kJ per brake
  36. Wing Anti-ice
    The wing anti-ice should not be used with a Total Air Temperature (TAT) above 10 °C (50 °F).
  37. IRS Alignment Functionality
    between 78°15’ North and 78°15’ South latitude.
  38. 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.
  39. Passenger oxygen mask drop
    above 14,500 ft ± 500 ft
  40. APU maximum operating altitude
    35,000 ft
  41. APU maximum starting altitude
    35,000 ft
  42. APU Maximum N1 speed
    110 %
  43. APU EGT Temperature limit
    Starting
    974 °C
  44. APU EGT Temperature limit 
    Stabilized
    746 °C
  45. 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
  46. Engine Thrust Ratings
    - Take-off
    - Maximum continuous
    • - Take-off............................................ 5,888 lb
    • - Maximum continuous ...................... 5,613 lb
  47. 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%
  48. Engine Vibration Limits
    • - N1 .............................1.0 in./sec.
    • - N2 ..............................1.5 in./sec.
  49. Engine ITT limits:
    - Ground start
    - Airstart
    - Restart max. temperature
    • - Ground start.................................815 °C
    •  -Airstart.........................................890 °C
    •  -Restart max. temperature.............150 °C
  50. 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
  51. Engine ITT Limits:
    Windmilling max. temperature
    • 970 °C........10 seconds max.
    • 1,000 °C.......2 seconds max.
  52. Engine Starting Time: Ground
    • Ground start:
    • - start to light-off.....10 seconds max. after reaching 22 % N2
    • - light-off to idle......60 seconds max.
  53. Engine Starting Time: Airstart
    • - Assisted...................90 seconds
    • - Windmilling...........180 seconds
  54. Starter Re-engagement Limit
    Starter cutout N2: 53.6 %
  55. 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
  56. Oil Temperature Limits
    • - Maximum..........................................138 °C
    • - Minimum for take-off..........................30 °C
    • - Transient: for 3 min................138 to 155 °C
    • - Cold start...........................................- 40 °C
  57. Severe Turbulence Penetration:
    - Speed
    - Altitude
    - 280 KIAS max / MI 0.76 max

    - Decrease altitude to increase buffet boundary margin.
  58. Severe Turbulence Penetration:
    - Autopilot Disengaged
    • With the autopilot disengaged:
    • - Fly attitude,
    • - Avoid using the stabilizer trim,
    • - Do not chase altitude and speed.
  59. Excpetions Engine and Wing Icing Operations
    climb or cruise when the TAT is below -40 °C (-40 °F).
  60. 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.
  61. Contaminated Runway System limitations:
    -Take off
    • - Slats-flaps must be in 20° position.
    • - If runway contaminated by ice: both reversers must be operative.
  62. Contaminated Runway System limitations:
    - After take off
    • - Landing gear retraction ................Delayed 15 seconds
    • - IAS < 190 KIAS)........................ Recycle landing gear
  63. Contaminated Runway System limitations:
    - Before Landing
    • - Landing gear...............................Down
    • - PARK BRAKE..............Pull to second detent for 5 seconds  Several times
  64. 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.
  65. 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.
  66. Noise Abatement Operational Limitations
    • - Maximum pitch........................20°
    • - Speed........................................At or above V2 + 10 kt
  67. 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.

What would you like to do?

Home > Flashcards > Print Preview