B717 Limitations

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Author:
captjen83
ID:
90123
Filename:
B717 Limitations
Updated:
2011-09-03 02:13:07
Tags:
HAL
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Description:
B717 Limitations
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  1. Maximum Emergency Gear Extension Speed
    230 KIAS
  2. Do not takeoff if Brake Temperature exceeds
    170 C, unless other data is available and utilized
  3. Do NOT set parking brake if this Alert is displayed
    "BRAKE OVERHEAT"
  4. Minimum Brake Pressure for parking
    2000 psi, to assure at least 8 hours of parking time
  5. Gear Load Limit at landing (at Max Takeoff weight)
    360 fpm
  6. Gear Load Limit at landing (at Max Landing weight)
    600 fpm
  7. Cumulative systems tolerance may dictate a Maximum Gear Retraction Speed of
    220 KIAS, to achieve positive gear retraction
  8. Maximum Gear Retraction Speed
    250 KIAS or .70 Mach
  9. Maximum Gear Extension and Extended Speed
    300 KIAS or .70 Mach
  10. Tripped Hydraulic Pump Circuit Breakers
    Should not be reset
  11. The Maximum permissable Fuel Imbalance under all operating conditions
    1500 pounds
  12. Fuel may be Loaded into the Center Tank for Ballast purposes provided the following Conditions are met:
    1. Completion of the flight, including reserve fuel, does not require the use of ballast fuel.

    AND

    2. The ZFW and CG includes the weight of the ballast fuel.
  13. After Takeoff, Center Tank Fuel should be Emptied
    Prior to Main Tank Fuel.

    If Ballast Fuel is being carried, the Center Tank shall be emptied to the Ballast Value prior to using Maing Tank Fuel.
  14. If Main Fuel Tanks are NOT Full, Fuel may be added to the Center Tank until Full if:
    ZFW and CG plus the Center Tank Fuel do not Exceed the MZFW and CG limitations.
  15. If Main Fuel Tanks ARE Full, additional Fuel may be Added to the Center Tank to attain:
    Maximum Ramp Weight
  16. Fuel Management and Loading Limitations do NOT apply to:
    Ballast Fuel
  17. Minimum Fuel Temperature
    • Jet A: -40 C
    • Jet A1: -47 C
  18. Tripped Fuel Pump Circuit Breakers
    Should not be reset
  19. Fuel is Limited in Density from
    6.3 to 7.1 pounds per US gallon
  20. Maximum Fuel Temperature
    54 C
  21. The Maximum Demonstrated Crosswind Component for Landing
    38 knots
  22. The Maximum Takeoff Crosswind Component
    40 knots because of engine limitations
  23. Do NOT move Spoiler/Speedbrake Lever to Ground Spoiler Position
    In Flight
  24. Speedbrakes must NOT be used with Flaps Extended Beyond
    20 degrees
  25. Minimum Approach or Missed Approach Speed with "RUDDER PWR OFF" displayed (until landing is assured)
    144 KIAS
  26. Rudder Hydraulic Power must be "ON" for
    Takeoff
  27. Maximum Flaps Usage Altitude
    20,000 feet
  28. Minimum Flap Setting for Takeoff
    5 degrees
  29. "Design Speeds" Chart located in
    PERFORMANCE Section of FCOM
  30. Maximum Flap Speeds
    • 0 to 10 degrees: 280 KIAS/.57 Mach
    • 10.1 to 20 degrees: 240 KIAS/.57 Mach
    • 25 degrees: 220 KIAS/.57 Mach
    • 40 degrees: 200 KIAS/.57 Mach
  31. Maximum Slats Extend Speed
    280 KIAS/.57 Mach
  32. Slats must be Extended for
    Takeoff
  33. Vmo, Mmo
    • 340 KIAS, from sea level to FL260
    • .82 Mach, above FL260
  34. Powerback Operations
    Not Approved for HAL
  35. Assymetric Thrust should NOT be used for
    Directional Control
  36. Use of Reverse Thrust in Flight
    Prohibited
  37. Engine Starter Duty Cycle
    3-3-15-15:

    • 3 Start Attempts
    • Maximum Duration of 3 Minutes Per Attempt
    • Minimum of 15 Seconds Between Attempts
    • Allow 15 Minutes of Cooling before Further Attempts
  38. Do not Takeoff with either of these Alerts Displayed on Primary Engine Display
    "U/L" or "REV"
  39. Use of N1 Mode for Takeoff is
    Prohibited
  40. If Maximum Allowable Starting Temperature is Exceeded
    Engine should be Shutdown and Inspected
  41. Normal Oil Pressure
    45 psi or greater

    Oil pressure less than 35 psi is undesirable and should be tolerated only for completion of the flight, preferably at reduced power settings.
  42. If Any Engine Parameter is Exceeded
    A Maintenance Log Entry must be made
  43. Maximum TGT during Engine Start
    700 C
  44. Maximum Continuous Thrust Limits
    • No Time Limit
    • N1, N2, Min Oil Press, Max Oil Temp: Red Line
    • Max TGT: Amber Line
  45. Takeoff Thrust Time Limit
    5 minutes, except

    10 minutes, in the event of Engine Failure during Takeoff or Go Around.
  46. APU Maximum EGT and Rotor Speed
    Red Boxed Digits when Limits Exceeded
  47. APU Air must be "OFF" for
    Takeoff
  48. APU Starter Motor Duty Cycle
    3 Consecutive Start Attempts.

    Must Wait 30 Minutes prior to Further Attempts
  49. Maximum Altitude for APU Start
    FL 370
  50. During Ground Alignment of Inertial Reference System
    Airplane must be Stationary
  51. Use of Flight Director or Coupled Windshear Guidance is Prohibited with
    One Engine Inoperative
  52. Maximum Airspeed with Malfunctioning or Inoperative Mach Trim Compensator (MTC)
    .78 Mach
  53. If "STAB OUT OF TRIM" Alert displayed for More than 3 Seconds After airplane is Stabilized and Tracking Glideslope do NOT
    Conduct an Auto Coupled (ILS) Approach
  54. Autopilot Must be Disengaged No Lower than
    The Applicable Precision or Non-Precision Approach Minimums Minus 50 Feet
  55. On Takeoff, Do NOT Engage the Autopilot Below
    200 Feet AGL
  56. If Air Conditioning is Used for Takeoff, the FLOW Switch MUST be in
    NORM Position
  57. If Operating Pressurization in Manual Mode, Takeoff and Land
    Unpressurized
  58. Maximum Emergency Relief Pressure
    8.27 psi
  59. Maximum Cabin Differential Pressure
    7.86 psi
  60. Reduced Thrust Takeoffs on Wet Runways are Permitted when
    Using Wet Runway Takeoff Performance
  61. Reduced Thrust Takeoffs on Contaminated Runways are Permitted when
    NOT Permitted on Runways Contaminated with Standing Water, Loose Snow, Slush, Compacted Snow or Wet Ice
  62. When Using Reduced Thrust, the Operator Must
    Establish a means to Verify the Availability of Takeoff Thrust to Ensure Engine Deterioration does Not Exceed Authorized Limits
  63. Reduced Thrust Takeoffs are NOT Permitted where Items Affecting Performance Cause
    A Significant Increase in Crew Workload

    ie: INOP Equipment (engine gauges, anti-skid, or engine systems requiring additional performance) and/or

    Non-Standard Operations: Any situation requiring a non-standard takeoff technique
  64. The Slide Girt Bars Must be Inserted into the Floor Fittings for
    Departure, and Remain in Position Until Arrival at the Unloading Ramp
  65. The EMERGENCY Operating Handle on the Aft Pressure Bulkhead Door Must be
    Exposed, from Departure until Arrival at the Unloading Ramp
  66. The NORMAL Operating Handle on the Aft Pressure Bulkhead Door Must be
    Covered, from Departure until Arrival at the Unloading Ramp
  67. The Emergency Light System Must be Armed for
    All Flight Operations
  68. Wing Landing Light Motors Should be Allowed to Cool for
    • 1.5 Minutes - After Initial Extension or Retraction and
    • 3.5 Minutes - After Subsequent Extension or Retraction
  69. Lamps should NOT be "ON" in Still, Ambient Air for More than
    10 Minutes, due to Excessive Heat Buildup
  70. Maximum Weights (488HA, 489HA, 490HA)
    • Max Taxi: 190,000
    • Max Takeoff: 180,000
    • Max Landing: 110,000
    • Max ZFW: 100,500
  71. Maximum Weights (ALL aircraft except 488, 489, 490HA)
    • Max Taxi: 150,000
    • Max Takeoff: 140,000
    • Max Landing: 110,000
    • Max ZFW: 96,000
  72. Maximum Runway Slope for Takeoff and Landing
    +1.7% to -2.0%
  73. Maximum Tailwind Component for Takeoff and Landing
    10 knots
  74. When Crosswind Component Exceeds 40 knots or Tailwind Component Exceeds 10 knots, Operations are Limited to
    Taxi and Ground Handling with N1 Limited to 50%
  75. Maximum Certified Altitude
    FL 370
  76. ACARS is Limited to the Transmission and Receipt of Messages which
    • Do NOT Create an Unsafe Condition if:
    • Message or parts are delayed or not received
    • Message is delivered to wrong recipient
    • Message content is corrupted
  77. Windshielf Anti-Ice Must be ON and Checked for
    All Flight Operations
  78. If Window is Cracked, do NOT Operate
    Windshield Anti-Ice or Anti-Fog
  79. Maximum Airspeed Below 10,000 Feet with Windshield Heat INOP on Any Windshield
    315 KIAS
  80. Maximum Airspeed Below 10,000 Feet with Cracked Windshield
    • Outer Glass: 315 KIAS
    • Inner Glass: 235 KIAS
  81. When Operating in "IRS NAV" Only
    The Airplane Position Must be Verified Using Other Navigational Systems if Available
  82. If Computed V-Speeds Cannot be Confirmed or Displayed on the PFD Speed Tape, the Flight Crew Must
    Verify Any Displayed V-Speeds on the MCDU to AFM Derived Data Other than the FMS Before Entering them Manually
  83. FMS Computed V1, Vr and V2 Must be Verified to AFM Derived Data Unless Two Conditions Are Met
    • Dry Runway
    • Balanced Field Length
  84. Minimum Altitude for "FMS PROF" Mode
    MDA or DA for the Approach Being Used
  85. For ILS Approaches with INOP Glideslope, "FMS PROF" Mode and its Vertical Deviation Indication Must NOT be Used for Descent Beyond
    The FAF
  86. Range Calculations, Fuel Management and Engine Out Terrain Clearance Must NOT be Predicated on
    FMS Use
  87. When Using "FMS NAV" as a GPS Approach
    • The Reference Navaid Data for the Approach Need NOT be Displayed but
    • RNP Value Must be Reduced to 0.3
  88. Do NOT use Amber Vmin Foot Displayed on PFD Airspeed Tape for Setting Approach or Landing Target Speeds if
    The Airplane has NOT Transitioned Through the Acceleration Altitude Defined on FMS "TAKEOFF" Page

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