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HAC > EMERGENCIES - NATOPS CH. 12 > Flashcards

EMERGENCIES - NATOPS CH. 12 Flashcards

1
Q

What five things should be performed for all emergencies?

A

Maintain aircraft control.
Alert the crew.
Determine the precise nature of the problem.
Complete the applicable emergency procedure or take action appropriate for the problem.
Determine landing criteria and land as required.

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2
Q

In what steps of EMIF are you increasing power available?

A

Turning contingency power on and anti ice off

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3
Q

In what step of EMIF are you reducing power required?

A

External cargo/stores/fuel jettison/dump

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4
Q

What are the two types of high side failures?

A

EDECU and HMU

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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, and 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 does an impending high speed shaft failure manifest?

A

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 _____.

A

20%

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10
Q

1/#2 DRVSHAFT FAIL Caution

A

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

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11
Q

An 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

This condition (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 jammed or stuck cable (LDS) may result in _______ LDS input to the HMU regardless of collective position. Operation in ________ will not clear this low power condition.

A

Minimum

LOCKOUT

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14
Q

LDS: PCLs in IDLE

A

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

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15
Q

LDS: During rotor engagement

A

Failed LDS will indicate higher torque as PCLs are advanced to fly.

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16
Q

LDS: PCLs in FLY on deck

A

Possible 1-2% torque split with Nr and both Nps matched 101-102%

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17
Q

LDS: Collective increases (below 75%)

A

Torque of failed LDS will lag

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18
Q

LDS: Collective increases (above 75%)

A

No split

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19
Q

LDS: Collective decreases (below 75%)

A

Torque will lag

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20
Q

LDS: Autorotation

A

Rapid Np/Nr rise. Failed LDS may show residual torque up to 12%

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21
Q

LDS Warning

A

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

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22
Q

1/#2 ENG HOT

A

TGT > 949

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23
Q

1#2 ENG OIL HOT

A

Oil temp > 150

Caution triggered by VIDS so can not be used as secondary

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24
Q

1#2 ENG OIL PRESS HI

A

Oil px > 120

Caution triggered by VIDS so can not be used as secondary

25
Q

1/#2 ENG OIL PRESS LOW

A

Ng > 70% and engine oil < 26psi

Engine oil < 22 psi

26
Q

Reasons to Abort Start

A

Ng doesn’t reach 14% within 6 seconds of starter initiation

No oil px within 30 sec of starter

No light off within 30 seconds of IDLE

ENG STARTER advisory disappears before 52% Ng

TGT likely to exceed 851 before idle speed is attained

27
Q

When does ENG OUT warning appear?

A

Ng < 55%

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

30
Q

Ground resonance may occur rapidly (within ____ seconds) and produce violent lateral, vertical, and circular vibrations resulting in difficulty ________ ______, pilot induced oscillations, and possible dynamic rollover.

A

3

Reaching PCLs

31
Q

A sheared _______ hydraulic line will instantaneously deplete the reservoir, degrading all four main rotor dampers and may result in ground resonance or unusual vibrations on deck.

A

Damper

32
Q

What airspeed will minimize abnormal vibrations in flight?

A

80 KIAS

33
Q

In cold weather, what can aid in droop stops seating?

A

Blade de-ice power on

34
Q

When does LOW ROTOR RPM come on?

A

Nr < 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.

HAC (24 decks)

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