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TH-57 EP/LIM > EP > Flashcards

EP Flashcards

1
Q

T/R Chip

A
  1. Land as soon as possible

W- May result in complete loss of T/R thrust

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2
Q

Electrical Fire - Known Origin

A
  1. Affected Equipment - Secure
  2. Affected Circuit breakers - pull
    If fire persists:
  3. Electrical fire unknown origin procedure - execute
    If fire extinguishes
  4. Land as soon as practicable
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3
Q

Spare Caution

A
  1. Check for other indications

2. Land as soon as possible

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4
Q

Smoke and Fume elimination

A
  1. ECS and DEFOG blower - off
  2. Vents/windows - open
    If smoke/fumes persist:
  3. Slip or skid aircraft to eliminate smoke and fumes
    If source of the smoke and fumes cannot be identified:
  4. Land as soon as possible
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5
Q

Abort Start Conditions

A
  1. Battery voltage stabilized below 17V.
  2. TOT fails to rise after twist grip rotated to flight idle and Ng fails to rise above 20 percent (igniter failure).
  3. TOT rises more slowly than normal and Ng rises slowly and stabilizes (hung start).
  4. TOT exceeds limits and TOT caution light flashes twice per second (hot start).
  5. Engine Oil Pressure remains at 0 PSI.
  6. Rotors not turning by 25 percent Ng.
  7. Transmission Oil Pressure not indicated by 30 percent Nr.
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6
Q

Immediate Landing/Ditching

A
  1. Crew and passengers - Alert
  2. Shoulder Harness - Lock
  3. Mayday - Transmit
  4. Transponder - Emergency
  5. Doors - Open/Jettison - As required
  6. Landing light/Search Light - As required
    When on Deck:
  7. Emergency Shutdown - Complete
    If water landing:
  8. Underwater Egress - Execute
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7
Q

Under speeding Nf/Nr

A
  1. Collective - Lower as require to maintain a minimum of 90%Nr
  2. Twist Grip - Full Open
  3. GOV RPM - Full Increase
    If underspeed persists:
  4. Check Power Available
    If power is not sufficient:
  5. Autorotate
    If power is sufficient:
  6. Land as soon as possible
    W: This emergency may result in engine failure
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8
Q

Battery Hot

A
  1. BAT switch - Off

2. Land as soon as possible

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9
Q

Mast Bumping:

Indication: Sharp two-rev knocking

A

If mast bumping is suspected:
1. Establish positive G load and/or balanced flight (as required)
2. Land Immediately
N - If mast bumping occurs while on deck, maintenance action is required prior to flight.

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10
Q

Engine Failure In Flight

A
  1. Autorotate
  2. Shoulder Harness-Lock
    If time and altitude permit:
  3. Mayday-Transmit
  4. Transponder- Emergency
  5. Engine Restart in Flight EP- As required
    NOTE:
    -Best glide airspeed is 72 KIAS. The minimum rate of decent airspeed is 50 KIAS. Do not exceed 100 KIAS in a sustained Auto.
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11
Q 
Compressor Stall
Indications:
1. Popping, rumbling or loud noises
2. Abnormal Vibrations
3. Rapid rise or fluctuations in TOT
4. Q fluctuations with yaw kicks
5. Ng Fluctuations 
6. Power Loss
A
  1. Collective - Lower
  2. ENG anti-ice switch - On
  3. Cabin heat valve - On
  4. Check power available
    If power is insufficient to maintain level flight:
  5. Autorotate
  6. Twist Grip - Flight Idle
    If power is sufficient to maintain level flight:
  7. Land as soon as possible
    W: This emergency may result in engine failure
    N: Power available is considered sufficient if level flight can be maintained with Nr at 90 percent or higher without re - aggravating the compressor stall.
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12
Q

Pitot Static Instruments malfunction

Airspeed, VSI, or ALT fluctuates or gives false indications while power and attitude are normal.

A 
1. Pitot Heat Switch(es) - Heat
If pitot heat does not remedy the situation, accomplish the following:
2. (C) Alternate source knob - Pull
If icing conditions are present:
3. Icing procedures - execute
If icing conditions are not present:
4. Land as soon as practicable
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13
Q

Complete loss of tail rotor thrust
Indications:
1. Pedal input has no effect on helicopter trim.
2. Right yaw (left sideslip).
3. Left roll of fuselage along the longitudinal axis.
4. Loud bang.

A

In a hover:
1. Twist grip — Flight idle.
2. Cyclic — Eliminate drift.
3. Collective —Increase to cushion landing.
Transition to forward flight or hover/airtaxi:
1. Twist grip — Flight idle.
2. Cyclic — Eliminate sideward drift.
3. Collective —Increase to cushion landing.
At altitude:
4. Autorotate.
If yaw is not controllable:
5. Twist grip —Flight idle immediately.
If yaw is controllable:
6. Continue powered flight and setup to a suitable landing area at or above minimum rate of descent autorotational airspeed.
7. Autorotate
8. Twist Grip - Rotate to flight idle prior to touchdown
W - Autorotation may be the safest option. Attempting to control a loss of tail rotor thrust in powered flight requires considerable skill and may result in loss of aircraft control.

Airspeed indications during side-slip are unreliable. At airspeeds below approximately 50 knots, the side-slip may suddenly become uncontrollable, and the helicopter will begin an unrecoverable vertical axis “flatspin”.

If attempting to achieve higher airspeeds, care must be taken to avoid excessive cyclic inputs coupled with large power settings that could lead to mast bumping or rapid nose tucking.

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14
Q

Transmission Chip

A

First light:
1. Check for secondary indications
If secondary indications exist:
2. Transmission malfunction procedure - perform
If no secondary indications exist:
3. Press clear chip
If light remains:
4. Transmission malfunction procedure - perform
If light extinguishes:
5. Note time and continue flight
Second TRANS CHIP light:
If within 30min of the first:
6. Transmission malfunction procedure - perform
If more than 30 min have elapsed since the first TRANS CHIP light:
7. Proceed as with the first TRANS CHIP Caution light
Any subsequent TRANS CHIP caution light within 50 hours from the first:
8. Transmission Malfunction procedure - perform

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15
Q

Transmission Malfunction

A 
If failure is imminent:
1. Land Immediately 
2. Shoulder Harness - lock
If failure is not imminent:
3. Land as soon as possible
N - Transiting at a minimum power required airspeed and low altitude may permit a quick flare and immediate landing in the event of an imminent transmission failure.

Possible indications of an imminent transmission failure may include yaw attitude excursions with no control input, an increase in power required for a fixed collective setting, increased noise, or increased vibration levels.

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16
Q

Emergency Shutdown

A
  1. Twist Grip - Close
  2. Fuel Valve - Off
  3. BATT Switch - Off
  4. (C) STBY ATT Indicator switch - Off
  5. (C) Rotor Brake - engage immediately
  6. Helicopter - egress, as required. Use fire bottle or get clear of the aircraft as applicable.
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17
Q

Engine or Transmission oil temperature malfunction

A

If engine oil temperature gauge exceeds red line limitation:
1. Land as soon as possible
If transmission oil temperature gauge exceeds red line limitation:
2. Transmission Malfunction Procedure - Perform
If either oil temperature gauge fluctuates or falls to zero:
3. Land as soon as practicable

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18
Q 
Sprag Clutch Slippage:
When twist grip full Open:
1. Nf indication higher than Nr. 
2. Low torque indication.
3. Ng and TOT indication slower than normal and not responsive to collective.
A
  1. Autorotate
  2. Twist Grip - Flight Idle
    If time and altitude permit:
  3. Twist grip - smoothly rotate to full open
    If Nf and Nr are married:
  4. Collective - increase
    If sprag clutch continue to slip:
  5. Autorotate
  6. Twist grip - closed
    If the sprag clutch renegades:
  7. Land as soon as possible
    N - Multiple attempts to reengage are permitted dependent on time and altitude

After completing the landing ensure the twist grip is closed to prevent the sprag clutch from reengaging causing severe damage to the drive system.

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19
Q

Icing

OAT less than 4C and visible moisture

A
  1. Engine Anti-icing - On
  2. Pitot heat switches - On
  3. (C) Alternate Static Source Knob - As required
  4. Descend or climb to warmer temperature or vacate clouds/moisture
    If unable to get clear of icing conditions:
  5. Land as soon as possible
    W - Be prepared for partial or complete power loss
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20
Q

Rotor Blade Stall
Two per rev vibrations
Loss of longitudinal control, severe cyclic feedback
Violent vertical nose oscillations independent of cyclic position

A
  1. Severity of the maneuver - Decrease
  2. Collective - Lower
  3. Airspeed - Decrease
  4. Altitude - Descend, if flight permits
  5. Rotor RPM - Increase

W - Entry into severe blade stall can cause structural damage to the helicopter

21
Q

Torquemeter wet line rupture

Low needle indication and digital readout

A
  1. Monitor Engine Oil Instruments

2. Land as soon as possible

22
Q

Uncommanded Right Roll during Flight Below 1G

A
  1. Cyclic - Immediately apply aft to establish a positive G load on rotor, then center laterally
    When main rotor returns to positive thrust condition:
  2. Controls - as required to regain balanced flight
    If mast bumping has occurred:
  3. Land Immdiately
23
Q

Fuel Control Failure:
Indications:
Erratic Nf/Nr
Fluctuating Ng and or TOT

A
  1. Collective - adjust to maintain Nr within operating range
  2. Twist Grip - adjust to maintain Nf within operating range
  3. Land as soon as possible
    W: This emergency may result in engine failure
24
Q

Pr>Pa

Uncommanded descent with torque at maximum available.
Rotor droop.
Loss of tail rotor authority.

A
  1. Collective - Lower as required to maintain a minimum of 90%Nr
  2. Twist Grip - Full Open
  3. Angle of bank - level wings
  4. Airspeed - 50KIAS (minimum power required airspeed)
  5. Jettison - as required
    If impact is imminent:
  6. Level skids to conform to terrain
  7. Cushion the landing
25
Q 
Engine Fire in Flight
Indications:
Fire light
Flames
Smoke
A 
1. Confirm Existence of Fire
If fire exists:
2. Land Immediately
If fire not confirmed:
3. Land as soon as possible
When on Deck:
4. Emergency Shutdown - Complete
W- This emergency may result in engine failure
26
Q

Engine Restart in Flight

A 
1. Ng - Note
If Ng is below 12%:
2. Twist Grip - Close
3. Starter - On
4. At 12% Ng, Twist Grip - Full Open
If Ng is at or above 12%:
5. Starter - On
If light off occurs:
6. At 58%Ng Starter - Off
7. Land as soon as possible
27
Q

Emergency Descent

A
  1. Collective - Lower (to minimum pitch)
  2. Airspeed - 130 KIAS (122 KIAS max with FCS on)

N- During recovery Nr may tend to Overspeed

28
Q

LTE

A
  1. Pedals - Full Left
  2. Collective - Lower (as altitude permits)
  3. Airspeed - Increase
    If spin cannot be stopped:
  4. Autorotate
29
Q

Hydraulic Power Cylinder Malfunction

A
  1. HYDRAULIC BOOST switch - Off
  2. Helicopter - regain control
  3. Airspeed - Adjust (to obtain the most comfortable control movement level)
  4. Land as soon as possible
    W - Hydraulic system will not secure if HYD BOOST circuit breaker is out and the pilot will be unable to maintain control of the aircraft.
30
Q

Dynamic Rollover

A
  1. Collective - lower to stop the roll

2. Cyclic - Neutral

31
Q

Abort Start

A
  1. Twist grip - close
  2. Starter - off after TOT stabilizes at 400 C or below
    C - Failure to utilize a GPU/battery cart on subsequent start attempts may result in hot start.
32
Q

Fixed Pitch in a Hover

A

Fixed Pitch Pedal in a Hover — Right Yaw: If rate of rotation is not excessive and landing surface is smooth and firm:
1. Collective — Decrease to effect a power - on landing.
If rate of rotation is excessive or landing surface is unsuitable for a power - on landing:
2. Twist grip — Reduce as nose approaches windline.
3. Cyclic — Eliminate drift.
4. Collective — Increase to cushion landing.
Fixed Pitch Pedal in a Hover — Left Yaw:
If rate of rotation is not excessive and landing surface is smooth and firm:
1. Collective – Decrease to affect a power - on landing.
If rate of rotation is excessive or landing surface is unsuitable for a power - on landing:
2. Smoothly increase collective to stop the left yaw.
3. When the left yaw has stopped, smoothly decrease collective to setup for a landing.
N - Steps 2 and 3 may need to be repeated until an acceptable yaw has been established for landing

Twist grip manipulation may be required to aid recovery

  1. Eliminate lateral drift with cyclic as the aircraft settles.
  2. Continue to smoothly lower collective once on deck to control yaw and transfer aircraft weight to the skids.
33
Q

Fuselage Fire

A
  1. Land Immediately
    When on deck:
  2. Emergency Shutdown - Complete
    W - Fire extinguisher fumes are dangerous. The TH-57 with doors and windows open is considered a well ventilated are.
    N - Sideslip may be desired to keep the fire from spreading.
34
Q

High Frequency Vibrations

A
  1. ECS - Off
    If vibrations continue:
  2. Land as soon as possible
    W - May result in loss of T/R Thrust

Maintain auto profile or low powered landing (sliding)

35
Q

Post Shutdown Fire Internal
TOT rises above 400C
Flames or smoke coming from the engine

A
  1. Starter - Engage
  2. Fuel Valve - Off
  3. Igniter CB - pull
  4. Starter - secure after fire is extinguished
36
Q

Engine Chip

A 
1. Check for secondary indications
If secondary indications exist:
2. Land as soon as possible
If no secondary indications exist proceed as follows:
3. Press Chip Clear
If ENG Chip remains:
4. Land as soon as possible
If ENG Chip extinguishes:
5. Note time and continue flight
Second Chip Light
If within 30 min from the first:
6. Land as soon as possible
If more than 30 min have elapsed since the first light:
7. Proceed as with the first light
Any subsequent Chip caution light within 50 hours from the first:
8. Land as soon as possible
37
Q 
Electrical Fire - Unknown Origin
Smoke
Fumes
Sparks
Loadmeter shows excessive loads
DC voltmeter shows a decrease in voltage
A
  1. Battery Switch - Off
  2. (C) STBY GEN switch - Off
  3. (C) If in VMC, STBY ATT IND Switch - Off
  4. Main Gen Switch - Off
    If fire persists:
  5. Land Immediately
  6. Emergency Shutdown - Complete
    If fire extinguishes:
  7. Land as soon as possible

(C) Voltmeter select switch may aide in identifying the location of the fire.

38
Q 
Main Driveshaft Fail
Indications:
1. Nr decrease.
2. Nf indication highert han Nr. 
3. Left yaw.
4.Loud bang/sound of overspeeding engine.
5.Low torque.
A
  1. Autorotate
  2. Twist Grip - adjust if necessary to maintain Nf in operating range
    When on Deck:
  3. Emergency Shutdown - Complete
    W: The engine must continue to operate to provide tail rotor drive. Tail rotor authority may be lost if Nf is allowed to go below 80 percent.
39
Q

Engine or Transmission oil Pressures

A

If engine oil pressure is exhibiting abnormal indications:
1. Land as soon as possible
If transmission oil pressure is exhibiting abnormal indications:
2. Transmission malfunction procedure - Perform

The engine SHALL be shutdown if transmission oil pressure exceeds 70psi or engine oil pressure exceeds 150psi on deck.

W - excessive power changes may expedite engine or transmission failure

40
Q

Engine Failure at high speed low altitude

A
  1. Cyclic - Immediately Apply Aft
  2. Autorotate
    W: Rapid Cyclic movement may cause mast bumping
41
Q

Underwater Egress

A
  1. SEBD - Don, As required
  2. Communication cords - Disconnect
  3. Doors - Open/Jettison
  4. Place hand on known reference point
    When all violent motion stops:
  5. Shoulder harness/lap belt - release
  6. Exit Helicopter
    After Egress:
  7. Swim clear and inflate LPU
42
Q

Fuel Boost Pump Failure

A
  1. Decent - Initiate if above 6,000’PA and flight permits
  2. Fuel pressure and quantity - note
    If both fuel pumps fail or single pump failure below 20gal remaining
  3. Land as soon as possible
43
Q

Over torque/Overtemp/Overspeed

A

If Q>120%: Land as soon as possible
If Q<=120%: Land as soon as practicable
If TOT is exceeded: Land as soon as possible
If Ng/Nf/Nr are exceeded: Land as soon as possible

44
Q

Suspected Fuel Leakage

A 
1. Land as soon as possible
If time and altitude permits:
2. Transmit position and intentions
3. Unnecessary electrical equipment - secure 
When on deck
4. Emergency Shutdown - Complete
45
Q

Battery Temperature Caution

A
  1. BAT Switch - Off

2. Flight may be continued

46
Q 
Vortex Ring State
Rates of descent greater than 800 fpm at airspeeds less than 40KIAS.
High,steep,and/or downwind approaches. 
Indications:
1. Rapid descent rate increase.
2. Pitch and roll oscillations.
3. Increase in overall vibration level.
4. Loss of control effectiveness.
A
  1. Controls - as required to clear VRS
    If impact is imminent:
  2. Level skids to conform to terrain
47
Q

Engine Overspeed

A
  1. Twist Grip - Reduce (to maintain Nf/Nr in operating range)
  2. Collective/Twist Grip - Coordinate
  3. Land as soon as possible
48
Q

Airframe Fuel Filter Caution

A
  1. Land as soon as possible

TH-57 EP/LIM (2 decks)

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