Limitations CRJ-1000

Home > Preview

The flashcards below were created by user FlyQuick on FreezingBlue Flashcards.


  1. Maximum Ramp Weight (MRW)
    • 41867 Kg
    •  92300 lbs
  2. Maximum Take-Off Weight (MTOW)
    • 41640 Kg
    • 91800 Lbs
  3. Maximum Landing Weight (MLW)
    • 36968 Kg
    • 81500 Lbs
  4. Maximum Zero Fuel Weight (MZFW)
    • 35153 Kg
    • 77500 Lbs
  5. Maximum airport pressure altitude for take-off and landing is:
    10000 feet.
  6. Maximum operating altitude is:
    41000 feet.
  7. Maximum ambient air temperature approved for take-off and landing is:
    ISA + 35°C.
  8. Minimum ambient temperature approved for take-off is:
    −40°C (−40°F).
  9. Cowl Anti-ice System:
    (1) Ground Operations
    The cowl anti-ice system must be ON when the OAT is __________ or below and visible
    moisture in any form is present (such as fog with visibility of 1500 metres [one mile] or
    less, rain, snow, sleet and ice crystals).
    The cowl anti-ice system must also be ON when the OAT is __________ or below when
    operating on runways, ramps, or taxiways where surface snow, ice, standing water, or
    slush is present.
    • The cowl anti-ice system must be ON when the OAT is 10°C (50°F) or below and visible
    • moisture in any form is present (such as fog with visibility of 1500 metres [one mile] or
    • less, rain, snow, sleet and ice crystals).
    • The cowl anti-ice system must also be ON when the OAT is 10°C (50°F) or below when
    • operating on runways, ramps, or taxiways where surface snow, ice, standing water, or
    • slush is present.
    • (2) Flight Operations
  10. Wing Anti-ice System
    (1) Ground Operations
    The wing anti-ice system must be ON for take-off when the OAT is _________ or below
    and visible moisture in any form is present (such as fog with visibility of 1500 metres
    [one mile] or less, rain, snow, sleet and ice crystals).
    The wing anti-ice system must also be ON for take-off when the OAT is_________ or
    below and the runway is contaminated with surface snow, slush or standing water.
    When Type II, III or Type IV anti-icing fluids have been applied, the wing anti-ice system
    must only be selected ON, if required, just prior to thrust increase for take-off.
    • Wing Anti-ice System
    • (1) Ground Operations
    • The wing anti-ice system must be ON for take-off when the OAT is 5°C (41°F) or below
    • and visible moisture in any form is present (such as fog with visibility of 1500 metres
    • [one mile] or less, rain, snow, sleet and ice crystals).
    • The wing anti-ice system must also be ON for take-off when the OAT is 5°C (41°F) or
    • below and the runway is contaminated with surface snow, slush or standing water.
    • When Type II, III or Type IV anti-icing fluids have been applied, the wing anti-ice system
    • must only be selected ON, if required, just prior to thrust increase for take-off.
  11. Define Icing Conditions:
    • Icing conditions exist in flight at a TAT of 10°C (50°F) or below, and
    • visible moisture in any form is encountered (such as clouds, rain, snow,
    • sleet or ice crystals), except when the SAT is −40°C (−40°F) or below.
  12. The wing anti-ice system must be ON:
    • When ICE is annunciated by the ice detection system, or
    •  When in icing conditions and the airspeed is less than 230 KIAS.

    >>Do not hold in icing conditions with the flaps/slats extended.<<
  13. The cowl anti-ice system must be ON:
    • When in icing conditions, or
    • When ICE is annunciated by the ice detection system.
  14. The maximum runway slopes approved for take-off and landing are:
    • +2% (uphill)
    • −2% (downhill)
  15. The maximum tailwind component approved for take-off and landing is _______.
    The maximum tailwind component approved for take-off and landing is 10 knots.
  16. Flight must be within ___minutes of a suitable airport if cargo is carried in either cargo
    compartment.
    • Flight must be within 60 minutes of a suitable airport if cargo is carried in either cargo
    • compartment.
  17. LEAST RISK BOMB LOCATION (LRBL) on the CRJ-1000?
    The LRBL location is the right (forward) galley service door.
  18. With the engines running and bleeds configured for take-off, the crew must verify that the
    target N1 values correspond to the data presented in the thrust setting charts (______). Refer
    to PERFORMANCE – Thrust Settings. With the thrust levers set for take-off, target and actual
    N1 values should match.
    • With the engines running and bleeds configured for take-off, the crew must verify that the
    • target N1 values correspond to the data presented in the thrust setting charts (±1.0%). Refer
    • to PERFORMANCE – Thrust Settings. With the thrust levers set for take-off, target and actual
    • N1 values should match.
  19. Engine Warm-up requirement.?
    • The engine must remain at IDLE until oil pressure reaches normal operating range.
    • During all starts, do not exceed 75% N1 for two minutes after start or until all operating
    • indications are in the normal range, whichever is longer.
  20. Minimum Oil Level for Flight?
    40% minimum with affected engine not started. (Below 15% in flight do not re-start)
  21. Airplane Cold Soak
    Before the first flight of a day, when the airplane is cold-soaked at an ambient temperature of
    −30°C (−22°F) or below for more than 8 hours:
    • The engines must be motored for 60 seconds and the fan rotation must be verified beforean engine start is initiated.
    •  The thrust reversers must be actuated until the deploy and stow cycles are 2 seconds orless.
  22. Continuous engine ignition must be used during the following:
    • • Take-offs and landings on contaminated runways,
    • • Flight through moderate or heavier intensity rain,
    • • Flight through moderate or heavier intensity turbulence,
    • • Flight in the vicinity of thunderstorms.
  23. STARTER CRANKING LIMITS
    * Engine Start (Ground)
    Image Upload
  24. Engine Start or Motoring (Flight)
    Image Upload
  25. Motoring (Ground)
    Image Upload
  26. Engine re-light envelope:
    Image Upload
  27. The maximum permissible fuel imbalance between the contents of the main left tank and the main right tank is as follows:
    • • During take-off – 136 kg (300 lb)
    • • All other phases of flight – 363 kg (800 lb)
    • >>Fuel remaining in a tank when the appropriate fuel quantity indicator reads zero is not usable.<<
  28. Total Fuel Load?
    • Pressure refueling: 8994 kg (19828 lb)
    • Gravity refueling:   6614 kg (14582 lb)
  29. Max Fuel load in Main tanks:
    • Left main tank 3410 kg (7517 lb) 3307 kg (7291 lb)
    • Right main tank 3410 kg (7517 lb) 3307 kg (7291 lb)
  30. Max Fuel load in Centre tank:
    Centre tank 2175 kg (4795 lb)

    >>Only available with pressure refueling<<
  31. Take-off with a fuel load in excess of 227 kg (500 lb) in the centre tank is not permitted
    unless:
    • • Each main wing tank is above 1996 kg (4400 lb); or
    • • Each main wing tank is above 907 kg (2000 lb): and
    • • The allowable zero-fuel weight is reduced by the weight of the fuel in the centre tank in excess of 227 kg (500 lb); and
    • • The Centre of Gravity (CG) in this configuration is verified to be within the allowable CG
    • envelope as calculated from the Weight and Balance Manual (WBM) (CSP D-041).
  32. The minimum fuel quantity for go-around is ____ kg (___ lb) per wing (with the airplane level)
    and assuming a maximum airplane climb attitude of 10 degrees nose up.
    The minimum fuel quantity for go-around is 272 kg (600 lb) per wing (with the airplane level) and assuming a maximum airplane climb attitude of 10 degrees nose up.
  33. Take-off with engine fuel temperature indications below _°C (__°F) is prohibited.
    Take-off with engine fuel temperature indications below 5°C (41°F) is prohibited.
  34. Engine oil levels must be checked as follows:
    • • The maximum duration without engine oil servicing is 36 operating hours.
    • • For airplane operations in excess of 36 operating hours (without engine oil tank servicing),the engine oil level must be checked within 3 minutes to 2 hours after every engine shutdown.
  35. If use of the oil replenishment system is required, then the engine(s) should be replenished
    __ minutes to _ hours after engine shutdown.
    • If use of the oil replenishment system is required, then the engine(s) should be replenished
    • 15 minutes to 2 hours after engine shutdown.
  36. AUXILIARY POWER UNIT (APU)
    Allied Signal RE 220 (RJ)
  37. Maximum RPM APU?
    106%
  38. The APU starter motor duty cycle is as follows:
    • Do not perform more than three starts/start attempts in one hour.

    • >>A two-minute delay must be observed between cranking attempts to allow
    • for cooling of starter and starter contractor and for APU drainage.<<
  39. APU Operating envelope:
    Image Upload
  40. MAX Load APU Generator:
    The maximum permissible load on the APU generator is 40 kVA.
  41. Explain Thrust limitations due to wind & direction:
    Image Upload
    Image Upload
  42. MAXIMUM OPERATING MACH NUMBER operating in RVSM Airspace?
    Mach 0.82
  43. The maximum speeds at which the flaps may be extended are:
    • • FLAPS 1: 230 KIAS
    • • FLAPS 8: 230 KIAS
    • • FLAPS 20: 220 KIAS
    • • FLAPS 30: 185 KIAS
    • • FLAPS 45: 170 KIAS
  44. MAXIMUM LANDING GEAR OPERATING SPEED
    • The maximum airspeed at which it is safe to extend the landing gear is 220 KIAS.
    • The maximum airspeed at which it is safe to retract the landing gear is 200 KIAS.
  45. TIRE LIMIT SPEED
    The tire limit speed is 195 knots ground speed.
  46. MAXIMUM AIRSPEED FOR ADG OPERATION
    The maximum speed for ADG operation is VMO/MMO.
  47. TURBULENCE PENETRATION SPEED
    Maximum airspeed for turbulence penetration is 280 KIAS or 0.75 Mach, whichever is lower.
  48. MINIMUM OPERATING LIMIT SPEED
    Intentional speed reduction below the onset of stall warning, as defined by stick shaker operation, is prohibited unless a lower speed is specifically authorized for flight test or training operations.
  49. WINDSHIELD WIPER OPERATION
    • The windshield wiper must not be operated above 250 KIAS.
    • If the windshield wiper has failed in a non-parked position, the airplane speed must not exceed 250 KIAS.
  50. MANEUVERING LIMIT LOAD FACTORS
    • These load factors limit the permissible angles of bank in turns and the severity of pull-up and
    • push-over maneuvers:
    • • Flaps up: −1.0 g to 2.5 g
    • • Flaps down: 0.0 g to 2.0 g
  51. The maximum positive differential pressure is ____ psi.
    The maximum positive differential pressure is 8.7 psi.
  52. The maximum negative differential pressure is _____ psi.
    The maximum negative differential pressure is −0.5 psi.
  53. During ground maneuvering, the pressure differential must not exceed ___ psi.
    During ground maneuvering, the pressure differential must not exceed 0.1 psi.
  54. Minimum altitude for use of Autopilot?
    600 Feet AGL
  55. Minimum altitude for use of Autopilot during non-precision approach?
    400 Feet AGL
  56. Minimum altitude for use of Autopilot for precision approach?
    ≤3.5 degrees 75 Feet AGL (115 Feet AGL if SE)
  57. Minimum altitude for use of Autopilot for precision approach >4.0 degrees?
    PROHIBITED.
  58. Permissible Loads on AC System:
    Image Upload
  59. Permissible Loads on DC Systems
     Ground Operation:
    To protect the flight compartment CRT displays, the maximum permissible time for ground operations with DC power only is 5 minutes.
  60. Permissible Loads on DC Systems
    Flight Operations:
    The maximum permissible continuous load on each TRU is 120 amp.
  61. Circuit Breaker Reset (In Flight)
    A circuit breaker must not be reset or cycled (i.e., opened or closed) unless doing so is consistent with explicit procedures specified in the AFM or unless, in the judgement of the Pilot−In−Command (PIC), that resetting or cycling of the circuit breaker is necessary for these completion of the flight.
  62. Limitations on use of Slats/Flaps:
    • En-route use of slats/flaps is prohibited.
    • Flight with slats/flaps extended at altitudes above 15000 feet is prohibited.
  63. Limitations on use of Flight Spoilers:
    • Flight spoilers must not be extended in flight below an altitude of 300 feet AGL.
    • To ensure adequate maneuver margins, flight spoilers must not be extended in flight at airspeeds below the recommended approach speed (VREF) plus 10 KIAS.
  64. Limitations on use of THRUST REVERSERS:
    • Thrust reversers are approved for ground use only, activation of the reverse thrust levers is prohibited in flight.
    • The thrust reversers are intended for use during full stop landings. Do not attempt a go-around maneuver after deployment of the thrust reversers.
    • Take-off with any thrust reverser icons or EICAS warning and/or caution messages displayed is prohibited.
    • During landing, maximum reverse thrust is prohibited below 75 KIAS, and reverse idle should be achieved by 60 KIAS.
    • During pre-flight check of the thrust reversers with the airplane stationary, reverse thrust must be limited to reverse idle.
    • Backing-up using thrust reversers is prohibited.
  65. Limitations on use of Taxi Lights:
    The taxi lights must be switched OFF whenever the airplane is stationary in excess of 10 minutes.

Card Set Information

Author:
FlyQuick
ID:
322402
Filename:
Limitations CRJ-1000
Updated:
2016-08-15 04:27:44
Tags:
Bombardier CL 65 Jet CRJ 1000
Folders:
CRJ-1000
Description:
Limitations for the CRJ-1000
Show Answers:

Home > Flashcards > Print Preview