T-38 Dash 1 Ch 1.txt

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Author:
elitylski
ID:
247901
Filename:
T-38 Dash 1 Ch 1.txt
Updated:
2013-11-19 18:51:23
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t-38 dash 1 ch 1
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  1. Engine
    J85-GE-5R eight-stage, axial-flow, turbojet
  2. MIL Power Thrust (standard day, SL)
    2200 pounds
  3. MAX Power Thrust (standard day, SL)
    3300 pounds
  4. Ignition cycle time
    30 sec
  5. Temps above __ degrees F result in EED activation within __ seconds. Below that temperature it may take __ minutes.
    • 32
    • 15
    • 5
  6. Before engine start EED FF indicator should read no higher than
    60 PPH
  7. Fuel Low light comes on when
    Fuel quantity is 250 pounds or less for 7.5 seconds
  8. MAX AB fuel flow at rest
    7300 PPH
  9. MAX AB fuel flow at Mach 1
    11,400 PPH
  10. Oil reservoir normal capacity
    4 quarts
  11. Oil reservoir air expansion space
    1 quart
  12. Oil consumption through engine operation and overboard venting should not exceed
    1 pint per hour
  13. Flight above __ feet and below __ IMN increases susceptibility to compressor stall/flameout
    • 28,000
    • 0.6
  14. With airspeeds below __ above altitudes of __ maintain rpm at __ or above to avoid engine RPM dropping below ground idle.
    • 200 KCAS
    • 20,000 feet
    • 80%
  15. Above __ feet, cockpit displays provide estimates of
    • Black Stripe Altitude
    • Min Mach
  16. FUEL PRESS Light comes on below __ (normal is __)
    • 6 PSI
    • 10 PSI
  17. Total fuel with single point refueling (JP-8)
    • 583 gal
    • 3906 lbs
    • 1990 lbs right side
    • 1916 lbs left side
  18. Total fuel with manual refueling (JP-8)
    3866 lbs (subtract 6 gal or 40 lbs)
  19. Below __ lbs fuel, boost pump output is reduced to __
    • 650 lbs (either system)
    • 40%
  20. Taxi operations with less than __ lbs in either system could cause cavitation of the boost pump
    150 lbs
  21. Gravity fuel flow only guaranteed below __
    6,000 feet
  22. AC Electrical power provided by:
    Two AC busses powered by 2 engine-driven AC generators
  23. DC Electrical power provided by:
    2 50-amp DC transformer-rectifiers or a 24-volt battery power 2 essential DC busses and 1 nonessential DC bus
  24. Non-essential DC bus drops offline when DC Voltage drops from __ to __ (dual TRU failure)
    • 28 VDC
    • 24 VDC
  25. RPM required for generator operation
    43-48%
  26. AC generator voltage
    115 ± 2 V
  27. AC Generator gearbox shifts at __ Engine speed to maintain output within limits
    65-75%
  28. When AC voltage drops below __ the affected TRU triggers RECTIFIER FAILURE PFL
    180 ± 2 V
  29. The caution light may take up to __ to illuminate after a generator failure
    2.5 sec
  30. When either TRU output falls below __ for more than __ a RECTIFIER FAILURE PFL and AVIONICS advisory are triggered
    • 25.5 V
    • 2 sec
  31. Min voltage to close the battery relay (and apply external power)
    18 V
  32. The battery should remain on until the voltage drops below
    10 V
  33. In the event of a TRU failure the battery supplies power to the two essential busses for __
    15 min
  34. Static inverter converts DC BUS voltage to __
    115 VAC
  35. Static inverter activated when:
    • Engine start button pressed
    • OXY/FUEL switch held in GAGE TEST
    • OXY/FUEL switch held in QTY CHECK
    • Either throttle moved to MAX (in flight)
  36. Hydraulic system pressure
    3000 PSI
  37. Hydraulic caution light activation occurs when:
    • Pressure is 1500 PSI and below (goes out when restored to 1800 PSI)
    • Fluid overtemperature detected
  38. Left engine hydraulic system
    Utility
  39. Right engine hydraulic system
    Flight control
  40. Landing gear warning conditions
    • Below 210 KCAS
    • Below 10,000 feet
    • Throttles below 96% RPM
  41. Red light extinguishes during gear extension
    All three gear down and locked
  42. Red light extinguishes during gear retraction
    All three gear doors closed
  43. Gear caution voice message activated
    • With nose gear down and locked above 240 KCAS
    • With nose gear down and locked between 220 and 240 KCAS increasing at 2 kts/sec
  44. Time window for alternate gear extension
    15-35 sec
  45. Nose gear extension 3/4 or less limits rudder deflection to __
    6 degrees
  46. Nose gear extension more than 3/4 allows full rudder deflection of __
    30 degrees
  47. Rudder trim deflection
    2 degrees
  48. Pneumatic System (HC-CAGED)
    • Hydraulic reservoir
    • Canopy Seal
    • Cabin pressurization
    • Air Conditioning
    • G-Suit
    • Engine anti ice
    • Defog
  49. Cabin pressure scheduling
    • 0 PSI differential up to 8000 feet
    • 8000 ± 1000 feet up to 23,000 feet
    • 5 PSI differential (±2000 feet) above 23,000
  50. Cabin altitude above 23,000 feet
    (Altitude – 6k)/2
  51. RAM DUMP deactivates the following systems (C-CAG-D)
    • Cabin pressurization
    • Canopy seal
    • Air Conditioning
    • G-suit
    • Defog
  52. Defog Thermostat Temperature
    200°F
  53. Defog Overheat Thermostat Temperature
    280°F
  54. Placing ENG ANTI-ICE to MAN ON results in EGT increase of __ at speeds of __
    • 15 °C
    • 94-98% RPM
  55. The anti-ice valve is always open below engine speeds of __
    65% RPM
  56. Loss of thrust with ENG ANTI-ICE on (Thrust, % MIL, % MAX)
    • 180 ±10 pounds
    • 8.5% loss in MIL
    • 5.5% loss in MAX
  57. Items de-iced with PITOT HEAT switch
    • Pitot boom
    • AOA vane
    • Total Air Temperature (TAT) probe
  58. Do not exceed __ with pitot heat on during ground operations
    30 sec
  59. OXYGEN Caution Light illuminates with less than __ LOX
    1 Liter
  60. OXYGEN Caution Light can flicker due to sloshing with less than __ LOX
    3 Liters
  61. Max Endurance AOA
    0.3
  62. Max Range AOA
    0.18
  63. Optimum Approach AOA
    0.55 to 0.65
  64. Approach to Stall Warning AOA
    0.80 to 0.99

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