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HAC > NATOPS Lists > Flashcards

NATOPS Lists Flashcards

1
Q

Primary Missions

A

SUW
ASW
EW
CC
NCO

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2
Q

Secondary Missions

A

AMW
AW
HS
FS-O
INT
LOG
NSW

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3
Q

30% of airflow is used for combustion, the rest is used for:

A

Inlet temperature (T2)
Discharge pressure (P3)
Combustion and turbine cooling
Oil seal pressurization

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4
Q

Fuel is tapped off of the HMU for:

A

Metering valve
Variable geometry vane servo
Amplify T2, P3, Ng signals

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5
Q

PAS sets max available Ng for:

A

Fail safe to high power
Power available with OEI

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6
Q

Functions of the HMU

A

Rapid engine transient response through collective compensation

Auto fuel scheduling for start

Ng overspeed protection at 110 +- 2

Flameout and compressor stall protection

Acceleration limiting

Ng governing

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7
Q

Functions of the ODV

A

Trap fuel upstream so priming isn’t required

Return fuel back to HMU in Np overspeed or hot start

Injectors - provide fuel to 12 injectors

Purge fuel overboard after shutdown to prevent coking of injectors

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8
Q

EDECU Functions

A

Np governing
Np overspeed protection
Np overspeed test
Ng decay rate relight
Contingency Power (auto, man, dual)
Hot start prevention
Engine speed trim
Fault diagnostics
TDI
Auto ignition
Signals
TGT limiting
Engine load sharing
DECU lockout

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9
Q

Three ways to anti-ice the engine

A

Vent bleed air into engine swirl vanes and IGV

Vent bleed air into airframe engine inlet

Pump hot oil through scroll vanes

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10
Q

Three ways to determine a malfunctioning anti-ice/start valve

A

Appearance of ANTI-ICE on outside of the ranges in the associated chart

No appearance of anti-ice on when switch is on

No rise in TGT when anti-ice is on

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11
Q

Three pigs

A

Backup hydraulic pump (No. 1 AC Pri)

Mission avionics system (No. 1 AC Secondary (TR DE-ICE also)

Main rotor de-ice (AC Monitor)

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12
Q

GCU Protection

A

Over voltage, under voltage, feeder faults, under frequency

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13
Q

Battery Analyzer/Conditioner Functions

A

Fault conditions, battery charge, internal temperature, cell conditions, battery charging capability

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14
Q

4 Reasons for Auto Backup Hyd Pump

A

1 HYD PUMP

#2 HYD PUMP
#1 RSVR LOW
#1 TAIL ROTOR SERVO

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15
Q

5 things required for a Hyd Leak Test

A

W - WOW
A - AC Power
A - Backup Hyd pump in AUTO
A - All reservoirs full
R - Rotors engaged

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16
Q

Hyd Leak Test Lights

A

1 RSVR LOW

#2 RSVR LOW
BACK UP RSVR LOW
SAS
BOOST
AFCS DEGRADED
#1 TAIL ROTOR SERVO
#2 TAIL ROTOR SERVO ON
BACK UP PUMP ON
MASTER CAUTION

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17
Q

Functions of the AFCS System

A

5 holds - Airspeed, RADALT, BARALT, pitch and roll attitude, heading

4 hovers (plus auto depart) - auto approach, coupled hover, cable angle hover, crew hover, auto depart

3 stabs - stability augmentation, stabilator control, maneuvering stability

Blade fold
Auto preflight check
Diagnostics
Turn coordination
Gust alleviation/hover augmentation
Trim

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18
Q

Mixing Unit Functions

A

Collective to Yaw
Collective to Lateral
Collective to Longitudinal
Yaw to Longitudinal
Collective/airspeed to yaw

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19
Q

4 inputs to the Stab

A

Collective position
Lateral acceleration
Airspeed
Pitch rate

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20
Q

Requirements for Cable Angle Hover

A

Ground speed less than 5 knots
RADALT within 10 feet
AFCS Degraded not illuminated
AUTO PLT engaged
Dome wet
DPRT or crew hover not engaged

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21
Q

5 things required for Automatic Preflight Checks

A

Both EGIs
Rotor brake on
Engine torques below 10%
WOW
SAS 1 engaged

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22
Q

In what order does ALL STORES JETT work

A

Sonobuoys
LIB
RIB
LOB
ROB

INOP WITH A COMPLETE ELECTRICAL FAILURE

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23
Q

Automatic ADHEELS Activation

A

Fresh or saltwater immersion
Impact of 11-13 Gs or greater
Attitude changes of 100+-5 or greater in pitch or roll

24
Q

IHEELS Automatic Activation

A

Fresh or saltwater immersion
Attitude changes of 100+-5 in pitch or roll

25
Q

What are the four operational restrictions for JP-4/JET B?

A

All takeoffs shall stabilize in a hover with no fuel px cautions for a minimum of 10 seconds

Single engine training is prohibited

Operating characteristics may change

Next two refuelings shall be treated as if JP-4/JET B is still present

26
Q

Primary Fuels

A

JP-5
JP-8
F-24
TS-1

27
Q

Restricted Fuels

A

JET A
JET A1
JET B
JP-4

28
Q

Emergency Fuels

A

JP8+100
F-27

29
Q

Five reasons to abort start

A

Ng doesn’t reach 14% within 6 sec

No oil px within 30 seconds of starter initiation

No light off within 30 seconds of IDLE

ENG STARTER dropout before 52% Ng

TGT likely to exceed 851 before idle speed attained

30
Q

Four Types of Approaches to a Ship

A

Visual
Instrument
ELVA
Offset or Ordnance Approach

31
Q

Cable Angle Hover Corrective Action Techniques

A

Cyclic 4-way trim
Fly against lateral trim
Using trim release, reposition the aircraft
Fly against longitudinal trim

32
Q

Five Rescue/Recovery Methods

A

Landing to effect a rescue
Rescue via one or two wheels
Rescue via hoist
Rappelling
Direct deployment

33
Q

How to get out of retreating blade stall

A

Severity of maneuever - decrease
Collective pitch - decrease
Airspeed - decrease
Altitude - decrease
Rotor RPM - increase
Gross Weight - decrease

34
Q

LTE Effects

A

AOA Reduction - 060-120
Weather Vaning - 120-240
TR VRS - 210-330
ME Disc Vortex - 280-330

35
Q

Vortex Ring State Requirements

A

Rate of descent > 700 fpm

0-20 KIAS

Worse at > 1500 fpm

5-10 KIAS

36
Q

Recovery from VRS

A

Decrease collective pitch

Increase airspeed

Enter autorotation if altitude permits

37
Q

Five thing that should be performed for all aircraft emergencies (MADCD)

A

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

38
Q

High Side Failure Conditions

A

TRQ is 10% or greater then other engine
Ng is 5% or greater than other engine
Np is matched within 5%
Nr is at or above 103%

39
Q

Low Side Failure Conditions

A

TRQ is 10% below the good engine
Ng is 5% or less than good engine
Np is at or below 98%
Nr is at or below 97%

40
Q

High Speed Shaft Failure Conditions

A

Np is greater than Nr by more than 3%
Engine TRQ is less than 10%

41
Q

Indications of Main Trans Imminent Failure

A

Yaw attitude excursions with no control input

Increased power required for a fixed collective setting

Failure of main gen or hyd pump

Increased noise

Increased vibrations

Abnormal fumes

42
Q

Indications of Tail/Int Gearbox Imminent Failure

A

Strong medium frequency vibrations

Hot metal fumes

Any other associated indication

43
Q

Three Types of Tail Rotor Malfunctions

A

Control cable failure

Servo failure

Restricted flight controls

44
Q

With the stab in manual mode, the following are not recommended:

A

Swimmer deployments lower than 15’

Night takeoffs, approaches, landings (except one time landing following failure)

Automatic approaches to a hover

Simulated EPs

Flight in known IMC

45
Q

Three things to be performed for every sonar emergency

A

Alert crew.

Execute Reeling Machine Malfunction EP.

Complete the Sonar Troubleshooting Checklist.

46
Q

Five Sections of the Engine

A

Inlet, Compressor, Combustor, Turbine, Exhaust

47
Q

Flow of Air through Engine

A

Inlet cowling, inlet fairing, swirl vanes, IPS, collection scroll (dumped overboard by blower assembly), scroll vanes, de swirl vanes, compressor.

48
Q

What does the Ng turbine drive?

A

Compressor

AGB

49
Q

What do you lose and retain in LOCKOUT?

A

Lose: TGT limiting, load sharing, Np governing.

Retain: Np overspeed.

50
Q

Two functions of the engine driven fuel boost pump

A

Provide reliable suction feed from fuel tank to the engine

Provide discharge px to satisfy minimum inlet px of HMU

51
Q

Three control parameters of EDECU

A

Np sensing

Np overspeed and torque sensing

TGT monitoring

52
Q

Inputs the EDECU Receives

A

ENG SPEED TRIM

CONT PWR

ENG OVERSPEED A AND B

53
Q

EDECU sends these signals to cockpit

A

TRQ

Np

TGT

CONT PWR

54
Q

What three things get power from the alternator?

A

AC power to igniter assembly, EDECU, and Ng signal to VIDS

55
Q

Three factors that must be present to enter into Ground Resonance

A
  1. Total loss of hydraulic pressure to the main rotor damper system
  2. Lateral disturbance of main rotor head on deck or upon landing
  3. Convergence of fuselage roll frequency and main rotor lag frequency
56
Q

When de-ice manual mode should be used?

A
  1. The pilot has determined by judgement of icing intensity that the icing rate system is inaccurate.
  2. Torque required has increased to an unacceptable level.
  3. Helicopter vibration has increased to an unacceptable level.
57
Q

What are the assumptions when calculating FlyAway Torque?

A

1.5 sec reaction time from first torque split
C-Power on
70ft AGL min hover
Nr maintained between 96-100%
Satisfactory Maneuver execution

HAC (24 decks)

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