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Buns HAC Study > EMERGENCIES - NATOPS CH. 12 > Flashcards

EMERGENCIES - NATOPS CH. 12 Flashcards

1
Q

What five things should be performed for all emergencies?

A
  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.
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2
Q

In what steps of EMIF are you increasing power available?

A

Step 2. CONTGCY PWR switch - ON.
Step 4. ENG ANTI-ICE switches — OFF.

4. ENG ANTI-ICE switches — As required.

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3
Q

In what step of EMIF are you reducing power required?

A

Step 5. External cargo/stores/fuel —
JETTISON/DUMP

5. External cargo/stores/fuel —
Jettison/dump, as required.

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4
Q

What are the two types of Engine High-Side Failures?

A
  1. EDECU driven High Side Failure.
  2. HMU driven High-Side Failure.
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5
Q

____ does not pass through the EDECU and is a highly reliable signal.

A

Ng

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6
Q

ENG SPEED LOW will display when Np is at or below _____ for greater than 2.0 seconds.

A

96%

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7
Q

Fluctuations of the Nr, torque, Ng, and the other engine instruments on either or both engines, may be indicative of ______ __________ _____.

A

Water contaminated fuel

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8
Q

How might an impending Engine High-Speed Shaft Failure manifest?

A

As high intensity, medium to high frequency vibration accompanied by a howl.

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9
Q

The engine Np sensor is unreliable with Np less than ____. For this reason, any (#1/#2) DRVSHAFT FAIL caution should be acknowledged and ignored when engine Np is less than ____. ____ maintenance action is required when in
this condition.

A

20%, 20%, No

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10
Q

When will the #1/#2 DRVSHAFT FAIL Caution illuminate?

A

When Np is greater than Nr by more than 3% and engine torque is below 10%.

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11
Q

A LDS roll-pin failure will result in the ________ LDS input to the HMU, regardless of collective
position.

A

Maximum

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12
Q

LDS roll-pin failure may result in excess power driving the main rotor during an authoritative descent because the EDECU will not have enough ____________ authority to reduce torque to zero.

A

Down-trimming

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13
Q

A ____ or ____ cable may result in ____ LDS input to the HMU regardless of collective position. This condition may restrict maximum power available from the affected engine. Operation in ____ will not clear this low-power condition.

A

Jammed, stuck, minimum, LOCKOUT

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14
Q

How will an LDS Malfunction manifest while on deck with PCLs in IDLE?

A

Ng of malfunctioning engine will read 3% - 4% higher than other engine.

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15
Q

How will an LDS Malfunction manifest during rotor engagement?

A

As a torque split, the affected engine will indicate a higher torque as PCLs are evenly advanced to FLY. The good engine may not indicate any torque until its PCL is in FLY.

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16
Q

How will and LDS Malfunction manifest while on deck with PCLs in FLY?

A

Indications may range from matched torque with Np/Nr matched at 100%, to a possible 1-2% torque split with Nr and Nps matched within 2% above 100%.

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17
Q

How will an LDS Malfunction manifest in flight while increasing collective (collective position < 75%)?

A

As a torque split, the affected engine torque will be lower than good engine.

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18
Q

How will an LDS Malfunction manifest in flight when increasing collective (collective position > 75%)?

A

There will be no torque split because both LDS are at their maximum setting.

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19
Q

How will an LDS Malfunction manifest in flight when decreasing collective (collective position < 75%)?

A

As a torque split, the torque of the affected engine will be above the good engine.

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20
Q

How will an LDS Malfunction manifest during an autorotation?

A

As a rapid rise in Np/Nr. The affected engine may show a residual torque of approx 12% with collective full down.

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21
Q

What is the WARNING for the Load Demand System Failure EP?

A

During low-power or autorotative descents with an engine LDS malfunction, Np/Nr may rise rapidly and activate Np overspeed protection (120%).

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22
Q

When will the #1/#2 ENG HOT Caution display?

A

When Engine TGT is above 949 °C.

The engine oil pressure and temperature
cautions are triggered by the vertical
instrument. Therefore, cautions and
gauge indications cannot be used as
secondary indications for each other.

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23
Q

When will the #1#2 ENG OIL HOT Caution illuminate?

A

When engine oil temperature is above 150 °C.

The engine oil pressure and temperature
cautions are triggered by the vertical
instrument. Therefore, cautions and
gauge indications cannot be used as
secondary indications for each other.

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24
Q

When will the #1#2 ENG OIL PRESS HI Caution illuminate?

A

When Engine oil pressure is at or above 120 psi.

The engine oil pressure and temperature
cautions are triggered by the vertical
instrument. Therefore, cautions and
gauge indications cannot be used as
secondary indications for each other.

25
Q

When will the #1/#2 ENG OIL PRESS LOW Caution illuminate?

A

Either of the following:

  1. Ng is above 70% and engine oil pressure is below 26 psi.
  2. Engine oil pressure is below 22 psi.

The engine oil pressure and temperature
cautions are triggered by the vertical
instruments. Therefore, cautions and
gauge indications cannot be used as
secondary indications for each other.

26
Q

What are the 5 reasons to abort an engine start?

A
  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.
27
Q

When will the (#1/#2) ENG OUT Caution illuminate?

A

When Ng decreases below 55%.

Also, during an isolated Ng signal failure; in which case, the ENG OUT caution will be illuminated while the engine is operating normally.

28
Q

NOTE
In the event of an alternator failure, the ____ signal may be unavailable. Engine start will not be possible without ac power provided to the ________ _______.

A

Ng

Ignition exciter

29
Q

The temporary hang up of the engine ________ ________ system at the engine anti-ice/start bleed valve may cause engine flameout at low collective settings.

A

Variable Geometry (VG)

30
Q

Ground resonance can occur rapidly (within ____ seconds), and produce violent vibrations resulting in difficulty ____ ____ and pilot-induced oscillations. Vibrations can grow severe enough to result in ____ ____ of rotor blades and potential ____ ____.

A

Three, reaching PCLs, dynamic departure, dynamic rollover.

31
Q

Any break in the ____ ____ ____ hydraulic system (e.g., a ruptured damper hose) will instantaneously ____ ____ ____, resulting in a total loss of damping to all four main rotor blades, and may result in ____ ____.

A

Main rotor damper, deplete the reservoir, ground resonance.

32
Q

What airspeed will typically minimize abnormal vibrations in flight?

A

80 KIAS

33
Q

While operating in cold weather,
turning the ____ ____ ____ switch to ON activates the droop-stop ____ which will aid
the droop stops in ____.

A

BLADE DEICE POWER, heaters, seating.

34
Q

When does LOW ROTOR RPM come on?

A

When Nr is < 96%.

35
Q

Failure to hold the gust lock switch in the LKD or UNLK position for a minimum of ____ seconds during operation may result in a partially engaged gust lock without a gust lock caution, causing damage when the rotor is engaged.

A

5

36
Q

When does the ROTOR BRAKE caution come on?

A

Hydraulic pressure greater than 6-8 psi

37
Q

ROTOR SPEED HIGH

A

Nr > 120%

38
Q

What five micro switches lead to a SPREAD light?

A

Two on folding part of pylon (5 degree switch and the one on the starboard side)

Two stabilator lock pins

Tail rotor indexer retracted

39
Q

What are the two categories of transmission malfunctions?

A

Chip or lubrication

40
Q

If a chip is present in a module what should you consider?

A

Reducing the load on that particular module.

e.g. PCL to IDLE, secure a generator, secure both generators once APU generator is up, etc

41
Q

What does a low but steady transmission oil pressure indicate?

A

A single pump failure

42
Q

What does a continually leaking transmission oil pressure indicate?

A

A leak

43
Q

What do you lost once oil is depleted and pressure has dropped?

A

No oil to the temperature sensors or chip detectors so those sensors will not indicate properly.

44
Q

Previous events of a complete loss of lubrication in main gearbox have shown that the ______ ______ ______ will likely fail first, resulting in a loss of tail rotor drive in as little as _____ minutes.

A

Tail drive pinion

8 minutes

45
Q

Drive failures were proceeded by a dramatic increase in vibrations/noise approximately _____ minute(s) prior to failure.

A

1 minute

46
Q

Indications of an Imminent Transmission Failure

A

Yaw attitude excursions with no control input

Increased power required for a fixed collective setting

Failure of a main gen or hyd pump

Increased noise

Increased vibrations

Abnormal fumes in the cockpit

47
Q

Indications of an imminent tail rotor failure

A

Strong medium frequency vibrations

Hot metal fumes

Any other associated indication

48
Q

What is the hazard in delaying autorotation with a loss of tail rotor drive?

A

Large sideslip angles can develop, causing low indicated airspeed which then will cause the stab to program down. Then making it difficult to establish and maintain auto rotational airspeed.

49
Q

How do you check for tail rotor control in the AUTO, AUTO, AUTO procedure?

A

The application of slight right pedal should reveal the tendency to yaw with a functioning tail rotor.

This should not be confused with the pitching moment created by the mixing unit (yaw to longitudinal).

50
Q

In an autorotation with both engines secured, the cushioning collective pull at the bottom will result in yaw in which direction?

A

Left yaw, vice the right yaw associated with practice (power on) autorotations.

51
Q

What are the three types of loss of tail rotor control malfunctions?

A

Control cable failure

Servo failure

Restricted flight controls

52
Q

What occurs when both tail rotor cables fail?

A

Tail rotor will assume a preset spring loaded position where at 19,500 lb gross weight, balanced flight will occur at 25 KIAS and 145 KIAS.

53
Q

Where does the remaining tail rotor control come from with a servo failure (loss of #1 pump and backup pump)?

A

Yaw boost servo is still pressurized and normal yaw control is available between 40-120 KIAS.

54
Q

What it’s important to note about the tail rotor cables in a servo failure?

A

Elongation and/or failure of the tail rotor cables may occur if there is no yaw response with pedal inputs. If airspeed decreases below 40 KIAS, a lot of tail rotor control will likely occur.

55
Q

What type of landing is recommended for a servo failure? Can you reduce collective after touchdown?

A

A roll on landing above 40 KIAS. Yes, once on deck and torque is reduced, yaw control should be regained.

56
Q

How do you overcome a yaw trim malfunction, induced by the AFCS, producing up to 30 lb of force at the pedal? Or a jammed yaw trim actuator producing up to 80 lb of force?

A

Apply opposite pedal firmly and then turn off the trim.

57
Q

How will a fixed pitch right pedal landing look?

A

May need a minimum power required run on landing, perhaps as high as the minimum power required airspeed (70 KIAS)

58
Q

How will a fixed pitch left pedal landing look?

A

Allows for slower airspeeds or even a normal approach to a hover, but may require dropping PCLs depending on severity of stuck left.

59
Q

How do you do a controllability check?

A

Establish level flight, reduce airspeed to bring the nose back to the left, note airspeed which the nose is centered (ball centered) and starts to yaw right.

Slowly decrease collective and increase airspeed to maintain wave off capability and bring nose back to the left.

Buns HAC Study (24 decks)

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