CRJ 200 Limitations

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Author:
lockdown643
ID:
173691
Filename:
CRJ 200 Limitations
Updated:
2012-09-27 02:31:13
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CRJ 200
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CRJ Limitations
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  1. Max Ramp Weight
    53,250 lbs
  2. Max Takeoff Weight
    53,000 lbs
  3. Max Landing Weight
    47,000 lbs
  4. Max Zero Fuel Weight
    44,000 lbs
  5. Minimum Flight Weight
    25,480 lbs
  6. Max Aft Cargo Weight
    3,500 lbs
  7. Flight Time to suitable airport
    45 minutes
  8. Max Ops Altitude
    41,000 feet
  9. Max Takeoff and Landing Distance
    10,000 feet
  10. Max Temperature Takeoff and Landing
    ISA +35 degrees C
  11. Minimum Temperature for Takeoff and Landing
    -40 degrees C
  12. Runway Slope
    +/- 2 degrees
  13. Maximum Tailwind
    10 knots
  14. VMO
    335 knots
  15. MMO
    0.85 Mach
  16. VFE 8,20
    230 knots
  17. VFE 30
    185 knots
  18. VFE 45
    170 knots
  19. Vlo Ext
    220 knots
  20. Vlo Ret
    200 knots
  21. Vle
    220 knots
  22. VTire
    182 knots GS
  23. Vmax ADG Deploy
    250 knots
  24. VB
    280 knots
  25. MB
    .75 knots
  26. VWiper Operations Max
    220 knots
  27. Hydraulics Normal PSI
    2950 - 3050 (Green)
  28. Hydraulics Low PSI
    <1800 (Amber)
  29. Hydraulic High PSI
    >3200 (White)
  30. Hydraulic Pressure Relief
    >3750 (White)
  31. Hydraulic Accumulator PSI
    1500 PSI
  32. Normal Hydraulic Level
    45-85% (Green)
  33. Hydraulic High Temp Caution
    93-96 Degrees C
  34. Brake Normal PSI
    1000-3200 PSI (Green)
  35. Brake Anti-Skid
    > 35 knots WOW +5 sec
  36. Anti-Skid INOP below
    10 knots
  37. Slats/Flaps Max Altitude
    15,000 feet
  38. Slats/Flaps Enroute Operations
    prohibited
  39. Min Spoiler Speed
    Vref + 17
  40. Min Altitude Spoilers
    300 feet.
  41. Flight spoilers must not be deployed in flight with flap settings greater than:
    30 degrees
  42. Engine
    CF 34-3A1/3B1
  43. Max Takeoff Thrust
    8729 lbs
  44. APR Thrust
    9220 lbs
  45. ITT Maximum Continuous Thrus
    • 3A1: 860 degrees
    • 3B1: 874 degrees
  46. ITT Max. Start
    900 degrees
  47. Oil Temp Minimum Start
    -40 Degrees C
  48. Oil Temp Max Continuous
    155 Degrees C (Amber)
  49. Max. (15 min)
    163 Degrees C (Red)
  50. Oil Min. Start/Idle Pressure
    25 PSI (red)
  51. Min Takeoff Thrust Oil Pressure
    25 psi (green)
  52. Max Continuous Oil Pressure
    115 psi (amber)
  53. Max Continuous N1
    98.6% (red)
  54. Normal Takeoff N1
    96.2% (green)
  55. Minimum Reduced Thrust N1
    83.5%
  56. N2 Start
    20% (green)
  57. N2 Idle
    56.5 - 68% (green)
  58. N2 Max Takeoff (APR) op / APR Max. Power
    99.4% (red)
  59. N2 Minimum Reduced Thrust
    83.5%
  60. N2 Normal takeoff
    98.3% (green)
  61. Engine Start (Ground)
    • 60 sec on, 10 sec off
    • 60 sec on, 10 sec off
    • 60 sec on, 5 min off
    • 60 sec on, 5 min off
  62. At Initiation of thrust lever movement from SHUT OFF to IDLE, ITT must be ______ or less for all ground start.
    120 degrees
  63. Dry Motoring (Ground)
    • 90 sec on, 5 min off
    • 30 sec on, 5 min off
  64. Fuel Left Main
    4,760 lbs
  65. Fuel Right Main
    4,760 lbs
  66. Fuel Center Tank
    4,998 lbs
  67. Fuel Total
    14,518 lbs
  68. Fuel Max. Imbalance
    800 lbs
  69. Fuel Min. for GA per wing tank
    450 lbs (amber)
  70. Fuel Min. Temp for Takeoff
    +5 degrees C
  71. Electric Main Gen:
    • to 35,000 ft: 30 KVA
    • Above 35,000 ft: 25 KVA
  72. APU Gen
    to 37000 ft: 30 KVA
  73. Ground Ops DC Only time in use
    5 minutes
  74. Automatic Flight Control System (AFCS) IAS Mode
    Prohibited during approach
  75. Automatic Flight Control System (AFCS) APPR Mode
    Prohibited for VOR approaches
  76. Automatic Flight Control System (AFCS) ADC Source
    ADC source coupled to the active autopilot must be the same as taht coupled to the ATC transponder during flight in RVSM airspace
  77. Nose Steering Tiller max angle
    70 Degrees Left/Right
  78. Nose Steering Rudder max angle
    5 Degrees
  79. APU Max RPM
    107% (Red)
  80. APU Max Continuous EGT
    743 Degrees C (Red)
  81. APU Max EGT Start
    974 Degrees C
  82. APU Min Temp Start
    -40 Degrees C
  83. APU Max Ops Altitude
    37,000 feet
  84. APU Max Start Altitude
    30,000 feet
  85. APU Max Altitude Bleed Use
    15,000 feet
  86. APU Max Alt Engine Start
    13,000 feet
  87. APU Max Generator Load
    30 KVA
  88. APU Max Door Open with APU not operating airspeed
    300 knots
  89. APU Start (Aircraft Battery) 2x30 sec On
    • 20 min off
    • 20 min off
    • 40 min off
    • 40 min off
  90. APU Start (Generator) 2x15 sec ON
    • 20 min. off
    • 20 min. off
    • 40 min. off
    • 40 min. off
  91. AC and Pressurization Max Diff.
    8.7 PSI
  92. AC and Pressurization Max Negative Differential
    -0.5 PSI
  93. AC and Pressurization Taxi, Takeoff, and Landing Max.
    0.1 PSI
  94. AC and Pressurization No Manual Operations to:
    1,500 feet
  95. AC and Pressurization Single Pack Operations
    25,000 feet
  96. AC and Pressurization Pack Overheat
    88 Degrees C
  97. AC and Pressurization Pack Overpressure
    >53 PSI
  98. AC and Pressurization Cabin Altitude Caution 
    >8,500 feet > 10,000 feet
  99. AC and Pressurization Cabin Altitude Warning
    >10,000 feet
  100. AC and Pressurization CPAM Pax O2
    14,000 +/- 500 feet
  101. AC and Pressurization CPAM NoSmFaSB
    10,000 feet
  102. AC and Pressurization Em Depr
    14,250 feet +/- 750 feet
  103. Engine N2 at ground idle power should not be greater than ___ split.
    2%
  104. If N2 is ___ or less with an OAT of ____ or warmer, do not:
    57%, -20 degrees C, do not accelerate above idle.
  105. Engine Warm Up:
    Engine must remainat idle until oil pressure reaches normal operating range
  106. After all engine starts:
    do not exceed 75% N1 for 2 mins. or until operating indications are in normal range.
  107. Before FFOD, when the aircraft is cold soaked at a temp of -30 degrees C or below for more than 8 hours:
    the engine must be motored for 60 seconds and fan rotation verified before engine start is initiated.
  108. During preflight checks of the thrust reversers after being cold soaked for more than 8 hours:
     the thrust reversers must be actuated until the deploy and stow cycles are less than 5 seconds.
  109. Continuous Ignition must be used during the following:
    • Takeoffs and landings on contaminated runways
    • Takeoffs with high crosswind components > 10 knots
    • Flight through moderate or heavier intensity rain.
    • Flight through moderate or heavier intensity turbulence
    • Flight in the vicinity of thunderstorms.
  110. Thrust Reversers are approved for
    ground use only
  111. After the deployment of thrust reversers
    do not attempt a go-around maneuver
  112. During landing, application of maximum reverse thrust is not permitted at airspeeds below:
    75 knots.
  113. Below ____ knots reverse thrust must be to idle (not abouve 30%N1)
    60 KIAS
  114. If both engines are to be started using the APU bleed air, then the operating engines thrust must not exceed:
    70% N2
  115. EICAS display cooling is not available when:
    • the battery bus is powered and normal AC power is off
    • or
    • when the battery bus is powered and APU is in proper service configuration
  116. Between each APU start:
    The APU, PWR FUEL switch/light must be selected off.  
  117. APU at or below 50% rpm max time:
    60 seconds
  118. Takeoff with a fiel load in excess of _____ lbs in the center tank is not permitted unless each main tank is above ______ lbs.
    500 lbs, 4,400 lbs
  119. Takeoff with engine fuel temp indications below ___ degrees C is prohibited.
    5 Degrees C
  120. Powered crossflow and gravity cross flow must be _____ for takeoff.
    Off
  121. Minimum climb speed above 10,000 MSL:
    250 knots to .70 M.
  122. Maximum climb speed above 10,000 MSL:
    290 knots to .70 M.
  123. ___ Mach will be the minimum climb speed once the transition to Mach is made from IAS to Mach.
    .70
  124. maximum Authorized Altitude
    FL 370
  125. Reduced thrust takeoffs are prohibited when:
    • Cowl and/or wing anti-ice is selected ON
    • The takeoff runway is contaminated with standing water, slush, ice or snow.
    • tailwind components are in excess of 5 knots
    • Warning of windshear or downdrafts have been forecast or reported.
    • anti-skid is inop.
    • takeoff behind a heavy aircraft
    • flaps 8 takeoff
  126. Takeoff is _______ with frost, ice, snow or slush adhering to any critical surface.
    prohibited
  127. Cowl anti-ice system must be ON when:
    • OAT is below 10 degrees C and visible moisture in any form is present
    • or
    • when it is below 10 degrees C when operating on ramps, taxiways or runways where snow, ice, standing water or slush is present.
  128. The wing anti-ice system must be on for takeoff when:
    • visible moisture is presented below 400 feet agl, or
    • runway is wet or contaminated, or
    • any precipitation exist.
  129. Anytime the wing anti-ice is selected ON, the cowl anti-ice:
    must also be selected ON.
  130. The engine cowl anti-ice system must be ON:
    • When in icing conditions, or
    • when ICE is annunciated by the ice detection system.
  131. 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 knots

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