SH-60B EPS

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Author:
Maximus
ID:
222425
Filename:
SH-60B EPS
Updated:
2013-06-25 21:50:36
Tags:
EPS emergency procedures
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Description:
SH-60B Emergency Procedures
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  1. The following should be performed for all emergencies:
    • 1. Maintain control of the aircraft.
    • 2. Alert crew.
    • 3. Determine the precise nature of the problem.
    • 4. Complete the applicable emergency procedure or take action appropriate for the problem.
    • 5. Determine landing criteria and land as required.
  2. Engine Malfunction In Flight
    • *1. Control Nr.
    • Warning
    • Flying at an airspeed greater than 105 KIAS with one engine inoperative may result in unrecoverable decay of Nr in the event of a dual−engine failure.
    • *2. CONTGCY PWR switch — ON.
    • *3. Single−engine conditions — Establish.
    • *4. ENG ANTI−ICE switches — As required.
    • Warning
    • With engine anti−ice on, up to 18 percent torque available is lost. Torque may be reduced as much as 49 percent with improperly operating engine inlet anti−ice valves.
    • *5. External cargo/stores/fuel —JETTISON/DUMP, as required.
    • *6. Identify malfunction.
  3. Engine High-Side Failure In Flight
    • *1. Engine Malfunction in Flight emergency procedure — Perform.
    • *2. PCL (malfunctioning engine) — Retard to set:
    •    a. Torque 10 percent below good engine or
    •    b. Matched Ng or
    •    c. Matched TGT.
    • 3. Land as soon as practicable
  4. Engine High-Side Failure on Deck
    *1. PCLs — IDLE.
  5. Engine Low−Side Failure in Flight
    • 1. Engine Malfunction in Flight emergency procedure — Perform
    • 2. PCL (malfunctioning engine) — Momentarilyadvance to LOCKOUT, then retard to set:
    •     a. Torque 10 percent below good engine or
    •     b. Matched Ng or
    •     c. Matched TGT.
    • 3. Land as soon as practicable
  6. Engine Torque or TGT Spiking/Fluctuations
    • If an engine instrument is spiking/fluctuating and inducing secondary indications in Ng, Np, and/or Nr:
    • *1. Engine Malfunction in Flight emergency procedure — Perform.
    • If fuel contamination is suspected:
    • *2. Land as soon as possible.
    • Warning
    • PCL movement during engine fluctuations may precipitate an engine failure. Consider performing APU Emergency Start procedure prior to manipulating the PCL. Maintaining a low power setting when moving the PCL will minimize the Nr decay rate if the malfunctioning engine fails.

    • If engine electronic circuitry is suspected:
    • 3. PCL (malfunctioning engine) — Momentarilyadvance to LOCKOUT, then retard to set:
    • a. Torque 10 percent below good engine or
    • b. Matched Ng or
    • c. Matched TGT.
    • If fluctuations persist:
    • 4. PCL (engine in LOCKOUT) — Retard to IDLE,then return to FLY.
    • 5. Repeat steps 3. and 4. for the other engine,as required.
    • If an engine instrument is spiking/fluctuating with no secondary indications:
    • 6. Land as soon as practicable.
  7. Compressor Stall
    • *1. Engine Malfunction in Flight emergency procedure — Perform.
    • *2. PCL (malfunctioning engine) — IDLE.

    • Caution
    • If the Ng decay relight feature attempts to relight the engine,subsequent compressor stalls may occur and damage the engine. A yaw kick may be experienced each time the engine relights. The engine must be manually shut down.
  8. Engine High−speed shaft failure
    • *1. Engine Malfunction in Flight emergency procedure — Perform.
    • *2. PCL (malfunctioning engine) — OFF.
    • 3. Land as soon as practicable.
    • Caution
    • Following a high−speed shaft failure, the engine will overspeed, the Np overspeed system will flame out the engine, and the autoignition system will activate the relight feature. The engine Np governor will eventually bring Np down toward 100 percent. The engine must be manually shut down to prevent further damage.
  9. Abort Start
    • 1. PCL — OFF.
    • *2. ENGINE IGNITION switch — OFF.
    • *3. Starter — Engage.
    • 4. Starter — Disengage after 30 seconds and TG Tbelow 540 C.
  10. Abort engine start if any of the following limits is exceeded:
    • 1. Ng does not reach 14 percent within 6 seconds after starter initiation.
    • 2. No oil pressure within 30 seconds after starter initiation (do not motor engine).
    • 3. No light−off within 30seconds after moving PCLto IDLE.
    • 4. ENGINE STARTER advisory disappears before reaching 52 percent Ng.
    • 5. TGT reaches 851 0C before idle is attained.
    • CAUTION
    • For aborted starts, fuel flowmust be stopped immediately (PCL — OFF)to prevent engine overtemperature.
  11. Engine Malfunction During Hover/ Takeoff
    • *1. Control Nr.
    • *2. CONTGCY PWR switch — ON.
    • If a suitable landing site exists or unable to transition to forward flight:
    • *3. Set level attitude, eliminate drift, cushion landing.
    • If able to transition to forward flight:
    • *4. Engine Malfunction in Flight emergency procedure— Perform.
  12. Dual−Engine Failure inFlight
    • Collective — Full down, enter autorotation.
    • *1. Immediate landing/ditching emergency procedures— Perform.
    • If time and altitude permit:
    • *2. Engine Air Restart emergency procedures —Perform
  13. ENG OUT(#1/#2)
    *1. Engine Malfunction in Flight emergency procedure — Perform.
  14. Engine Air Restart
    • *1. APU Emergency Start procedure — As required.
    • *2. ENGINE IGNITION switch — NORM.
    • *3. Fuel selector lever(s) — DIR or XFD.
    • *4. PCL(s) — OFF.
    • *5. Starter(s) — ENGAGE, motor engine.
    • *6. PCL(s) — IDLE (TGT 80 C or less, if time permits).
    • *7. PCL(s) — Advance to FLY after starter dropout.
    • Caution
    • Engine failure accompanied by an explosion or unusual noise indicates damage to the engine. There is a possibility that any attempt to restart the engine may result in a fire. Under such circumstances, do not try to restart the engine unless it is needed to maintain level flight.
  15. APU Emergency Start
    • *1. ECS — OFF.
    • *2. AIR SOURCE ECS/START switch — APU.
    • *3. FUEL PUMP switch — APU BOOST.
    • *4. APU CONTROL switch — ON.
    • *5. APU GENERATOR switch — Check ON.
  16. Unusual Vibrations on Deck
    • *1. Collective — Lower.
    • *2. PCLs — OFF.
    • *3. Rotor brake — Apply as required.
  17. Hung Droop Stop(s)
    *1. Reengage rotor to greater than 75 percent Nr.
  18. LOW ROTOR RPM
    • Warning light is activated by the vertical instrument when Nr is 95percent or less.
    • *1. Control Nr.
    • 2. Determine cause of low Nr condition.
  19. Main Transmission Malfunction
    MAIN XMSN OIL TEMP
    or
    MAIN XMSN OIL PRESS
    or
    CHIP
    • If failure is imminent:
    • *1. Land immediately.
    • If secondary indications are present: 
    • *2. Land as soon as possible.
    • Warning
    • Possible Indications of main transmission imminent failure may include: yaw attitude excursions with no control input, an increase inpower required for a fixed collective setting,failure of a main generator or hydraulic pump,increased noise, increased vibration levels, or abnormal fumes in the cabin.
  20. CHIP INT X MSN 
    or
    INT XMSN OILTEMP
    or
    TAIL XMSN OIL TEMP
    • If failure is imminent:
    • *1. Land immediately.
    • If failure is not imminent:
    • *2. Land as soon as possible.
  21. Loss of TailRotor Drive Altitude and Airspeed Sufficient to Establish Autorotation
    • *1. PAC call — AUTO, AUTO, AUTO.
    • *2. Autorotation — Establish. Center tail rotor pedals.
    • *3. Drive failure — Attempt to verify.
    • *4. Immediate Landing/Ditching emergencyprocedure — Perform.
    • *5. PCLs — OFF when directed (prior to the flare).
  22. Loss of Tail Rotor Drive and Airspeed Not Sufficient to Establish Autorotation
    • *1. PAC call — HOVER, HOVER, HOVER.
    • *2. Collective — Lower.
    • *3. PNAC — Hand on PCLs.
    • *4. PCLs — OFF when directed (approximately 20 to 30 feet).
  23. Loss of Tail Rotor Control
    *1. Collective/airspeed — Adjust as required to control yaw.
  24. #1 RSVR LOW & #1 HYD PUMP cautionlight illuminate,  BACK−UP PUMP ON
    • *1. SERVO switch — 1ST OFF.
    • *2. Land as soon as practicable.
    • If the BACKUP RSVR LOW caution also appears or the backup pump fails:
    • *3. Land as soon as possible.
    • Note:
    • Be prepared for loss of tail rotor control.
    • If the #2 PRI SERVO caution and/or HYD warning appears:
    • *4. Land immediately.
    • CAUTION
    • Switching the BACK UP HYD PMP to OFF withweight on wheels and #1 HYD PUMP caution lightilluminated will result in loss of tail rotor directionalcontrol when the backup pump secures.
  25. ##2 RSVR LOW #2 HYD PUMP
    and Back UP PUMP ON
    • *1. SERVO switch — 2ND OFF.
    • *2. Land as soon as practicable.
    • If the BACKUP RSVR LOW caution also appears or backup pump fails:
    • *3. Land as soon as possible.
    • If the #1 PRI SERVO caution and/or HYD warning appears:
    • *4. Land immediately
  26. Boost Servo Hardover
    *1. SAS/BOOST pushbutton — OFF.
  27. STABILATOR
    • 1. PAC call — STAB, STAB, STAB.STABILATOR
    • *2. Cyclic — Arrest pitch rate.
    • *3. Collective — Do not reduce.
    • *4. MAN SLEW switch — Adjust to 0.When at a safe altitude and airspeed (below 70 KIAS):
    • Warning
    • It is possible for the stabilator to fail without illumination of the stabilator caution light and associated aural warningtone. In this case, the first indication of failure will be an uncommanded pitch change.
  28. Unusual Attitude Recovery
    • *1. Level wings.
    • *2. Nose on horizon.
    • *3. Center ball.
    • *4. Stop rate of climb/descent.
    • *5. Control airspeed
  29. Total Ac Power Failure/Dual Generator Failure
    • *1. Safe altitude and airspeed — Establish.
    • *2. Stabilator — Check position, SLEW as required.
    • *3. APU Emergency Start Procedure — Perform.
    • 4. AFCS/SAS — ON.
  30. #1 or #2 FUEL FLTR BYPASS or #1 or #2 FUEL PRESS Caution Lights
    • *1. Fuel selector lever (affected engine) — XFD (DIR ifcurrently in XFD).
    • 2. Land as soon as practicable
  31. External Engine Fire
    • *1. Confirm fire.
    • *2. Engine Malfunction in Flight emergencyprocedure — Perform.
    • *3. PCL (affected engine) — OFF.
    • *4. Engine T−handle (affected engine) — Pull.
    • *5. FIRE EXT switch— MAIN (RESERVE if required orac power is off).If airborne and fire continues:
    • *6. Land immediately.
    • If fire appears extinguished:
    • *7. Land as soon as possible
  32. Internal Engine Fire
    • *1. Starter — Engage. Motor engine.
    • 2. Portable fire extinguisher — As required.
    • 3. Starter — Secure (once TGT decreases below540 C).
  33. APU Fire
    • 1. APU T−handle — Pull.
    • *2. Confirm fire.
    • *3. FIRE EXT switch — RESERVE (MAIN if requiredand available).If airborne and fire continues:
    • *4. Land immediately.If fire appears extinguished:
    • *5. Land as soon as possible.
    • If on ground:
    • *6. Fire extinguisher — As required.
    • 7. FUEL PUMP switch — OFF.
    • 8. APU CONTROL switch — OFF.
  34. Cockpit Fire/Cabin Fire
    • Source is known:
    • *1. Affected power switches and circuit breakers —Secure.
    • *2. Portable fire extinguisher — As required.
    • If fire continues or source is unknown:
    • *3. Cabin/doors/vents/ECS — CLOSE/OFF, as required.
    • *4. Unnecessary electrical equipment and circuit breakers — Secure.
    • If fire continues:
    • *5. Land as soon as possible.
    • 6. Stabilator — Manually slew to zero.
    • 7. NO. 1 and NO. 2. GENERATOR switches — OFF, as required
    • 8. BATT switch — OFF, as required.
    • If fire is extinguished:
    • 9. Smoke and Fumes Elimination emergencyprocedure — Perform.
    • 10. Land as soon as practicable.
  35. Sonobuoy Lithium Battery Venting
    • *1. Alert crew; sonobuoys — Jettison.
    • *2. Smoke and Fumes Elimination emergencyprocedure — Perform.
    • Warning
    • Portable fire extinguishers shall not be used to extinguish burning lithium fires since a violent reaction may occur.
  36. Smoke and Fumes Elimination
    • *1. Airspeed — Adjust, as required.
    • *2. Doors/windows/vents — Open.
    • *3. Aircraft — Yaw, as required.
  37. Immediate Landing/Ditching (Pilot)
    • *1. Crew and passengers — Alert.
    • *2. Shoulder harness — Locked.
    • *3. External cargo/stores/fuel — Jettison/dumpas required.
    • *4. Searchlight — As required.
    • *5. MAYDAY/IFF — Transmit/EMER.
    • *6. Windows — Jettison, as required.
    • After landing:
    • *7. PCLs — OFF.
    • *8. Rotor brake — ON.
    • *9. ATO collective — Stow.
    • After all violent motion stops:
    • *10. Egress.
  38. Underwater Egress
    • *1. HABD — As required.
    • *2. Cord(s) — Disconnect.
    • *3. Door/window — Open/jettison.
    • *4. Place hand on known reference point.
    • *5. Harness — Release.
    • *6. Exit helicopter.After egress: Do not inflate LPU until outsidehelicopter.
    • *7. Swim clear of helicopter and inflate LPU.
  39. FLIR Uncommanded Lasing
    • *1. WEAPON SELECT (AN/ASQ-198) — OFF.
    • *2. MASTER ARM — Verify SAFE.
    • *3. LASER — DISABLE.
    • If lasing continues:
    • *4. FLIR PWR — OFF.
    • *5. FLIR circuit breakers — Pull (SO circuit breakerpanel, SO OVHD: FLIR AC, FLIR/HFSAC,FLIR/HFS AC).
  40. #1 and #2HYD PUMP Failure
    • *1. Restrict flight control movement.
    • *2. Land as soon as possible.
  41. Turbine Gas Temperature
    • 12 Seconds 903-949
    • 2.5 Minutes 851-903
    • 30 Minutes 810-851
    • Normal 0-810
    • DECU limit 839+/-10
    • With C-power 891+/-10
  42. Single Engine Torque Limits
    0-13000 135%   10 SEC 135-144%
  43. Dual Engine Torque Limits
    • 0-4000       106%
    • 4000-5000  103%
    • 5000-6000  100%
    • 6000-8000   94%
    • 8000-10000  88%
    • 10000-13000 78%

    And 127% for 10 seconds for all altitudes.
  44. Np Limits
    • Maximum 120%
    • Continuous 96%-101%
  45. Fixed Stab Limits
    • 00    150 kias
    • 100 100 kias
    • 20  80 kias
    • 300    60 kias
    • 400    45 kias
  46. Ng Limits
    • 12 sec transient 102% - 105%
    • 30 minute 98%-102%
    • Continuous 0%-98%
  47. Engine Oil Temperature
    • Maximum 1500C
    • 30-min     1350-1500C
    • Continuous -500-1350C
  48. Engine Oil Pressure
    • Max 120 psi
    • Precautionary 100-120psi
    • Normal Operation 26-100psi
    • Precautionary22-26psi
    • minimum 22psi
    • Normal Idle Range is 22-55psi
  49. Main Transmission Oil Temperature
    • Max 1200
    • Precautionary 105-1200C
    • Maximum 1050C
  50. Main Transmission Oil Pressure
    • Max 130psi
    • Precautionary 65-130psi
    • Continuous 30-65psi
    • Idle and Transient 20-30psi
    • Minimum 20psi

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