H-60 Dash 1

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cthad
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193279
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H-60 Dash 1
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2013-01-20 15:57:08
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Flashcards from H-60 Ops Manual
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  1. 5 Stab Warnings:
    • 1.Accel with Stabilator full down you will lose longitudinal control
    • 2.Stab hardover may cause it to move down when you press Auto Control Reset
    • 3.Momentary loss of AC; may cause stab to program down
    • 4.If Auto Mode repeatedly fails; no fly >70 kts in Auto
    • 5.A/S Advisory Lt; no fly >70 kts in Auto
  2. If A/S Advisory Lt on and/or Auto Mode repeatedly fails.  Do not flly over_____ kt in Auto Mode
    70 kts
  3. Pitch Boost Hardover Force
    20 lbs
  4. Yaw Trim SAS Malfunction Force
    30 lbs
  5. Yaw Trim Actuator Jam Force
    80 lbs
  6. Yaw Boost and/or T/R Servo Fail Force
    250 lbs
  7. Required to perform HIT Check
    • 1.1st Flight of the day
    • 2.Engine deterioration suspected
    • 3.After Salt Water Ops
  8. Allowed In-Flt Hit Ck vs Ground
    • 1.Discretion of crew
    • 2.May ingest FOD while on ground
  9. Open/Close Doors max KIAS
    130 kts
  10. Doors Open Max KIAS (soundproofing removed)
    145 kts
  11. Hoist Cable Length
    200 feet
  12. Normal Rate Breeze Eastern Hoist
    Normal Rate Lucas Western Hoist
    • 0 - 215 fpm
    • 0 - 250 fpm
  13. Hoist rate using P/CP switch
    100 fpm
  14. Warning: If AFCC computer is blank or "Computer Bad"....
    Do not fly aircraft
  15. Caution for Aux Fuel System Check
    Fuel Pumps may overheat if transfering fuel while Main Tanks full
  16. Caution: Do not select _________ Transfer with Man Aux Flow in "Flow".  May cause pump failure.
    Auto
  17. Tie down rotor blades above  _______ kts wind
    45
  18. Fold main rotor blades when ______ kts wind.
    60
  19. Maximum you can pull down on MR blade at nose of aircraft:
    6 inches
  20. APU Start Checklist
    • 1.Cabin Heat - OFF
    • 2.Air Source Heat/Start - APU
    • 3.Fuel Pump - APU Boost
    • 4.APU Switch - ON
  21. Warning: After dumping fuel ________ is Inoperative
    Auto Fuel Transfer
  22. Initial action for Uncommanded Nose Down Pitch Attitude Change
    Aft Cyclic, Collective maintain or raise
  23. At what airspeed does Uncommanded Nose Up Pitch Attitude Change become noticeable?
    140 kts
  24. Stabilator Malfunction: Characteristic of Approach with Stab @ 0 deg.
    4-5 deg nose higher than normal at 20-40 kts
  25. Caution for Refueling Probe Check: amount of fuel change in Main Tanks should be no more than _____ lbs.  A change of ______ could indicate faulty valve allowing fuel to XFR from Main to AUX.
    20-30 lbs  /  80-120 lbs
  26. Warning: Satcom use on ground
    No body should be on top of Helo when transmitting on Satcom.
  27. Warning: Use of RADAR on ground
    RADAR has 15' hazardous area in front when on ground.
  28. Warning: Engine Cowlings
    One person on cowling (250 lbs max) Total Max weight = 400 lbs
  29. Engine Start Parameters:
    1.TGT < ____ deg C before Thrtl to Idle
    2.If OAT < ____ deg C, obtain Max Ng before Thrtl to Idle
    • 1.80 deg C
    • 2. 15 deg C
  30. Abort Eng Start If: (5 items)
    • 1.No TGT rise w/in 45 sec
    • 2.No Nf/Nr w/in 45 sec
    • 3.No Eng Oil Press w/in 45 sec
    • 4.TGT > 851 deg C prior to 63% Ng
    • 5.Starter dropout prior to 52-65%
  31. If Eng Start aborted for no TGT rise...
    Motor Eng 30 sec prior to next start attempt
  32. Caution: If you attempt start with Ignition switch off...
    Abort start, do not flip Ignition on in middle of start.
  33. Note: E. AI. Lights before start should be...
    Illuminated
  34. RADAR/VAWS Test Procedure (3 steps)
    • 1.Set 80' / 800' (LO & DH lights on / Digit 0-3' & Needle +-5')
    • 2.Press to Test (1000+-100' / HI light / Betty: "Check Altitude"
    • 3.Release (Betty "Low Altitude" / Silence / All crew members acknowledge)
  35. Accurate INU Alignment Requirements
    • 1.Starting Coordinates
    • 2.HSI Heading (Slaved & Aligned)
    • 3.SGU Altitude (VSDS Cal)
    • 4.Magnetic Variance
  36. 1.MR Disk Diameter:
    2.Overall Length:
    3.T/R to Ground:
    • 1.53'8"
    • 2.64'10"
    • 3.6'6"
  37. Caution: APU Starting
    1.If APU shuts down...
    2.If APU OIL TEMP HI...
    3.If no start...
    • 1.don't cycle APU Cntr Sw, don't cycle Batt Sw
    • 2.shut down, wait 30 min and check oil prior to starting again.
    • 3.wait 2 min prior to attempting restart
  38. Stabilator Check
    • 1.34-42 deg
    • 2.Press Test, Stab Lt & Horn, Up 5-12 deg
    • 3.Auto Contr Reset, Back to Orig Posn
    • 4.Pil up 15 deg, CP up 15 deg, Up to 6-10 deg, Down to 0
    • 5.Auto Contr Reset back to Orig Posn
  39. Warning: Stabilator Check
    Do not fly if it fails any portion of the check.
  40. Batt Sw ON - What Caution Lights?
    • C-#1&#2 CONV
    • B-BATTERY ONLY
    • B-BOOST SERVO OFF
    • A-A/C ESS BUS OFF
    • S-SAS OFF
    • S-STABILATOR
    • 2xMASTER CAUTION
    • Eng Off Horn
  41. AHHS Check
    • 1.AFSC - All ON.
    • 2.AHHS HOV - ON; HOV & RDR ALT Switches
    • AHHS Armed Lt; Roll/Pitch Bars; CDI/GS & CPI; GA&AHHS Fail Lts Off
    • 3.TRIM - OFF; AHHS CL On
  42. Flight Contr & Hydraulics Check (no AHHS)
    • 1.Iso Hyd #1/#2; Cyc/Pdls>5sec, Coll <1sec (Non Iso Pri Svo does NOT Illum)
    • 2.T/R Back Up - Sel; Left Pdl:Star-in, Right Pdl
    • 3.Boost - OFF; Coll>5sec (1.5"), Pdls(.75" ea)
  43. Before Taxi/Takeoff
    1.TQs Matched w/in:
    2.TQ Matched w/in Computed pwr:
    3.If Test A/B pushed repeatedly:
    • 1.5%
    • 2.+-3%
    • 3.May get 95+-3% error on TQ Gauge
  44. 1.TQ Loss w/ E. AI. On:
    2.Max TQ Incr using DECP
    • 1.-18%
    • 2.+3%
  45. Caution: Eng Shutdown
    1.Engine Cool-down requirement
    2.If C/D is not followed
    • 1.Ng<90% for 2 min prior to shutdown
    • 2.Eng must be restarted w/in 5 min or else cooled for 4 hrs for #4 Eng Bearing
  46. Eng Shutdown: Droop stops in by _____. If not in...
    50% - accel to 75% Nr and move cyc slightly then decel again.
  47. Engine Inlet Anti Ice
    1.Adv Light Illum when temp at Inlet =
    2.EI. AI. should open when (OAT Conditions)
    3.When EI. AI. turned off, Adv Lt should extinguish in ____ sec
    4.When OAT<-25 degC...
    5.During Start, EI.AI. should be...
    • 1.93 deg C
    • 2.>13 deg C; Not On / 4-13 deg C; May be On / <=4 deg C; Will be On
    • 3.90 sec
    • 4.TGT rise may be up to 125 degC when EI.AI. valve opens
    • 5.During start EI.AI. is held close
  48. Warning: Engine Anti Ice Loss of Power
    May lose up to 18% power.  Consider turning off while hovering, or flying at low alt/aspd
  49. HIT Check Write Ups w/o Abort Req'd (2)
    • 1.TGT rise w/in 5 deg of HIT Log max
    • 2.TQ Matching not w/in 60+-5%
  50. Warning: Flight Contr Hydraulics Check; While moving collective ensure... (2)
    • Ensure Non-isolated SERVO Lt does not illum. May indicate Pri Servo Bypass Valve jam in isolated Servo.
    • Ensure cyclic does not move when collective is moved. May indicate rate related discrepancy between servos.
  51. Warning: HIT Check if E.AI. / EI.AI. checks fail. (2)
    • 1.If TGT rise>110 deg C or EI.AI. malfunctions do not take if Icing Conditions
    • 2.Malf E.AI. & EI.AI. may cause power loss up to 40%
  52. WOW Functions Left Side
    • B/U Pump Thermal Sw disabled in Flt
    • B/U Pump Off Sw disabled in Flt
    • Retracted Probe Refuel disabled on G
    • AFCC MX Test disabled in Flt
    • AHHS Fcns disabled on G
    • Transponder Mode IV dumped unless held
    • SAS Roll Fcn disabled on G
    • Windshield override disabled on G
    • Audio for Low Nr disabled on G
    • SPS/Flare launch disabled on G
    • Hyd LDI Test disabled in F
  53. WOW Functions Right Side
    • Underfreq protection for Gen disabled in F
    • MX Fcns for CDU disabled in F
  54. Caution: Starter Dropout Malfunction
    • 1.Pull down on Throttle
    • 2.Circuit Breaker
    • --#1-DCE panel O/H Pil side
    • --#2-2 DCP above Pil's head
    • 3.Remove air source
  55. May accomplish in Flight HIT Check In Lieu of Ground when: (2)
    • 1.FOD ingestion is possible
    • 2.Crew Discretion
  56. Required to accomplish In Flight HIT check when: (2)
    • 1.Eng Deterioration suspected
    • 2.After Salt Water Ops
  57. HIT Check Numbers
    1.TQ Stiction limit at ___ % Nf
    2.Max TGT rise for Air Source Heat Sw
    3.TGT rise for E.AI.
    • 1.Zero-5% / 92-98%
    • 2.5 deg C
    • 3.30-110 deg C
  58. HIT Check Fail (6)
    • 1.TQ Stiction >5%
    • 2.TGT outside HIT Log limit
    • 3.Air Src Sw TGT rise >5 deg C
    • 4.TGT rise<30 degC or>110 degC w/ Icing
    • 5.EI.AI. fails with icing
    • 6.TGT does not return to previous reading
  59. In Flight HIT Check
    1.Pull TQ to:
    2.Expect TGT to rise:
    • 1.62%
    • 2.50-80 degC
  60. Post Start Engine Parameters
    1.Eng Out Warning Off at:
    2.Ng > ___%
    3.#1 & #2 Eng Ng match within ___%
    4.Avoid Nf Range ____ & ____
    • 1.55%Ng
    • 2.63%Ng
    • 3.3%Ng
    • 4.20-40 & 60-90% Nf (adv throttle as necessary)
  61. Warning: APU Compartment Fire
    1.With no AC power...
    2.Resetting the...
    • 1.Only the Reserve Bottle can be fired
    • 2.Resetting the T-Handle will cause the APU to restart.
  62. Turbulence Limits
    1.Intentional flight into known___ prohibited
    2.Intentional flight into ____ prohibited
    • 1.Severe
    • 2.Thunderstorms
  63. Icing Limits
    1.Equip req'd for ANY icing
    2.Equip Req'd for Trace
    3.Equip Req'd for Light
    4.Equip Req'd for Moderate
    Icing Definition:
    • 1.E.AI. / EI.AI. / Wndshld AI. / Pitot Ht req'd for any icing.
    • 2.Above
    • 3.Above (not recommended w/o Bld DeIce)
    • 4.Above + Blade DeIce
    • Icing = Visible Moisture / OAT =<4 degC
  64. Ng Alternator Powers: (3)
    • 1.Ng gauge
    • 2.DECU
    • 3.Ignition Exciter
    • Airframe power is b/u for 2 & 3
  65. HMU Functions (4)
    • G-Governs Ng (variable inlet guide vanes)
    • M-Meters Fuel
    •   --Sets max power for PAS
    •   --Responds to LDS
    • O-Overspeed Protection (Ng > 110+-2%)
    • P-Pressurizes fuel for nozzles
  66. AFCS Master Caution Lights
    1.BOOST SERVO OFF =
    2.SAS OFF =
    3.FLT PATH STAB =
    4.TRIM FAIL =
    • 1.Hyd press from PAM to Pedal/Collective boost servos <2000+-50 psi
    • 2.Hyd press from PAM to SAS Actuator <2000+-50 psi
    • 3.FPS inop in one or more axes
    • 4.Y,R or P trim actuators not responding properly (FPS will also be on)
  67. EP Initial Action: Eng Compressor Stall
    Reduce Collective, Throttle to Idle
  68. EP Initial Action: High Speed Shaft Failure
    Affected Engine - Idle
  69. EP Initial Action:Torque Split
    Suspected Engine - Idle
  70. EP Initial Action: OIL FILTER BYPASS Light
    Affected Engine - Idle
  71. EP Initial Action: CHIP INPUT MDL
    Affected Engine - Idle
  72. EP Initial Action: Increasing Nr
    Affected Engine - Idle
  73. EP Initial Action: Engine Oil Temp
    Affected Engine - Idle
  74. EP Initial Action: CHIP ENGINE
    Affected Engine - Idle
  75. EP Initial Action: Engine Compartment Fire
    Affected Engine - Off
  76. EP Initial Action: Engine FOD
    Affected Engine - Off
  77. EP Initial Action: ENGINE OIL PRESS
    Affected Engine - Off
  78. #1 Hyd System Leak - 1st Stage of Leak; Lights and location of leak.
    #1RSVR LOW, #1 TAIL RTR SERVO, BACKUP PUMP ON, #2 TAIL RTR SERVO ON - Leak in hydraulic lines to T/R.
  79. #1 Hyd System Leak - 2nd Stage of Leak; Lights and location of leak.
    #1RSVR LOW, #1HYD PUMP, BACKUP PUMP ON - Up Stream of #1Transfer Module
  80. #1 Hyd System Leak - 3rd Stage of Leak; Lights and location of leak.
    #1RSVR LOW, #1HYD PUMP, BACKUP PUMP ON, BACKUP RSVR LOW - Leak in #1Primary Servos; Isolate 1st Stage: #1PRI SERVO PRESS
  81. #2 Hyd System Leak - 1st Stage of Leak; Lights and location of leak.
    #2RSVR LOW, BOOST SERVO OFF, SAS OFF, TRIM FAIL, FLT PATH STAB - Leak in the PAM.
  82. #2 Hyd System Leak - 2nd Stage of Leak; Lights and location of leak.
    #2RSVR LOW, #2HYD PUMP, FLT PATH STAB, TRIM FAIL, BACKUP PUMP ON - Leak upstream of the #2 Transfer Module
  83. #2 Hyd System Leak - 3rd Stage of Leak; Lights and location of leak.
    #2RSVR LOW, #2HYD PUMP, FLT PATH STAB, TRIM FAIL, BACKUP PUMP ON plus BACKUP RSVR LOW - Leak in #2Primary Servo; Isolate 2nd Stage: #2PRI SERVO PRESS
  84. Lights that will turn on the Backup Pump (5)
    • #1TAIL RTR SERVO
    • #1HYD PUMP
    • #1RSVR LOW
    • #2HYD PUMP
    • APU ACCUM LOW
  85. #1HYD PUMP Caution Light On - If Backup Pump does not operate, both T/R servos are inop and you will have limited T/R authority.  Accomplish roll on landing above _____ kts
    40 kts
  86. NOTE: Boost Servo Malfunction - may or may not be accompanied by
    Caution Lights
  87. Pitch Boost Servo Hardover - how it manifests, how to eliminate?
    Approximately 20lb force felt in cyclic longitudinal; turn off SAS
  88. Pedal Bind/Restriction or Drive with No Accompanying Caution Light - how it manifests, how to eliminate?
    SAS/FPS Yaw malfunction can create up to 30 lbs of force at pedals. Jammed Yaw Trim actuator can take 80 lbs of force to oppose.  Yaw Boost and/or Tail Rotor Servo malfunction may cause up to 250 lbs of pressure.  Try shutting off Trim or Boost or switching to #2TAIL RTR SERVO.
  89. Tail Rotor Quadrant Caution Light On (with Loss of T/R Control): Approximate Airspeeds for Trimmed Flight:  _____  and _____
    Above or below those airspeeds = ____ yaw
    In between those airspeeds = ____ yaw
    • 25 & 145 kts
    • Right Yaw
    • Left Yaw
  90. With SAS/FPS computer, ______ is req'd for Turn Coord to disengage and transition to Hdg Hold
    Airspeed < 60 KIAS
  91. If the Ground BITE check AFCC is inadvertently initiated _____.
    Do not take off for approximately 2 min to ensure FPS authority is enabled
  92. Flight near high power RF emitters such as _________ may cause __________
    • Microwave antennas or shipboard radar
    • Uncommanded AFCS and/or Stabilator inputs
  93. Warning: If _____ part of the stab check fails ______.
    • Any
    • Do not fly the aircraft
  94. With AFCC, turn coordination will disengage and transition to heading hold when:
    -Roll attitude < ___
    -Roll rate < ___
    -Airspeed < ___
    • 3 deg
    • 5 deg/sec
    • 60 kts

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