DC-10

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Author:
MGeorge
ID:
62659
Filename:
DC-10
Updated:
2011-01-29 17:16:56
Tags:
LIMITATIONS SPECIFICATIONS
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LIMITATIONS AND SPECIFICATIONS
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  1. Do not engage Autopilot to CMD and/or engage a Flight Director when
    Airplane rate of climb exceeds 4000 feet per minute, or rate of descent exceeds 8000 feet per minute.
  2. The Autopilot must be disengaged when
    Operating on Emergency Power.
  3. Do not automatically capture glide slope above
    250 knots.
  4. The Autopilot must be disengaged for
    Split Flap/Slat handle operation.
  5. If the AP OUT OF TRIM light is illuminated for over three seconds after airplane is stabilized and tracking the glide slope
    Disengage Autopilot and disable APT (Auto Pitch Trim) (SEE AP OUT OF TRIM LIGHT ON Irregular Procedure.)
  6. Prior to re-engagement of the Autopilot without APT
    The airplane must be manually trimmed and tracking the Glideslope at the target approach speed.
  7. Do not use the Autopilot GO-AROUND
    • with an engine failure.
    • during touch and go landings.
  8. Autoland mode
    Not approved
  9. If destination weather is forecast to be below ¾ mile or RVR 4000 at time of arrival.
    At least one autopilot and Captain’s flight director must be operative
  10. AUTOPILOT ENGAGED - MINIMUM
    ALTITUDES IN CMD
    • After Takeoff 500 feet AGL
    • Non-precision Approaches 50 feet below MDA or DA
    • Coupled Approaches 50 feet below DH (DA)
  11. AUTOTHROTTLES- Do not use
    during touch and go landings
  12. AUTOTHROTTLES May be used for takeoff provided
    The computed (OPS) N1 is less than 1% difference in favor of a more aggressive reduction of thrust than the ALT 1 or ALT 2 positions of the TRC (Thrust Rating Computer). If computed (OPS) N1 is greater than TRC limit, a manual autothrottles OFF using (OPS) computed N1 setting should be used for takeoff.
  13. TAKEOFF WARNING SYSTEM
    The Slat function of the takeoff warning system
    Must be operative for takeoff
  14. GENERATOR LOAD - MAXIMUM
    AC and DC Load
    • 1.0 Max Continuous
    • 1.0 - 1.5 Max of 5 minutes
  15. VOLTS/AMPS/FREQUENCY - INSTRUMENT MARKINGS
    Normal Operating Range
    Cautionary Range
    • Normal Operating Range - Green or White arc
    • Cautionary Range - Yellow Arc (Operations outside this range or sustained operation in this range is not recommended.)
  16. EMERGENCY LIGHTING
    The emergency exit light circuit
    Must be armed for all flight operations.
  17. OXYGEN PRESSURES - MINIMUM (PSI)
    If Maximum flight altitude is 10,000 feet MSL or lower, the minimum fixed system pressure for dispatch is 900 psi.
  18. ENGINES (AFM) engine instrument markings
    Maximum/Minimum
    Caution
    Normal
    • Maximum/Minimum - Red Radial
    • Caution - Yellow Arc
    • Normal - Green or White Arc
  19. EGT AND THRUST - MAXIMUM (AFM)
  20. EGT AND THRUST (KSSU)- MAXIMUM
  21. ENGINES
    Min OIL PRESSURE (PSI)
    10 PSI
  22. ENGINES
    OIL QUANTITY (QUARTS)
    Minimum Before Engine Start and At Least 10 Minute After Engine Shutdown
    12 QUARTS
  23. OIL TEMPERATURE
    Maximum Time Operating in Caution Range
    15 Min
  24. OIL TEMPERATURE
    Engine Must Be Shut Down If Oil Temperature Exceeds
    • 175 C
    • * Caution (yellow) range may be lower on some gauges - temperature in degrees C will be the limiting factor.
  25. REVERSE THRUST
    Takeoff is not permitted if any of the following conditions exist:
    Any engine, REV PRESS, REV U/L or REV THR light(s) illuminated.
  26. REVERSE THRUST
    For takeoff with both wing engine thrust reversers deactivated, the following limitationsapply:
    • Takeoff under contaminated runway conditions is prohibited.
    • For wet runway conditions, increase required runway length by 5%.
    • NOTE: Ops wet takeoff data meets or exceeds AD imposed 5% increase.
  27. REVERSE THRUST
    For landing with both wing engine thrust reversers deactivated, the following limitationsapply:
    For DC-10-30 increase the required runway length by 10% under wet or contaminated runway conditions.
  28. CF6-50 C2/CF6-50C2B
    RPM - MAXIMUM (PERCENT)
    • N1 - 118.5 (Max reverse 95% N1)
    • N2 - 109.5
  29. STARTER DUTY CYCLES
    • 5 minutes 30 seconds cooling (per minute on)
    • Two duty cycles 10 minutes
    • NOTE: If duty cycle is les s than 5 minutes , and 30 second cooling per 1 minute of s tarter use is observed, number of duty cycles is unlimited.
  30. STARTER PRESSURE (PSI)
    Minimum Duct Pressure Before Start
    • > 0°F (-18°C) 30 PSI
    • < 0°F (-18°C) 35 PSI
    • A start attempt may be made as low as 15 psi, closely monitor engine start parameters.
  31. FUEL IMBALANCE - MAXIMUM (POUNDS)
    Between Main Tanks 1 and 3
    4000 LBS
  32. FUEL QTY INDICATOR (POUNDS)
    Any Indicator Less than 5000
    All Associated TANK PUMP Switches ON
  33. LANDING FUEL - MINIMUM (POUNDS)
    Minimum Desired Landing Fuel (Indicated) Total 7500
  34. ANY TRIPPED FUEL PUMP CIRCUIT BREAKERS
    DO NOT RESET
  35. No. 2 Engine Operation
    Minimum Tank Pumps
    One AFT PUMP Tank 2 ON
  36. Any operation requiring the use of ballast fuel
    Must be coordinated through flight operations.
  37. Minimum hydraulic quantity for dispatch
    To the Chevron
  38. Icing conditions exist on the ground and for takeoff when
    • Ground/Takeoff Temperature (OAT/TAT) 42°F (6°C) or below
    • AND
    • Either visible moisture in any form is present (clouds, fog with visibility of one mile or less, rain, wet rwy, snow, sleet, or ice crystals), or OAT and dew point are within 5°F/3°C.
  39. Icing conditions exist in-flight when
    • In-flight (TAT) -- 6°C or below
    • Visible moisture in any form is present (clouds, fog with visibility of one mile or less, rain, snow, sleet, or ice crystals).
  40. When descending in icing conditions, engine power must be sufficient to provide at least_______pneumatic temperature from each operating engine to assure adequate anti-icing.
    170°C
  41. CABIN DIFFERENTIAL PRESSURE
    Takeoff and Landing
    .5
  42. CABIN DIFFERENTIAL PRESSURE
    Relief Valve
    9.1

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