Limitations.txt

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jnas2020
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58039
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Limitations.txt
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2011-01-15 19:17:46
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  1. Engine oil temperature
    0-107 deg Celsius cont. operation

    107 deg Max
  2. engine oil pressure
    Y-50 psi minimum below 78% N1 (engine speed)

    G-90 psi minimum from 78%-94% N1

    G-115 psi min aboove 94% N1 (dbl wide arc)

    R-50 psi min, 130 psi max
  3. transmission oil press
    G- 30 to 50 psi cont. operation

    R- 30 psi min, 70 psi max
  4. transmission oil temp
    G- 15 deg C to 110 deg C cont. operation

    R- 110 deg C max
  5. Fuel press
    R- 4 psi min

    G- 4 to 30 psi cont op

    R- 30 psi max

    R- 8 psi min-type A, A-1, JP-5, JP-8 fuel below -18 deg C (0 deg F) to -32 deg C (-25 deg F)
  6. load meter
    R- 70% max
  7. Airspeed
    G- 0 to 130 knots cont op

    R- 130 knots max

    B- 100 knots max for autorotation
  8. Airspeed Indicator Note:
    Autorotation above 100 KIAS will result in high rates of descent and low rotor RPM
  9. VNE for internal Gross Weight above 3,200lbs=
    78 KIAS, not to exceed placarded VNE
  10. TOT (exhaust temp)
    Turbine outlet Temp

    G- 100 to 738 deg C cont op

    Y- 738 to 810 deg C Take-off Power Range (5 min limit)

    R- 810 deg C max (810-843 deg C, 6 sec transient, not to be used intentionally)

    R- 927 deg C max during starting and shutdown (10 sec max)
  11. TOT Note: The red warning light illuminates when either of the following conditions are exceeded:
    810-927 deg C for 10 sec, or higher than 927 deg C
  12. TOT limits: Caution
    Exceeding the limits of 810 deg C TOT or 100% torque may cause N1 topping with resultant rotor droop
  13. Gas Producer (N1)
    G- 60 to 105% cont op

    R- 105% max

    * 105 to 106% transient (15 sec max)
  14. Rotor
    R- 90% min op

    Y- 50-60% accelerate through this range

    G- 90-107% norm op

    R- 107% max

    *power on transient rotor droop limit=95% (5 sec max)
  15. Power Turbine (N2)
    R- 97% min op

    G 97-100% cont op

    R- 100% max

    *N2 75%-88%, 60 sec max (time not cumulative)
  16. WARNING: ENGINE RPM LIMITATIONS
    Use of throttle to control rpm is not authorized. (Refer to ch 9, EP's and USAAWC Flight Training Guide for exceptions)
  17. N2 Transient overspeed
    N2 transient overspeed limit is 15 sec max, shaded area represents allowable overspeed. (look at chart)

    *Increase RPM=Decrease torque
  18. Torque
    G- 0 to 85% cont op

    Y- 85 to 100% take-off power range (5 min limit)

    R- 100% max
  19. Transient torque limit is:
    100 to 110% (5 sec max)

    *Intentional use is prohibited
  20. PLACARD: 2 PILOT IMC VNE MAX
    110 knots
  21. PLACARD: VNE FOR GW OVER 3,200LBS
    78 KIAS, not to exceed placarded VNE
  22. PLACARD: MIN PILOT WEIGHT
    This helicopter must be operated in compliance with the operating limitations specified in the approved helicopter flight manual.....min pilot wt=170lbs
  23. PLACARD: MAX ALLOWABLE WT IN BAGGAGE COMP.
    250lbs

    *Cargo must be secured in accordance with the flight manual instruction
  24. PLACARD: MAX ALLOWABLE WT PER SQ FT
    86lbs
  25. PLACARD: MAX ALLOWABLE WT IN BAGGAGE COMP WITH AIR CONDITIONER
    176.5lbs
  26. PLACARD: NICKEL CADMIUM BATTERY REPLACEMENT
    The nickel cadmium battery has been replaced with a sealed lead acid battery. Battery temp monitoring system has been deactivated
  27. Altitude limitations: 3,000lbs GW and below
    • Max op-
    • *VFR 20,000ft press. altitude
    • *IFR 14,000ft press. altitude
  28. Altitude limitations: Above 3,000lbs GW
    • Max op-
    • *VFR 13,500ft press altitude
    • *IFR 8,000ft press altitude
  29. Wind limitations: starting
    The helicopter can be started in a max wind velocity of 45 knots and max gust spread of 15 knots
  30. Gust spread note:
    *Gust spreads are not normally reported. To obtain spread, compare min and max velocities
  31. Wind limitations: Hovering with a crosswind
    35 knots max
  32. Wind limitations: hovering with a tailwind
    30 knots max
  33. Hover operations at GW over 3,200lbs
    IGE maneuvers-refer to ch 8

    OGE maneuvers-calm wind only
  34. Standby Generator limits (IFR configured aircraft)
    Prolonged op of standby generator while it is the primary power supply to essential #1 bus is prohibited at airspeeds less than 50 KIAS (Vmini) to assist with generator cooling
  35. IFR Standbye generator Limit: Note
    With main gen. on, standby gen loadmeter should indicate 10% or less, momentary testing of standby gen under full bus load is permitted on ground or in air
  36. Engine anti-ice shall not be used in ambient temps above
    4 deg C
  37. Engine anti-icing shall be ON for flight in visible moisture in temps of
    4 deg C or below
  38. Low inlet pressure: CAUTION
    Takeoff with LOW INLET PRESSURE caution light illuminated is PROHIBITED
  39. Engine STARTER limits:

    *If there is no rise in TOT within the first 20sec of energizing starter, limit starter engergizing time to.....
    • External Power Battery
    • 25 sec on 40 sec on
    • 30 sec off 60 sec off
    • 25 sec on 40 sec on
    • 30 sec off 60 sec off
    • 25 sec on 40 sec on
    • 30 min off 30 min off
  40. Engine STARTER limits:

    *If there is a rise in TOT within the first 20 sec of energizing starter, limit starter energizing time to......
    • External/Battery Power
    • 1 min on
    • 1 min off
    • 1 min on
    • 1 min off
    • 1 min on
    • 30 min off
  41. Engine Starting limits
    * If N1 doesn't reach 58% in a total time of 45 sec (or 60 sec below 10 deg C FAT), close throttle and press starter button until TOT is below 200 deg C.

    * If engine fails to start on third attempt, abort start and make an entry on DA form 2408-13-1.

    * Starter engage time limits above do not apply to engine starting limitations should abort start procedures become necessary.
  42. Fuel Limitations: Types of fuel used
    Turbine fuel ASTM D-1655, (Type B) or MIL-T-5624 (JP-4) may be used at all ambient temps with no restrictions
  43. Fuel limits: minimum fuel press
    * 8 psi at temps of -18C to -32C (0 to -25 deg F)

    * 4 psi at temps above -18C (0F)
  44. Fuel Limitations: deceleration check
    * Must be performed if prior to the first flight of each day if fuels other than Type B or JP-4 are used

    * Must be performed if Power Off maneuvers are to be performed
  45. Fuel Limitations: using AVGAS
    Helicopters equipped with airframe mounted fuel filter do not require the use of anti-icing additive at any ambient temps.

    Refer to Allison 250-C20 series OP and Maint Manual for AVGAS Mix, Cold weather fuel, and blending instructions

    *The use of AVGAS in TH-67 is prohibited
  46. Fuel limitations: NOTE-Engine starting difficulties may be encountered if.....
    Any fuels other than Jet B or JP-4 are used at ambient temps below 5C
  47. Hit Check Differences (health indicator test)
    -Method by which the aviator in day-to-day flying monitors the aircraft engine condition

    -TOT is compared to a predicted value within a certain tolerance and differences are logged

    -differences -/+20C or greater between the recorded TOT and baseline TOT=2408-13-1

    -differences -/+ 40C grounded aircraft
  48. Longitudinal CG limits: VMC Center of gravity limits
    106.0-114.2

    CH 6
  49. Longitudinal CG limits: IMC Longitudinal Center of gravity limits
    106-110 at GW of 2,400-3,200lbs

    106.9 at GW above 3,200lbs

    CH 6
  50. Longitudinal CG limits: Doors off
    No change from basic helicopter CG with only aft cabin doors off

    With one or both forward doors off, long. CG limits are same as with doors on

    Actual wt. change is determined after doors, etc., have been removed and ballast readjusted, if nec., to return basic wt. CG to within allowable limits
  51. Longitudinal CG limits: NOTE
    Station 0 (datum) is located 55.6 in forward of forward jack point centerline
  52. Lateral CG limits
    3 in left of helicopter centerline

    4 in right of helicopter centerline
  53. Lateral CG limits:NOTE
    Lat. CG limits vary depending on long. CG location
  54. Weight Limitations:

    max allowable ramp weight
    3,350lbs
  55. Weight limitations: max allowable GW for hover/flight
    3,350lbs
  56. Weight limitations: min front seat wt
    170lbs

    ****Use ballast as required to maintain basic wt CG within limits
  57. VMC Airspeed Limitations: NOTE
    All airspeed values are Indicated Airspeed (IAS), except when Calibrated Airspeed (CAS) is specifically stated
  58. VMC Airspeed Limitations: At 3,000lbs GW and below.....
    VMC Vne 130 KIAS sea level to 3,000 ft density alt.

    Decrease Vne 3.5 KIAS per 1,000 ft above 3,000 ft. density alt

    Max dens. alt= 20,000 ft
  59. VMC Airspeed limitations: Above 3,000lbs GW......
    VMC Vne 122 knots sea level to 3,000 ft density alt.

    Decrease Vne 7.0 KIAS per 1,000 ft above 3,000 ft density alt

    Max density alt=13,500 ft
  60. Vne for internal GW above 3,200lbs=
    78 KIAS, not to exceed placarded Vne
  61. IMC Airspeed limitations:

    Minimum Climb (Vyi)
    70KIAS
  62. IMC Airspeed limitations:

    Minimum speed (Vmini)
    50 KIAS
  63. IMC Airspeed limitations:

    Maximum speed (Vnei)
    110 KIAS, or placarded Vne, whichever is less
  64. IMC Airspeed limitations:

    Maximum speed above 3,200lbs
    78 KIAS, or placarded Vnei, whichever is less
  65. Flight Restrictions For High Power
    Vne 80 knots with > 85% to 100% torque applied
  66. Cockpit and cabin door restrictions:

    *****WARNING*****
    AIRSPEEDS IN EXCESS OF AIRSPEED LIMITATIONS DOOR(S) OFF WILL CAUSE CYCLIC FORE AND AFT STICK REVERSAL AND FUSELAGE BUFFERING
  67. Cockpit and cabin door restrictions: aft doors off
    Vne 87 KIAS or placarded airspeed, whichever is less, power ON or OFF
  68. Cockpit and cabin door restrictions: forward doors off Vne 110 KIAS, or placarded, whichever is less...power is....
    ON
  69. Cockpit and cabin door restrictions: forward doors off Vne 100 KIAS, or placarded, whichever is less...power is...
    OFF

    **with one or both forward doors off, both rear sliding windows must be closed above 70 KIAS
  70. Cockpit and Cabin Door restrictions: NOTE
    with both forward doors removed, the aircraft is approved for day and night VFR ops only. IFR is prohibited
  71. Aerobatic Maneuvers
    Prohibited-Any intentional maneuver involving an abrupt change in aircraft attitude, an abnormal attitude, pitch angle greater than 30 deg or roll angles greater than 60 deg, or abnormal acceleration not necessary for normal flight
  72. Flight restrictions at low "G"
    flight at less than +0.5g is prohibited
  73. Control Movement Limitations

    ------Caution------
    For GW geater than 3,000lbs and density alt. greater than sea level, the directional control margin may be significantly reduced while hovering in winds from the right greater than 20 knots or for right sideward flight at speeds greater than 20 knots
  74. Flight restrictions for practice autorotations:
    *reported surface winds must not exceed 20 knots

    *surface crosswind component must not exceed 10 knots from crosswind chart

    *wind gust spread must not exceed 10 knots

    *touchdown autorotations downwind are prohibited

    *airspeed during autorotation shall not be less than est. for minimum rate of descent

    *ground speed at touchdown should be approx. 5 knots
  75. Flight restrictions for practice autorotations continued:
    *Touchdown in a level attitude prior to passing through 70% rotor RPM

    *Upon ground contact, collective pitch shall be reduced smoothly while maintaining the cyclic near the neutral or centered position

    *If skid "chatter" is encountered, a SLIGHT increase in collective may be temp. used to stop it

    *Continue to reduce collective as soon as practicable when chatter stops
  76. Flight restrictions for practice autorotations is prohibited when gross wt is above...
    3,200lbs
  77. Flight restrictions for practice autorotations...

    ------CAUTION------
    *Relatively long ground runs with the collective up, or any tendency to float for long distance prior to skid contact shall be avoided

    *If abnormal vibrations are felt before or after touchdown, immediate lowering of collective is recommended to dampen

    *Under normal conditions, the collective will be smoothly and slowly lowered to the full down position after skids on ground.

    *Cyclic will remain near neutral with aft cyclic inputs avoided.
  78. Slope Landing/Takeoff limitations
    limited to 8 degrees or less
  79. Slope landing/takeoff limitations:

    ------CAUTION-----
    *Caution is to be excercised on slopes greater than 5 degrees since rigging, loading, terrain, and wind conditions may alter the slope landing capability
  80. Flight under IMC: General limitations
    The anti-collision light may be turned off during flight or in near visible moisture to prevent reflections and possible pilot vertigo

    Keep cabin glass clean to prevent halation

    Maximum precision approach angle is 4.7 deg
  81. Flight under IMC: Rate of climb/descent
    Max rate of climb and descent=1000ft/min
  82. Flight under IMC: required equip
    • -Cyclic force trim system
    • -main gen
    • -standby gen
    • -batt. protection circuit
    • -pilot's flight instruments
    • -co-pilot's flight instruments
    • -standby attitude gyro-automatically powered by approved standby battery source in event of primary pwr loss
    • -2 comm systems
    • -2 nav systems appropriate to routes flown
    • -other equip as req. by operating rules
  83. Flight restrictions in falling or blowing snow
    Flight in falling and/or blowing snow is prohibited unless the Particle Separator Engine Air Induction System Kit and the Deflector Kit are installed to reduce possibility of engine flameout.

    If Kit is installed, hover flight is limited to 20min, then helicopter must be landed and checked for snow/ice accumulation

    Flight ops are prohibited when visibility is less than 1/2 statute mile
  84. Flight over salt water: caution
    prolonged hovering over salt water which results in spray ingestion, indicated by spray on windshield, should be avoided
  85. Flight over salt water and volcanic activity
  86. When aircraft has been operated within 10 miles of salt water or within 200 miles of volcanic activity, entry on DA 2408-13-1 to alert maint.
  87. Flight in Sand and Dust Conditions
    Operations in heavy sand or dusty conditions without the improved nozzles will result in lower inlet particle separator (IPS) efficiency which in turn severely shortens the engine life

    If the inlet air barrier filter is installed and the AIR INLET PRESSURE caution light illuminates or ENGINE AIR ALTERNATE switch is turned on, appropriate entries on Da 2408-13-1 to alert maint
  88. Flight in rain, snow, or icing conditions
    entry on DA 2408-13-1 to alert maint
  89. Exceeding operational limits
    entry on DA 2408-13-1 and state what limts were exceeded, range, time beyond limits, and any additional data that would aid maint. personnel in the inspection
  90. Fuel boost pump limitations
    Fuel boost pump shall be ON during normal ops

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