1. Runway slope
    +/- 2%
  2. Maximum Takeoff and Landing TailwindComponent
    15 knots
  3. Maximum Operating Altitude
    43,100 pressure altitude
  4. Maximum Takeoff and Landing Altitude
    8,400 feet pressure altitude
  5. Turbulent air (greater than moderate turbulence as defined by theAeronautical Information Manual) penetration speed is
    290 KIAS / .78Mach, whichever is lower.
  6. The navigation display system does not support operations at latitudes greater than?
    87 deg North or South
  7. Standby altimeters do not meet altimeter accuracy requirements of
    RVSM airspace.
  8. The maximum allowable in-flight difference between Captain and First Officer altitude displays for RVSM operations is
    200 feet
  9. The maximum allowable on-the-ground altitude display differences forRVSM operations are:
    Sea Level
    • Sea Level 40ft 75ft
    • 5000' 45ft 75ft
    • 10000' 50ft 75ft
  10. Do not operate the weather radar in a hangar or within
    50 feet of anypersonnel or a fuel spill.

    NOTE:The hangar and personnel restrictions do not apply to the weather radar test mode
  11. Maneuver Limits (AFM)
    Flaps UP -
    Flaps Down -
    • -1.0g to +2.5g
    • 0.0g to +2.0g
  12. Door Mounted Escape Slides
    Entry door evacuation slide systems must be armed and engagement of the girt bar with door sill verified prior to?
    taxi, takeoff, or landing whenever passengers are carried
  13. Maximum Taxi Weight
    322,000 lbs
  14. Maximum Takeoff Weight
    320,000 lbs
  15. Maximum Landing Weight
    272,000 lbs
  16. Maximum Zero Fuel
    250,000 lbs
  17. Minimum Inflight Weight
    168,000 lbs
  18. The maximum cabin differential pressure is
    9.10 psi.
  19. The maximum allowable cabin pressure differential for takeoff and landing is
    .125 psi
  20. Icing conditions exist when the OAT on the ground and for takeoff, and in flight is?
    10°C (41°F) or below, and visible moisture in any form is present (such as clouds, fog with visibility of 1 NM or less, rain, snow, sleet, and ice crystals).
  21. The Engine Thermal Anti-Ice system must be on during all ground and flight operations when icing conditions exist or are anticipated, except during climb and cruise when the temperature is
    below –40°C SAT. Engine anti-ice must be on prior to and during descent in icing conditions, including temperatures below –40°C SAT.
  22. When penetrating or operating in icing conditions in flight, maintain a minimum of __% of N1 RPM at _____ feet and above, and __%N1 RPM below ____ feet except as required for landing.
    45% above 10,000', 40% below 10,000'
  23. After takeoff, the autopilot must not be engaged below
    200 feet AGL.
  24. Use of aileron trim with the autopilot engaged
    is prohibited
  25. Autopilot max winds for
    • Headwind: 25kts
    • Crosswind: 25kts
    • Tailwind: 15kts
  26. No Passengers Onboard
    The following table lists the allowable flight duration corresponding to a minimum charge time. During charging cabin activity is limited to normal aisle traffic of crew and personnel.

    UP to 3 hours:
    >3 hours and < 3.5 hours:
    >3.5 hours and < 6.75 hours:
    • UP to 3 hours: 5 min
    • >3 hours and < 3.5 hours: 10 min
    • >3.5 hours and < 6.75 hours: 15 min
  27. Passengers Onboard and Seated

    Up to 4 hours:
    > 4 hours and <6 hours:
    • Up to 4 hours: 10 min
    • > 4 hours and <6 hours : 25 min
  28. Maximum N1 RPM
  29. Maximum N2 RPM
  30. Maximum Takeoff EGT
    625° C 5 Minutes
  31. Maximum Continuous EGT
    600° C Continuous
  32. Maximum Starting, Flight EGT
    625° C
  33. Maximum Starting, Ground EGT
    535° C
  34. Acceleration
    625° C 2 Minutes
  35. Engine Ignition is __ for takeoff and landing
  36. Continuous ignition must be on (engine start selector in the CONT position) while operating in ?
    Severe Turbulnce
  37. Continuous ignition is automatically provided in icing conditions when ________is on.
    engine anti-ice
  38. Minimum oil pressure is
    35 psi
  39. Maximum oil temperature is
    163 C
  40. Operation between ___C and ___C is limited to __ minutes
    Operation between 135°C and 163°C is limited to 20 minutes
  41. Flight crew shall not blank ________display during takeoff
    engine vibration
  42. Reverse thrust is for ________only.
    Reverse thrust is for ground use only.
  43. Backing the aircraft with use of reverse thrust is
  44. The minimum inflight fuel tank temperature is ___ above the freeze point of the fuel being used.
    3 C
  45. The maximum fuel temperature is ? {Jet B/ JP-4: ?}
    49 C / 43 C
  46. The center tank may contain up to _____ pounds of fuel with less than full main tanks provided center tank fuel weight plus actual zero fuel weight does not exceed the maximum zero fuel weight, and center of gravity limits are observed
    22,500 lbs
  47. The use of ___ or ___ is prohibited in center fuel tank.
    The use of JP-4 or Jet B is prohibited in center fuel tank.
  48. The maximum altitude for flap extension is
    20,000 ft
  49. With a single operational FMC, during VOR approaches, one pilot must have raw data from the VOR associated with the approach displayed on the RDMI, RMI or HSI in the VOR mode, no later than the _____.
  50. Do not operate under IFR or at night into airports north of __° North or south of __° South Latitude whose navigation aids are referenced to magnetic north.
    • 73 North
    • 60 South
  51. Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply within _____ warnings
  52. Do not use the look-ahead terrain alerting and terrain display functions:
    • within ___nm of takeoff, approach or landing at an airport not contained in the GPWS terrain database. The look-ahead terrain alerting and terrain display functions must be inhibited by selecting the TERR INHIBIT switch to INHIBIT
    15 nm
  53. Do not _____ a tripped fuel pump or fuel pump circuit breaker
  54. The maximum allowable fuel imbalance between the left and right main tanks for all operations is ____ pounds (1134 kilograms) when total main tank fuel is 48,000 pounds (21,772 kilograms) or less, with a linear
    reduction to ____ pounds (680 kilograms) when total main tank fuel is 79,800 pounds (36,197 kilograms), and is 1,500 pounds (680 kilograms) when total main tank fuel exceeds 79,800 pounds (36,197 kilograms).
    • 2,500 lbs
    • 1,500 lbs
  55. Use _______fuel feed for takeoff and landing with all operable main tank boost pumps on and the crossfeed valve(s) closed
  56. Intentional dry running of a center tank fuel pump (CTR L FUEL PUMP or CTR R FUEL PUMP message displayed on EICAS) is?
Card Set
Ops Limits