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IERW TH-67 instruments > 9's > Flashcards

9's Flashcards

1
Q

Immediate Action Emergency Actions

A

NOTE

The urgency of certain emergencies requires immediate and instinctive actions by the pilot. The most important single consideration is helicopter control. All procedures are subordinate to this requirement. If time permits during a critical emergency, transmit MAYDAY call, set transponder to emergency, turn the ELT ON, and lock the shoulder harness.

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2
Q

Land as soon as possible

A

Land without delay to the nearest suitable area (i.e. open field) in which a safe approach and landing is reasonably assured. (The primary consideration is to ensure the survival of the occupants.

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3
Q

Land as soon as practicable

A

The landing site and duration of the flight are at the discretion of the pilot. Extended flight beyond the nearest approved landing area is not recommended. (The primary consideration is the urgency of the emergency.)

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4
Q

Warning definition

A

An operating procedure, practice, etc. which if not correctly followed could result in personal injury or loss of life

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5
Q

Caution definition

A

An operating procedure, practice, etc. which if not strictly observed could result in damage to, or destruction of equipment.

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6
Q

Note definition

A

An operating procedure, condition etc. which is essential to highlight.

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7
Q

“Autorotate”

A
  1. Collective - Adjust as required to maintain rotor RPM (90 - 107%)
  2. “Pedals - Adjust” Crab or slip as required
  3. “Throttle - Adjust as necessary” Close as required
  4. “Airspeed - Adjust” as required
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8
Q

“Emergency Shutdown”

A
  1. “Throttle - Closed”
  2. “Fuel Valve Switch - Off”
  3. “Batt Switch - OFF as desired” Before turning the battery switch off during an in-flight emergency, the pilot should consider a “MAYDAY” call, selecting emergency on the transponder and the possible effects of a total electrical failure.
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9
Q

“Engine Failure at a hover”

A
  1. “Autorotate”
  2. “Emer Shutdown” - Accomplish after landing.
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10
Q

“Engine Failure - Low Altitude/Airspeed or Cruise.”

A
  1. “Autorotate”
  2. “Emer Shutdown” - Accomplish during descent if time permits.
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11
Q

Engine malfunctions

“Engine Restart”

A
  1. “Throttle - Close”
  2. “Fuel Valve Switch - On”
  3. “Attempt start”
  4. “Land as soon as possible”
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12
Q

Engine malfunctions

Engine Restart - CAUTION

A

Do not attempt air start above 12,000 feet MSL (TURB OUT TEMP rises too fast to control).

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13
Q

Engine malfunctions

Engine Restart Considerations

A

After an engine failure in flight, an engine start may be attempted. Because the exact cause of engine failure cannot be determined in flight, the decision to attempt the start will depend on the altitude and time available, rate of desent, potential landing ares and crew assistance available. 52 to 60 KIAS is recommended during the descent. Under ideal conditions, approximately on minute is required to regain powered flight from the time the attempted start is begun. If the decision is made to attempt an in-flight start:

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14
Q

Engine malfunctions

Engine Compressor Stall indications

A
  • Sharp rumble or a series of loud sharp reports
  • Severe engine vibration
  • Rapid rise in TURB OUT TEMP
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15
Q

Engine malfunctions

“Engine Compressor Stall”

A
  1. “Collective - Reduce”
  2. “Engine Anti-ice and Heater switches - OFF”
  3. “Land as soon as possible”
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16
Q

Engine malfunctions

Engine Overspeed indications

A
  • Right yaw
  • Rapid increase in both rotor and engine RPM
  • Increase in engine and rotor noise.
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17
Q

Engine malfunctions

“Engine Overspeed”

A
  1. “Collective - Increase” to load the rotor and sustain engine/rotor RPM below the maximum operating limit.
  2. “Throttle - Adjust” until normal operating RPM is attained.
  3. “Land as soon as possible” Perform a power-on approach and landing by controlling the RPM manually with the throttle.

If RPM cannot be controlled by throttle adjustment.

  1. “Autorotate” when over a safe landing area.
  2. “Emer Shutdown” - Accomplish during descent if time permits.
18
Q

Engine malfunctions

“Engine Underspeed”

A

If an engine underspeed occurs, the collective must be adjusted downward to maintain rotor RPM within limits. If powered flight with rotor in the green can be accomplished:

  1. “Land as soon as possible” in an area that will permit a run-on landing.

An engine underspeed below 90% results in rotor RPM decay below minimum safe limits. Should this occur:
2. Autorotate

  1. Emer Shutdown - Accomplish during the descent if time permits.
19
Q

Engine malfunctions

“Engine Surges”

A

a. GOV INCR switch - INCR for maximum RPM
b. Throttle - Adjust to 97% N2
c. Land as soon as possible

If engine surges are not controlled in steps a. and b. above proceed as follows:

a. Autorotate - When over a safe landing area.
b. Emer Shutdown - Accomplish during descent if time permits.

20
Q

Engine malfunctions

“LOW INLET PRESSURE caution light ON”

A
  1. “ENGINE ALTERNATE AIR SWITCH - OPEN”
  2. “If caution light remains ON, Land As Soon As Possible.”
  3. If caution light goes out, Land As Soon As Practicable. Related engine parameters should be monitored frequently until landing.
21
Q

Engine malfunctions

“Engine Icing”

A

NOTE
When anti-ice system is ON, TOT will rise for same power setting.

  1. “ENGINE ANTI-ICING switch - ON” (if conditions warrant).
  2. “TURB OUT TEMP - Maintain within limits”
22
Q

Engine malfunctions

“If the engine oil pressure is below 50 PSI or the temperature is above 107*C”

A
  1. “Land as soon as possible”

NOTE
If engine oil pressure is falling or low and the oil temperature is rising or high, a severe leak may be present.

23
Q

Engine malfunctions

“Main Drive Shaft Failure”

A

WARNING

The engine must remain in operation to provide power to the tail rotor. Failure to maintain engine power will result in loss of aircraft control. Adjust throttle as required to maintain engine RPM within normal limits.

  1. Autorotate - Establish a Power On autorotation.
  2. Emergency Shutdown - Accomplish after landing.
24
Q

Engine malfunctions

Main Drive Shaft Failure - Indications

A
  • Sudden Increase in engine RPM
  • Decrease in rotor RPM
  • Left yaw
  • Low RPM audio
  • ROTOR RPM caution light.

Transient overspeed of N1 and N2 may occur, but will stabilize.

25
Q

Engine malfunctions

“Clutch failing to disengage”

A
  1. “Throttle - Open”
  2. “Land as soon as possible”
26
Q

Engine malfunctions

Clutch failing to disengage - Indications

A

During Autorotation:

Rotor RPM decays with the engine RPM when throttle set to engine idle.

This condition results in total loss of autorotational capability

27
Q

Engine malfunctions

“Mast Bumping”

A

Land as soon as possible

28
Q

“Loss of T/R Effectiveness”

LTE

A

This is a situation involving a loss of effective tail rotor thrust without a break in the drive system which cannot be stopped with full left pedal application. If LTE is experienced, simultaneously:

  1. “Pedal - Full Left”
  2. “Cyclic - Forward”
  3. As recovery is affected, adjust controls for normal flight.

WARNING
Collective reducion will aid in arresting the yaw rate: however, if a rate of descent has been established, collective reduction may increase the rate of descent to an excessive value. The resultant large and rapid increse in collectiveto prevent ground or obstacle contact may further increse the yaw rate, decreasing the rotor RPM and cause an over torque and/or over-temperature condition. Therefore, the decision to reduce collective must be based on the pilot assesment of the altitude available for recovery.
4. If spinning cannot be stopped and crash is imminent, an autorotaion may be the best course a of action. Maintain full left peddle until spin stops, then adjust to maintain heading.

29
Q

Complete Loss of T/R thrust - Indications

A

a. This situation involves a break in the drive system, such as a severed driveshaft, causing the tail rotor to lose power.
b. Indications:
1. Pedal input has no effect on helicopter trim.

WARNING
Degree of roll and side-slip may be varied by throttle and/or collective. (At airspeeds below approximately 50 knots, the side-slip may become uncontrollable, and the helicopter will begin to spin on the vertical axis.)
2. Nose of the helicopter turns to right (left sideslip)
3. Left roll of fuselage along the longitudinal axis.

30
Q

Complete Loss of T/R thrust - Procedures

A
  1. If Safe landing area is not immediately available, continue powered flight to suitable landing area at or above minimum rate of descent autorotational airspeed.
  2. When landing area is reached, make an autorotational landing (THROTTLE CLOSED).
  3. Use Airspeed above minimum rate of descent airspeed.

NOTE
Airflow around the vertical fin may permit controlled flight at low power levels and sufficient airspeed when a suitable landing site is not available; however, touchdown shall be accomplished with the throttle in the full closed position.
4. If Run-on landing is possible,
* complete autortation with touchdown airspeed as required for directional control.
5. If a run-on landing is not possible,
* start decelerate from about 75 feet altitude, so that forward groundspeed is at a minimum when the helicopter reaches 10 to 20 feet; execute the touchdown with a rapid collective pull just prior to touchdown in a level attitude with minimum ground run.

31
Q

Loss of T/R Components: Indications

A

a. The severity of this situation is dependent upon the amount of weight lost. Any loss of this nature will result in a forward center of gravity shift, requiring aft cyclic. A full autorotational descent and landing should be accomplished with a run-on type termination if to an improved surface, or minimum ground run if to an unimproved surface. Landing should be accomplished in a level attitude.
b. Indications:

  1. Varying degrees of right yaw depending on power applied and airspeed at the time of failure.
  2. Forward CG shift.
32
Q

Loss of T/R Components Procedures

A
  1. Enter autorotative descent _(T_HROTTLE CLOSED)
  2. Maintain Airspeed above minimum rate of descent airspeed.
  3. If Run-on landing is possible,
    • complete autorotation with touchdown airspeed as required for directional control.
  4. If run-on landing is not possible,
    • start to decelerate from about 75 feet altitude, so that forward groundspeed is at a minimum when the helicopter reaches 10 to 20 feet; execute the touchdown with a rapid collective pull just prior to touchdown in a level attitude with minimum ground run.
33
Q

Fixed Pitch Settings

Description

A

This is a malfunction involving a loss of control resulting in a fixed pitch setting. Whether the nose of the helicopter yaws left or right is dependent upon the amount of pedal applied at the time of malfunction. Regardless of pedal setting at the time of malfunction, varying amount of tail rotor thrust will be delivered at all times during flight.

34
Q

Fixed Pitch Settings (Reduced Power Low Torque)

A

Indications:

The nose of the helicopter will turn right when power is applied.

Procedure ch 9:

  1. If helicopter control can be maintained in powered flight the best solution is to maintain control with power and accomplish a run-on landing as soon as practicable. Use airspeed, throttle, and collective to reduce sideslip angle at touchdown.
  2. If helicopter control cannot be maintained close the throttle immediately and accomplish an autorotational landing

Procedure modified by KG:

If helicopter control can be maintained in powered flight,

  • Maintain control with power
  • Run-on landing as soon as practicable.
  • Use Airspeed, Throttle, and Collective to reduce sideslip angle at touchdown.

If helicopter control cannot be maintained,

  • ​​Close the throttle immediately
  • Autorotate
35
Q

Fixed Pitch Settings (Increased Power high Torque)

A

Indications:

The nose of the helicopter will turn left when power is reduced.

Procedures ch 9:

  1. Maintain control with power and airspeed (Between 40 and 70 knots)
  2. Continue powered flight to a suitable landing area where a run-on landing can be accomplished
  3. Execute a run-on landing with power and a touchdown speed which will minimize sideslip. Use throttle and collective, as necessary, to control sideslip and heading at touchdown.

Procedures modified by KG:

  1. Maintain control with power and airspeed 40 and 70 kts
  2. Suitable landing area
  3. Run-on landing with power and a touchdown speed which will minimize sideslip.
  4. Use throttle and collective, as necessary, to control sideslip and heading at touchdown.
36
Q

Fixed Pitch Setting (Hover)

A

Indication:

  • Helicopter heading cannot be controlled with pedals.

Procedures:

  • Fixed pedal - Land.
37
Q

Flight control malfunctions

A

Failure of components within the flight control system may be indicated through varying degrees of feedback, binding, resistance, or slopiness. These conditions should not be mistaken for hydraulic power failure. In the event of a flight control malfunction:

  1. Land as soon as possible.
  2. Emer Shutdown - Accomplish after landing.
38
Q

Un-Commanded flight control input malunction

A

Un-commanded flight control input malfunctions may be indicated throught un-commanded lateral or longitudinal cyclic movements. The magnitude of the event may range from mild to severe. The duration of the event may range from one to several seconds. These conditions should not be mistaken for hydraulic power failure. In the event of an un-commanded flight control input malfunction:

  1. Collective-increse if near the ground to prevent main or tail roto ground contact.
  2. Pedal-apply in the direction of turn.
  3. Direct assistance with flight control inputs to level the aircraft.
  4. Land as soon as possible.
39
Q

Landing in trees

A

A landing in trees should be made when no other landing area is available. In addition to accomplishing engine malfunction emergency procedures, select a landing area containing the least numer of trees of minimum height. Autorotate with the throttle closed using the following procedures:

  1. Airspeed - Minimum at treetop level.
  2. Descend - Vertically into trees
  3. Collective - Apply remaining collective prior to blades entering trees.
40
Q

Ditching - Power off

A

If an engine failure occurs over water and ditching is imminent, accomplish engine failure emergency procedures and proceed as follows:

  1. AUTOROTATE. Decelerate to minimum forward speed as the helicopter nears the water. Apply all remaining collective as the helicopter enters the water. Maintain a level attitude as the helicopter sinks and until it begins to roll, then apply cyclic in the direction of the roll.
  2. Doors - Open
  3. Crew and passengers - Exit when the main rotor stops.
41
Q

“Lightning strike”

A

Land as soon as possible.

Emer Shutdown - Accomplish after landing.

42
Q

Ditching - Power on

A

If ditching becomes necesarry, with power available accomplish an approach to a hover above the water and:

  1. Doors - Open.
  2. Crew (except pilot) and passengers - Exit.
  3. Hover a safe distance away from personnel
  4. Autorotate. Apply all remaining collective as the helicopter enters the water. Maintain a level attitude as the helicopter enters the water. Maintain a level attitude as the helicopter sinks and until it begins to rell, then apply cyclic in direction of the roll.
  5. Pilot - Exit when the main rotor stops.

IERW TH-67 instruments (4 decks)

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