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Helicopter Aircraft Commander > Emergency Procedures > Flashcards

Emergency Procedures Flashcards

1
Q

Engine Malfunction in Flight

2 x W

A
  1. Control Nr
  2. CONTGCY PWR switch - On
  3. Single-engine conditions—Establish.
  4. ENG ANTI-ICE switches—As required.
  5. External cargo/stores/fuel—Jettison dump, as required.
  6. Identify malfunction.
W= 110% torque
W= Engine anti ice
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2
Q

Engine High Side Failure in Flight
1 x C
3 x N

A
  1. Engine Malfunction in Flight emergency procedure — Perform.
  2. PCL (malfunctioning engine)—Retard to set:
    a. Torque 10% below good engine, or
    b. Matched Ng, or
    c. Matched TGT.
C = Np overspeed
N = High collective
N = Ng is a highly reliable signal
N = Torque signal may be erratic or drop off
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3
Q

Engine High Side Failure on Deck

A
  1. PCLs - IDLE
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4
Q

Engine Low Side Failure

1 x A
Identification

A
  1. Engine Malfunction in Flight emergency procedure - Perform.
A = controlling engine in LOCKOUT
ID = 
1. TRQ is 10% below good engine
2. Ng is 5% or less than good engine
3. Np is at or below 98%
4. Nr is at or below 97%
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5
Q

Engine Torque or TGT Spiking/Fluctuations

1 x W

A

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.

W = PCL movement

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6
Q

Compressor Stall

1 x C

A
  1. Engine Malfunction in Flight emergency procedure - Perform.
  2. PCL (malfunctioning engine) - IDLE

C = Ng Decay Relight feature

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7
Q

Engine High Speed Shaft Failure

1 x C
1 x N

A
  1. Engine Malfunction in Flight emergency procedure - Perform.
  2. PCL (malfunctioning engine) - OFF.
C = engine will overspeed
N = Np sensor unreliable
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8
Q

Abort Start

1 x C
5 x Indications

A 
To abort start:
1. PCL - OFF.
2. ENGINE IGNITION switch - OFF.
If engine oil pressure is indicated:
3. Starter - Engage.

C = failure to secure fuel flow

Indications:

  1. Ng does not reach 14% 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 30 seconds after moving PCL to IDLE.
  4. ENG Starter advisory disappears before reaching 52% Ng.
  5. TGT is likely to exceed 851°C before idle speed is attained.
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9
Q

Engine Malfunction During Hover/Takeoff

A
  1. Control Nr
  2. CONTGCY PWR switch - ON.
    If a suitable landing 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.
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10
Q

Dual Engine Failure

A
  1. Autorotation - Establish.
  2. Immediate landing/ditching emergency procedure - Perform.
    If time and altitude permit:
  3. Emergency air restart emergency procedure - Perform.
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11
Q

Single Engine Failure in Flight

1 x Advisory about ENG OUT light

A
  1. Engine Malfunction in Flight emergency procedure - Perform.

Advisory = Warning light is activated by the vertical instrument when Ng decreases below 55%. In the event of an isolated Ng signal failure, the ENG OUT light will be illuminated with the engine operating normally.

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12
Q

Engine Air Restart

1 x W
1 x C
1 x N

A
  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.
W = APU unavailable
C = crossbreed starts
N = single or dual engine starts
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13
Q

APU emergency start

A
  1. ECS - OFF.
  2. AIR SOURCE ECS/START switch - APU.
  3. FUEL PUMP switch - APU boost.
  4. APU CTRL switch - ON.
  5. APU GENERATOR switch - ON.
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14
Q

Unusual Vibrations on Deck

1 x C

A
  1. Collective - Lower.
  2. PCLs - OFF.
  3. Rotor brake - Apply as required.

C = lead/lag tendencies

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15
Q

Hung Droop Stops

1 x N

A
  1. Re-engage rotor to greater than 70% Nr.

N = Consider turning blade de-ice on

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16
Q

Low Rotor RPM Warning

1 x Advisory

A
  1. Control Nr.

Advisory = Warning light is activated by the vertical instrument when Nr is less than 96%.

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17
Q

Main Transmission Malfunction

2 x W
3 x N

A

If failure imminent:
1. Land immediately.
If secondary indications are present:
2. Land as soon as possible.

W = possible indications of imminent failure
W = operating main gearbox with no oil
N = Consider applicable steps of immediate landing/ditching
N = loss of oil = unreliable temperature indications
N = continued operations in precautionary range
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18
Q

Tail/Intermediate Transmission Malfunction

2 x W
1 x N

A

If failure is imminent:
1. Land immediately.
If failure is not imminent:
2. Land as soon as possible.

W = high power settings
W = transit at altitude to enter autorotation and...
N = An INT XMSN/TAIL XMSN OIL HOT CAUTION occurring simultaneously with a WCA MISCOMPARE...
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19
Q

(#1/2) Input Chip Caution

1x N

A
  1. Main Transmission Malfunction emergency procedure - Perform.

N = Consider returning PCL to FLY

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20
Q

Loss of Tail Rotor Drive Altitude and Airspeed Sufficient to Enter Autorotation

1 x W
1 x Advisory

A
  1. PAC calls “Auto, auto, auto.”
  2. Autorotation - Establish, center tail rotor pedals.
  3. Drive failure - attempt to verify.
  4. Immediate landing/ditching emergency procedure - Perform.
  5. PCLs - OFF when directed (prior to the flare).
W = altitude hold
Advisory = attempt to verify rotation as loss of drive rather than flight control jam or boost hardover
21
Q

Loss of Tail Rotor Drive Altitude and Airspeed Not Sufficient to Establish Autorotation

1 x C

A
  1. PAC calls “hover, hover, hover.”
  2. Collective - Lower.
  3. PNAC - Hands on PCLs.
  4. PCLs - OFF when directed (approximately 20-30ft)

C = Altitude may have to be adjusted

22
Q

Loss of Tail Rotor Control

5 x W
1 x N

A
  1. Collective/Airspeed - Adjust as required to control yaw.
W = servo hardover
W = appearance of #1 tail rotor servo caution
W = after touchdown
W = right yaw, too low airspeed
W = tail rotor cables damaged
N = momentary uncommanded right yaw
23
Q

Tail Rotor Quadrant Caution

1 x C

A
  1. Check for tail rotor control.
    If tail rotor control is not available:
  2. Loss of Tail Rotor Control emergency procedure - Perform.

C = if helo is shutdown or hydraulic power removed

24
Q

Hydraulic System Warning

A
  1. Land immediately.
25
Q

1 and #2 HYD Pump Failure

A
  1. Restrict flight control movement.

2. Land as soon as possible.

26
Q

1 Primary Servo or #1 Transfer Module Leak

1 x W
1 x N

A
  1. Servo switch - 1st OFF.
  2. Land as soon as practicable.
    If the BACKUP RSVR LOW CAUTION appears or the backup pump fails:
  3. Land as soon as possible.
    If the #2 PRI SERVO CAUTION and/or HYD warning appear:
  4. Land immediately.
W = failure to ensure backup pump on or auto
N = be prepared for loss of tail rotor control
27
Q

2 Primary Servo or #2 Transfer Module Leak

2 x N

A
  1. Servo switch - 2nd OFF.
  2. Land as soon as practicable.
    If the BACKUP RSVR LOW CAUTION appears or the backup pump fails:
  3. Land as soon as possible.
    If the #1 PRI SERVO CAUTION and/or HYD warning appear:
  4. Land immediately.
N = Failure to ensure back up pump on/auto
N = be prepared for loss of pilot assist servos
28
Q

Boost Servo Hardover

2 x C

A
  1. PAC calls “ boost, boost, boost.”
  2. SAS/BOOST pushbutton - OFF.
C = up to 75lbs left pedal
C = landings on single spot ships should...
29
Q

Utility Pump Caution

1 x C

A
  1. Stop dome.

C = utility pump with low or no hydraulic fluid

30
Q

AFCS Degraded caution

1 X N

A
  1. Safe altitude and airspeed - establish (waveoff/ITO as required)

N = if caution appears during night/imc

31
Q

Stabilator Auto Mode Malfunction

4 x W
1 x N

A
  1. PAC calls “stab, stab, stab.”
  2. Cyclic - arrest pitch rate.
  3. Collective - do not reduce.
  4. MAN SLEW switch - slew to 0°
W = fail without illumination
W = if accelerated flight is continued
W = with stabilator fixed at or near 0*
W = high airspeed/low altitude
N = In Manual mode the following are not recommended:
Swimmer deployment lower than 15'
Night takeoffs, approaches, and landings (except one-time following failure)
Automatic approaches to a hover
Simulated EPs including practice autos
Flight in known IMC
Stab/Airspeed limits:
0* - 150kias
10* - 100kias
20* - 80kias
30* - 60kias
40* - 45kias
32
Q

Unusual Attitude Recovery

A
  1. Level the wings.
  2. Nose on horizon.
  3. Center the ball.
  4. Stop rate of climb or descent.
  5. Control airspeed.
33
Q

Electrical Power Failure/Dual Generator Failure

2 x W
2 x N

A
  1. Safe altitude and airspeed - establish.
  2. Stabilator - Check position, slew as required.
  3. APU emergency start procedure - Perform.
  4. CMPTR PWR/RESET, SAS1, SAS2, TRIM, AUTO PLT, STABILATOR AUTO CONTROL - ON.
W = exceeding airspeed vs stab angle
W = loss of electrical power, engine anti ice
N = capability to manual slew stab
N = stab position indicator
34
Q

1 OR #2 Fuel Filter Bypass or Pressure Caution

1 x W

A
  1. Fuel selector lever (affected engine) - XFD (DIR if currently in XFD)

W = intermittent fuel pressure caution

35
Q

1 AND #2 Fuel Filter Bypass or Pressure Cautions

2 x W
1 x N

A
  1. Land as soon as possible.
  2. APU emergency start procedure - Perform.
W = Be prepared dual engine failure
W = intermittent fuel pressure caution
N = Consider applicable steps
36
Q

Refueling Hose Jettison (HIFR)

1 x W

A
  1. T-Handle - Pull (if applicable)
  2. Hose status - Report.
    If hose fails to break away:
  3. Quickly disengage the nozzle and grounding wire, then cut the hoist cable

W = hose snap back on breakaway may impact the aircrewman depending on direction of aircraft motion

37
Q

External Engine Fire

1 x N

A
  1. Confirm fire.
  2. Engine Malfunction in Flight emergency procedure - Perform.
  3. PCL (affected engine) - OFF.
  4. Engine T-Handle (affected engine) - Pull.
  5. FIRE EXTGH switch - MAIN (RESERVE if required or AC power is off)
    If airborne and fire continues:
  6. Land immediately.
    If fire appears extinguished:
  7. Land as soon as possible.

N = HF transmissions and sunlight filtered

38
Q

Internal Engine Fire

Indication

A
  1. Starter - Engage. Motor engine.

Indication = Rise in TGT above 540 after shutdown

39
Q

APU Fire

1 x N

A
  1. APU T-Handle - Pull.
  2. Confirm fire.
  3. FIRE EXTGH switch - RESERVE (MAIN if required and 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.

N = HF transmissions and sunlight filtered

40
Q

Cockpit Fire/Cabin Fire

4 x W
1 x C
1 x N

A

If source is known:
1. Affected power switches and cbs - OFF/Pull.
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 cbs - OFF/pull.
If fire continues:
5. Land as soon as possible.

W = Severity of fire
W = vapors from fire extinguisher
W = may not be advisable to secure electrical power
W = loss of electrical power, engine anti ice
C = if source unknown, mission power
N = diag page
41
Q

Smoke and Fumes Elimination

A
  1. Airspeed - Adjust, as required.
  2. Doors/windows/vents - Open.
  3. Aircraft - Yaw, as required.
42
Q

Immediate Landing/Ditching

3 x W

A
  1. Crew and passengers - Alert.
  2. Shoulder harness - Locked.
  3. External cargo/stores/fuel - Jettison/dump, as required.
  4. Searchlight - As required.
  5. MAYDAY/IFF - TRANSMIT/EMER.
    Time permitting, consideration should be given to executing APU Emergency Start procedure to maintain electrical and hydraulic power upon rotor disengagement
    In the flare:
  6. Windows - Jettison, as required.
    After landing:
  7. PCLs - OFF
  8. Rotor brake - On.
  9. Copilot collective - Stow.
  10. Pilot HCU - Stow.
    After all violent motion stops:
  11. Egress.
W = stores jettisoned
W = position of emergency jettison window lever
W = failure to remain strapped
43
Q

Underwater Egress

5 x W

A
  1. Emergency breathing device - 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:
  7. Swim clear and inflate LPU.
W = downward stroke of seat
W = do not inflate LPU
W = water pressure
W = failure to disconnect ICS
W = entanglement or disorientation
44
Q

Cargo Hook Emergency Release

1 x W
1 x C

A
  1. Cyclic EMER REL - Press.

W = use of EMER REL may cause injury to crewmembers. Ensure all crewmembers are clear of cargo hook area prior to activating the emergency release button.

C = pressing cyclic EMER REL pushbutton with SONAR, CARGO HOOK, RSQ HOIST, and RAST MASTER on will fire the respective CADs.

45
Q

Dual EGI Failure

1 x W

A
  1. Backup instruments - Scan, as required.
  2. # 1 and #2 EGI PWR switches - OFF, then ON.

W = Altitude changes of +/- 40ft may occur

46
Q

MTS Uncommanded Lasing

A
  1. ACI MASTER ARM - SAFE.
  2. LASER SELECT - SAFE.
    If lasing continues:
  3. FLIR bezel key > +FLIR OFF - Select
47
Q

Hellfire Missile Hangfire

1 x W
1 x C
2 x N

A

If rocket motor ignites and aircraft yaws:
1. Adjust controls as required to maintain straight and level flight.

W = hellfire Missile thermal battery produces voltage up to 30 minutes after squib is automatically fired during launch sequence. Aircraft should remain airborne with missile pointed in a safe direction for a minimum of 30 minutes.
C = personnel shouldn't handle hung ordnance for at least 30minutes after attempted launch
N = normal rocket burn is 3 seconds. Motor failure may cause slow burn or smolder and smoke for longer than 3 seconds.
N = if motor squibs don't fire after 1.5 seconds, the Safe and Arm device will automatically return to Safe position.
48
Q

All Stores Jettison

1 x W
10 x N

A
  1. ALL STORES JETTISON - Press.
W = A PIU fault or failure with stores/ordnance on the corresponding weapons station may result in uncommanded jettison of that station's stores/ordnance
N = total electrical failure, all stores jettison unavailable
N = weight on wheels, all stores jettison unavailable
N = operates regardless of MASTER ARM position
N = pylon loaded weapons are disarmed before jettison
N = aux tanks jettison inhibited when <40 gallons ~272lbs
N = minimum of 1100psi to jettison all sonobuoys
N = does not jettison CMDS stores, only via selective jettison
N = operates normally in SIM mode
N = successful jettison indicated by stores being removed from ORD CTRL page
N = sonobuoy table will not update following jettison

Helicopter Aircraft Commander (12 decks)

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