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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
What are the four operational restrictions for JP-4/JET B?
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
Primary Fuels
JP-5 JP-8 F-24 TS-1
27
Restricted Fuels
JET A JET A1 JET B JP-4
28
Emergency Fuels
JP8+100 F-27
29
Five reasons to abort start
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
Four Types of Approaches to a Ship
Visual Instrument ELVA Offset or Ordnance Approach
31
Cable Angle Hover Corrective Action Techniques
Cyclic 4-way trim Fly against lateral trim Using trim release, reposition the aircraft Fly against longitudinal trim
32
Five Rescue/Recovery Methods
Landing to effect a rescue Rescue via one or two wheels Rescue via hoist Rappelling Direct deployment
33
How to get out of retreating blade stall
Severity of maneuever - decrease Collective pitch - decrease Airspeed - decrease Altitude - decrease Rotor RPM - increase Gross Weight - decrease
34
LTE Effects
AOA Reduction - 060-120 Weather Vaning - 120-240 TR VRS - 210-330 ME Disc Vortex - 280-330
35
Vortex Ring State Requirements
Rate of descent > 700 fpm 0-20 KIAS Worse at > 1500 fpm 5-10 KIAS
36
Recovery from VRS
Decrease collective pitch Increase airspeed Enter autorotation if altitude permits
37
Five thing that should be performed for all aircraft emergencies (MADCD)
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
High Side Failure Conditions
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
Low Side Failure Conditions
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
High Speed Shaft Failure Conditions
Np is greater than Nr by more than 3% Engine TRQ is less than 10%
41
Indications of Main Trans Imminent Failure
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
Indications of Tail/Int Gearbox Imminent Failure
Strong medium frequency vibrations Hot metal fumes Any other associated indication
43
Three Types of Tail Rotor Malfunctions
Control cable failure Servo failure Restricted flight controls
44
With the stab in manual mode, the following are not recommended:
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
Three things to be performed for every sonar emergency
Alert crew. Execute Reeling Machine Malfunction EP. Complete the Sonar Troubleshooting Checklist.
46
Five Sections of the Engine
Inlet, Compressor, Combustor, Turbine, Exhaust
47
Flow of Air through Engine
Inlet cowling, inlet fairing, swirl vanes, IPS, collection scroll (dumped overboard by blower assembly), scroll vanes, de swirl vanes, compressor.
48
What does the Ng turbine drive?
Compressor AGB
49
What do you lose and retain in LOCKOUT?
Lose: TGT limiting, load sharing, Np governing. Retain: Np overspeed.
50
Two functions of the engine driven fuel boost pump
Provide reliable suction feed from fuel tank to the engine Provide discharge px to satisfy minimum inlet px of HMU
51
Three control parameters of EDECU
Np sensing Np overspeed and torque sensing TGT monitoring
52
Inputs the EDECU Receives
ENG SPEED TRIM CONT PWR ENG OVERSPEED A AND B
53
EDECU sends these signals to cockpit
TRQ Np TGT CONT PWR
54
What three things get power from the alternator?
AC power to igniter assembly, EDECU, and Ng signal to VIDS
55
Three factors that must be present to enter into Ground Resonance
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
When de-ice manual mode should be used?
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
What are the assumptions when calculating FlyAway Torque?
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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