EMERGENCIES - NATOPS CH. 12

Question 1

What five things should be performed for all emergencies?

Answer 1

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.

Question 2

In what steps of EMIF are you increasing power available?

Answer 2

Turning contingency power on and anti ice off

Question 3

In what step of EMIF are you reducing power required?

Answer 3

External cargo/stores/fuel jettison/dump

Question 4

What are the two types of high side failures?

Answer 4

EDECU and HMU

Question 5

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

Answer 5

Ng

Question 6

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

Answer 6

96%

Question 7

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

Answer 7

Water contaminated fuel

Question 8

How does an impending high speed shaft failure manifest?

Answer 8

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

Question 9

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 _____.

Answer 9

20%

Question 10

1/#2 DRVSHAFT FAIL Caution

Answer 10

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

Question 11

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

Answer 11

Maximum

Question 12

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.

Answer 12

Down trimming

Question 13

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.

Answer 13

Minimum

LOCKOUT

Question 14

LDS: PCLs in IDLE

Answer 14

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

Question 15

LDS: During rotor engagement

Answer 15

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

Question 16

LDS: PCLs in FLY on deck

Answer 16

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

Question 17

LDS: Collective increases (below 75%)

Answer 17

Torque of failed LDS will lag

Question 18

LDS: Collective increases (above 75%)

Answer 18

No split

Question 19

LDS: Collective decreases (below 75%)

Answer 19

Torque will lag

Question 20

LDS: Autorotation

Answer 20

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

Question 21

LDS Warning

Answer 21

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

Question 22

1/#2 ENG HOT

Answer 22

TGT > 949

Question 23

1#2 ENG OIL HOT

Answer 23

Oil temp > 150

Caution triggered by VIDS so can not be used as secondary

Question 24

1#2 ENG OIL PRESS HI

Answer 24

Oil px > 120

Caution triggered by VIDS so can not be used as secondary

Question 25

#1/#2 ENG OIL PRESS LOW

Answer 25

Ng > 70% and engine oil < 26psi Engine oil < 22 psi

Question 26

Reasons to Abort Start

Answer 26

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

Question 27

When does ENG OUT warning appear?

Answer 27

Ng < 55%

Question 28

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 ________ _______.

Answer 28

Ng Ignition exciter

Question 29

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

Answer 29

Variable Geometry

Question 30

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.

Answer 30

3 Reaching PCLs

Question 31

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.

Answer 31

Damper

Question 32

What airspeed will minimize abnormal vibrations in flight?

Answer 32

80 KIAS

Question 33

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

Answer 33

Blade de-ice power on

Question 34

When does LOW ROTOR RPM come on?

Answer 34

Nr < 96%

Question 35

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.

Answer 35

5

Question 36

When does the ROTOR BRAKE caution come on?

Answer 36

Hydraulic pressure greater than 6-8 psi

Question 37

ROTOR SPEED HIGH

Answer 37

Nr > 120%

Question 38

What five micro switches lead to a SPREAD light?

Answer 38

Two on folding part of pylon (5 degree switch and the one on the starboard side) Two stabilator lock pins Tail rotor indexer retracted

Question 39

What are the two categories of transmission malfunctions?

Answer 39

Chip or lubrication

Question 40

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

Answer 40

Reducing the load on that particular module. e.g. PCL to IDLE, secure a generator, secure both generators once APU generator is up, etc

Question 41

What does a low but steady transmission oil pressure indicate?

Answer 41

A single pump failure

Question 42

What does a continually leaking transmission oil pressure indicate?

Answer 42

A leak

Question 43

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

Answer 43

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

Question 44

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.

Answer 44

Tail drive pinion 8 minutes

Question 45

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

Answer 45

1 minute

Question 46

Indications of an Imminent Transmission Failure

Answer 46

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

Question 47

Indications of an imminent tail rotor failure

Answer 47

Strong medium frequency vibrations Hot metal fumes Any other associated indication

Question 48

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

Answer 48

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.

Question 49

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

Answer 49

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).

Question 50

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

Answer 50

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

Question 51

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

Answer 51

Control cable failure Servo failure Restricted flight controls

Question 52

What occurs when both tail rotor cables fail?

Answer 52

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.

Question 53

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

Answer 53

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

Question 54

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

Answer 54

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.

Question 55

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

Answer 55

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

Question 56

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?

Answer 56

Apply opposite pedal firmly and then turn off the trim.

Question 57

How will a fixed pitch right pedal landing look?

Answer 57

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

Question 58

How will a fixed pitch left pedal landing look?

Answer 58

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

Question 59

How do you do a controllability check?

Answer 59

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.