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USCG MH-65D ZDB > 2015 STAN Closed Book > Flashcards

2015 STAN Closed Book Flashcards

0
Q

Any operation of an engine in the _____ power range will require major engine maintenance. The helicopter _____ be landed _____. Further flight _____ not be attempted until a thorough inspection has been accomplished by qualified maintenance personnel and a proper release obtained.

A

30-second power range
SHALL be landed AS SOON AS PRACTICABLE
SHALL NOT be attempted

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1
Q

30-second OEI is automatically selected by the FADEC upon any of the following malfunctions:

A
  1. Major FADEC failure
  2. BACKUP mode selected on one engine
  3. N1 difference between the two engines >6%
  4. Engine failure

“B-Men”

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2
Q
  1. Loss of transmit and/or receive capability from one crew position.
A

AUDIO CONTROL PANEL FAILURE

FMS/COMMS

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3
Q

SYMPTOM

1. Engine oil pressure on VEMD reading zero

A

VEHICLE PAGE INDICATION FAILURE

ENGINES

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4
Q

SYMPTOMS

  1. Blank RRU (COMM1 only)
  2. Loss of transmit/receive capability
  3. Annunciation of CHECK STATUS in the CDU
  4. CM1, CM2, HF, or FM in the STAT page fail line
A

TRANSMITTER AND RECEIVER FAILURE

FMS/COMMS MH SECTION

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5
Q

If time allows, wait _____ with the FADEC CONTROL SWITCH in the OFF position before attempting a restart.

A

30 seconds

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6
Q

If a start is initiated in flight with _____ above _____, the FADEC will not initiate the start sequence until _____ drops below _____.

A

17% N1

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7
Q

With both battery relay switches in the OFF position, the T/R will be unable to power the:

a. Battery BUS
b. Main DC BUS

A

B

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8
Q 
SEC SERVO P
SEC HYD LO PRESS
SERVO JAM
HYD 1 PRESS <720 psi
SEC HYD ISOLATE

Possible Symptoms:
High-pitched noise from transmission area
Stiffness in flight controls

A

SECONDARY HYDRAULIC SYSTEM FAILURE
(HYDRAULICS)

  1. CRUISE AIRSPEED - 75 TO 100 KIAS
  2. AVOID ABRUPT MANEUVERS
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9
Q

TCAS FAIL annunciation on VSI-TCAS display

A

TCAS FAILURE (FMS/COMMS)

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10
Q

Lateral vibration when performing run on/off maneuvers and during high speed taxiing; these vibrations may be quite violent

A

NOSEWHEEL SHIMMY DAMPER FAILURE
(LANDING GEAR)

  1. LIFT AIRCRAFT OFF GROUND IMMEDIATELY OR REDUCE TAXI SPEED
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11
Q

You are at 9000 pounds. What maneuvers are prohibited?

A

Above 8,500:
a. Practice single engine maneuvers

Above 8,900:

a. Shipboard landings
b. All RWAI maneuvers and AUF training maneuvers

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12
Q

MFD display pages continuously cycle without input.

A

DISPLAY CONTROL PANEL FAILURE

FMS/COMMS

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13
Q
  1. Annunciation of the CHECK STATUS in CDUs.
  2. Yellow CWM failure flag on the good MFD (all display pages).
  3. STAT page FAIL line: MFD1, HDG1, or MFD 2, HDG2
  4. MFD Status Page (failure annunciation in red): a. Possible PROCESSOR failure - CPU, RAM, MEM, EPROM, VIDEO
    b. Possible DISPLAY failure - GRAPHIC, LCD DRIVER, LAMP, VIDEO
  5. Degraded operation of one MFD, or one MFD becomes inoperative, display blanks, pages fluctuate, and/or edges turn white
  6. Possible loss of FD roll guidance
A 
MFD FAILURE (DELTA SECTION)
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
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14
Q

Do not turn the _______ switch ON until _______.

A

CAUTION - Do not turn HEAT on again until CAUSE OF OVERHEAT HAS BEEN DETERMINED.

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15
Q

Visual Autorotation Procedure

A
  1. COMPLETE THE “BIG 4” (AIRSPEED 75-105 KIAS)
  2. TURN TOWARD DESIRED LANDING AREA AND/OR INTO THE WIND
  3. AT 200-FT RADALT- WHEELS RECHECK
  4. AT 125-FT RADALT- INITIATE FLARE; INFLATE FLOATS AS REQUIRED
  5. ASSUME LANDING ATTITUDE, ELIMINATING YAW AND DRIFT PRIOR TO TOUCHDOWN
  6. COLLECTIVE- CUSHION THE LANDING
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16
Q

Instrument Autorotation Airspeed

A

75 KIAS

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17
Q

Max braking speeds

A

Above 8,900 pounds - 30 KGS

At or below 8,900 pounds - 38 KGS

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18
Q

Rotor brake limits

A

Max rotor speed for use - 170 RPM
Minimum cooling period of 5 mins between applications
After 3 consecutive attempts (13 secs per attempt), allow 10 mins cooling time.

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19
Q

Starter limits

A

5 consecutive attempts, 60 seconds cooling between attempts with a 30 minute cooling period after the 5th

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20
Q

Cranking limits

A

3 consecutive periods, 20 seconds per period, with 5 minutes cooling between each cranking period. Allow a 30 minute cooling period after the 3rd attempt.

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21
Q

ULY

A

UNCOMMANDED LEFT YAW (MAIN/TAIL ROTOR)

  1. IMMEDIATE FULL RIGHT PEDAL, MAXIMUM DEFLECTION
  2. ALTITUDE/OBSTACLES PERMITTING, SMOOTHLY APPLY FORWARD CYCLIC TO INCREASE FORWARD AIRSPEED
  3. ALTITUDE PERMITTING, REDUCE COLLECTIVE
  4. NR SWITCH - HI
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22
Q

Given MGB Failure Imminent symptoms:

A
  1. LANDING HOVER CHECKLIST - COMPLETE (200-FT checks at a minimum based on urgency)
  2. LAND/DITCH IMMEDIATELY
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23
Q

Any ONE of the following conditions:

  1. MGB PRESS
  2. XMSN oil pressure in red or zero (may be accompanied by MGB exceedance in CDU due to shared transducer)
  3. OIL TEMP
  4. XMSN oil temperature in red or zero
A

MAIN GEARBOX INDICATING SYSTEM FAILURE

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24
Q

Rotor blade damage known or suspected with vibrations of up to moderate.

A

LAND AS SOON AS POSSIBLE.

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25
Q

Abnormal vibrations of up to moderate.

A

ABNORMAL VIBRATIONS (ACFT DAMAGE)

  1. CRUISE AIRSPEED - 75-120 KIAS
  2. AVOID ABRUPT MANEUVERS
  3. LAND AS SOON AS POSSIBLE
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26
Q

Overriding consideration in an emergency

A
  1. MAINTAIN AIRCRAFT CONTROL
  2. ANALYZE THE SITUATION
  3. TAKE APPROPRIATE ACTION
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27
Q

In a hover, MCP for Torque is:

A

10.0 on FLI

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28
Q

(T/F) After a successful water ditching due to abnormal vibes you immediately throw on the rotor brake prior to egress.

A

FALSE

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29
Q

ENGINE COMPARTMENT FIRE ON DECK

A
  1. ATTEMPT TO CONFIRM THE PRESENCE OF THE FIRE (alert crew)
  2. FADEC CONTROL SWITCHES-BOTH OFF
  3. EMERGENCY FUEL SHUTOFF LEVERS - BOTH OFF
  4. BOOST PUMPS - ALL OFF
    If fire is confirmed:
  5. PRIMARY FIRE EXTINGUISHER BUTTON (affected engine)- CONFIRM; PUSH.
  6. SECONDARY FIRE EXTINGUISHER BUTTON - PUSH
  7. EMERGENCY ELECTRICAL CUTOFF - OFF
  8. ROTOR BRAKE - ON
  9. EVACUATE AIRCRAFT
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30
Q

A speed of ___ and ___ RPM will result in minimum rate of descent.

A

75 KIAS and 360 RPM

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31
Q

A speed of ___ and ___ RPM will result in maximum glide distance.

A

105 KIAS and 360 RPM

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32
Q

SE Failures In-Flight to Include: LOW HOVER, HIGH HOVER, AND TAKEOFF/LANDING TRANSITION

A
  1. NR - MAINTAIN
  2. AIRSPEED/ALTITUDE - CONTROL
  3. WHEELS/ FLOATS - AS REQUIRED
  4. LAND BACK OR CONTINUE FLIGHT
    Land back Procedure
  5. ASSUME LANDING ATTITUDE, ELIMINATE YAW AND DRIFT PRIOR TO TOUCHDOWN
    Continue Flight Procedure
  6. COLLECTIVE - ADJUST TO MAXIMUM POWER, MAINTAINING MINIMUM NR (at or above 345 RPM)
  7. AIRSPEED - CLIMB AT 70-75 KIAS
  8. NR/OEI - SET AS NECESSARY
  9. ANALYZE
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33
Q

Given:
N2 significantly above Nr
Zero Torque
Loud Noises

A

ENGINE GEARBOX/OUTPUT SHAFT FAILURE (ENGINES)

  1. COMPLETE THE “BIG 4”
  2. ENGINE SHUTDOWN PROCEDURE - COMPLETE
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34
Q
  1. GOV caution light illuminated
A

Minor FADEC failure

1. COMPLETE THE “BIG 4”

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35
Q

(T/F) A combination of engine oil pressure gauge decreasing or reading zero AND illumination of the OIL P warning light SHALL NOT be treated as and indication failure.

A

TRUE

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36
Q

OIL TEMP warning light illuminated

Abnormal rise in engine oil temp

A

ENGINE OIL COOLER FAN FAILURE

ENGINES

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37
Q

FLI DEGR annunciation on VEMD
TRQ value missing
GOV caution light illuminated

A

TORQUE, TOT, OR N1 INDICATING SYSTEM FAILURE (ENGINES)

  1. COMPLETE THE “BIG 4”
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38
Q
  1. VEMD Vehicle page indicator blanked without numerical values
  2. VEHICLE PARAMETER OVER LIMIT annunciation on the VEMD. (VEHICLE PARAMETER OVER LIMIT annunciation will no longer appear if Vehicle Page is selected. Selecting any other page will cause annunciation to reappear if the failure or out of limit condition still exists.)
A

VEHICLE PAGE INDICATION FAILURES

ENGINES

39
Q

Given MGB FAILURE IMMINENT symptoms, name EP and list bold face steps

A
  1. LANDING HOVER CHECKS - Complete (200-FT checks at a minimum based on urgency.
  2. LAND/DITCH IMMEDIATELY
40
Q

Due to the potential for fire damage to the _____ ______ ______, and/or the associated hydraulic lines, a fire in this __________ may result in complete loss of aircraft control.

A

FLIGHT CONTROL SERVOS….IN THIS COMPARTMENT

41
Q

After completing the Boldface steps for ENGINE COMPARTMENT FIRE IN FLIGHT up to Landing Checks, the fire appears to no-longer be evident - what is your landing criteria?

A

LAND AS SOON AS POSSIBLE

42
Q

Fire detector FAIL light illuminated

A

FIRE DETECTOR FAILURE (FIRES)

43
Q

When you pull the circuit breaker for the secondary hydraulic circuit breaker, it _____ power to the “2000 psi Isolation Valve, causing it to _____, possibly allowing _______.

A

SECURES POWER
OPENS THE VALVE
POTENTIALLY ALLOWING MORE FLUID TO LEAK OUT

44
Q

Angle of bank prohibited maneuvers:

A

a. Greater than 60 degrees less than 110 KIAS

b. Greater than 45 degrees at or above 110 KIAS

45
Q

Nr HI switch shall be in the HI position during hover flight greater than _____ AGL.

A

10 feet AGL

46
Q

Extended use of the Nr HI switch above _____, _____, may cause damage to aircraft systems.

A

best rate of climb airspeed, Vy

47
Q

Complete loss of audio (all stations)

A

AUDIO SYSTEM FAILURE (FMS/COMMS)

  1. PILOT AND COPILOT AUDIO BYPASS SWITCHES - BYPASS
48
Q

Approach mode is limited to no slower than ____ and a _____ glide path.

A

> 40 KIAS, 12 degree GP

49
Q

You are on deck with a gross weight of 9515 pounds; did you exceed a limit?

A

No; limit is 9590 on deck.

50
Q

You arm the floats at 110 KIAS- did you exceed a limit?

A

Yes; max speed to arm floats is 90 KIAS

51
Q

Upon departure from the water you unexpectedly enter IMC; what are your bold face steps?

A
  1. ANNOUNCE “INADVERTENT IMC”
  2. ESTABLISH AN INSTRUMENT SCAN
  3. ESTABLISH SAFE ALTITUDE, AIRSPEED, AND HEADING.
52
Q

HEATER O/HEAT light illuminated

A 
HEATER OVERHEAT (ECS) 
1. HEAT SWTICH - OFF
53
Q
  1. Copilot altimeter and VSI indicate erratic or erroneous information
  2. Erratic FD performance
A

COPILOT STATIC SYSTEM FAILURE
(PITOT/STATIC)

  1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
  2. AFFECTED FLIGHT DIRECTOR MODES - DESELECT
54
Q
  1. Erratic or erroneous copilot indicated airspeed
  2. MFDs - IAS readout erratic or erroneous
  3. Erratic FDS performance
  4. Possible loss of automatic turn coordination
A

COPILOT PITOT SYSTEM FAILURE
(PITOT/STATIC)

  1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
  2. AFFECTED FLIGHT DIRECTOR MODES - DESELECT
55
Q

Leaving Rescue Swimmer on Scene

A

(HOISTING/SWIMMER)

  1. MARK AND RECORD POSITION
  2. DEPLOY LIGHTED RAFT
  3. DEPLOY DMB
56
Q

EMERGENCY EGRESS

DITCHING/EGRESS

A
  1. WAIT FOR ALL VIOLENT MOTION TO STOP
  2. REFERENCE POINT - HOLD
  3. EMERGENCY RELEASE HANDLE - JETTISON
  4. CORDS/NVG(S) - DISCONNECT/REMOVE
  5. SEATBELT/HARNESS - RELEASE AND MAINTAIN REFERENCE
  6. EGRESS
  7. VEST - INFLATE WHEN CLEAR OF AIRCRAFT
57
Q

Fuel may be jettisoned at airspeed a between _____ and _____ KIAS at any rate of climb and descents up to _____ fpm. In addition, the landing gear shall be extended if jettisoning below ______ KIAS to help keep the fuel clear of the fuselage.

A

Between 40 and 120 KIAS
Up to 1,500 fpm
Extended below 60 KIAS

58
Q

If not manually secured, fuel will jettison to approximately ____ remaining in the left system and approximately ______ in the right system.

A 
150 lbs (approximately 7%) left system
170 lbs (approximately 8%) right system
59
Q

In any single-engine situation, maximum power available is attained at _____ and _____ RPM.

A

30-second OEI

365 RPM

60
Q

OEI Operations: Should a difference >= _____ % N1 develop between the two engines, the FADEC assumes an engine failure and arms OEI _____ rating for the good engine.

A

6% N1
30-second OEI
[it arms the rating for both engines]

61
Q

Hoist Electrical Runaway emergency procedure: Warning: Do not secure the cockpit master switch as all ______ capabilities will be lost.

62
Q

With an Altitude Controller Failure, the LOW ALT caution light is inoperative. FMS navigation will be degraded and the _____ maneuver is not available.

63
Q

Upon suffering a DUAL ENGINE FAILURE IN FLIGHT-GENERAL and conducting a power-off landing into a heavily wooded area, the flare and subsequent application of collective pitch should be executed so as to reach zero rate of descent and zero ground speed in a _______ nose up attitude as close to the top of the trees as possible. Increase/decrease collective to maximum/minimum as the helicopter descends vertically through the trees.

A

5 degrees nose up

Increase to maximum

64
Q

With loss of tail rotor thrust the offset lateral and cambered vertical fins provide sufficient horizontal lift to maintain balanced flight at airspeeds above _____ to _____ KIAS.

A

120-125 KIAS

65
Q

With a balanced fuel load, 3% or LOW in reference to the fuel quantity gauge indicates that at or about ______ mins of flight time remains at Maximum Continuous Power.

A

10 minutes

66
Q

Abort mission: The aircraft shall not proceed on its assigned mission. Allows for continued flight to the ________ _______ ________.

A

Desired recovery base

67
Q

Symptoms: HEATER O/HEAT warning light illuminated.

Corrective Action:
1. ________________

A

HEAT SWITCH - OFF

68
Q

Which checklist can be omitted when remaining in the VFR traffic pattern at the same airport?

A

Level off checks

69
Q

A minimum of _____ VDC is required for battery start. Both engines shall be started using _________.

A

The same DC power supply.

70
Q

WARNING: A jammed sliding door may present an egress hazard. Over-water operations below ____ feet should not be conducted with a jammed door.

71
Q

_____ and _______ flight director modes should not be used above _____ MCP.

A

IAS-ALT and IAS-VS

80% MCP

72
Q

During a MATCH, the attitude recommended when arriving at the GATE is _____ to _____ degrees for wind up to 10 knots, and _____ to _____ for winds over 10 knots.

A

4 to 5

2 to 3

73
Q

The MATCH procedure may be modified as required if the ______ can be identified by using the CDU or _____.

A

GATE

RADAR

74
Q

During a CATCH the PAC must monitor the HSI prior to ________

A

VERT Capture

75
Q

Due to the potential for fire, do not reset these circuit breakers.

A

AC electrical system and Fuel system

76
Q

The slope limitation for landing and stopping the rotor is ______ degrees.

A

10 degrees

77
Q

Allow for at least _____ after fuel jettison is terminated before hovering or landing.

78
Q

Symptoms:
ENG FUEL P light illuminated

Corrective Action:

A

ENGINE FUEL PRESSURE LOW (FUEL)

  1. Complete the “Big 4”
  2. Engine - Monitor

If abnormal indications

  1. Engine shutdown procedure - Complete
79
Q

Rotor engagement is limited to winds of ____ knots within ______ , or ______ knots from all other directions.

A

55 knots within 20 degrees.

35 knots from all other directions.

80
Q

A tail gearbox chip emergency procedure calls for what landing criteria?

A

Land as soon as possible.

81
Q

Slope operations are conducted (select all that apply)
Upslope
Downslope
Side slope

A

Upslope and side slope

82
Q

ULY in a hover boldface

A
  1. EFSLs - BOTH OFF
  2. MAINTAIN LANDING ATTITUDE
  3. CUSHION LANDING WITH COLLECTIVE

E=MC

83
Q

What is the BOLDFACE first step for the EP: ENGINE SURGE OR COMPRESSOR STALL ON DECK

A
  1. FADEC CONTROL SWITCH (affected engine) - OFF
  2. FUEL BOOST PUMPS (affected engine) - OFF
  3. TOT - MONITOR FOR POST SHUTDOWN FIRE
84
Q

The FLI will display what annunciation in the message zone to alert the crew to a fuel, hydraulics, or engine limit exceedance if the page is not currently displayed?

A

VEH (or FUEL) PARAM OVER LIMIT

85
Q

“Operating procedures, techniques, etc., which could result in personal injury or loss of life if not strictly followed” is the definition for __________.

86
Q

During a Secondary Hydraulic System Low Fluid Level condition, the following systems are hydraulically isolated: ______ ________ ________. Electrical power to the _______ is also isolated.

A

Brakes, landing gear and TALON

Hoist is electrically isolated

87
Q

Starter limits: For cooling purposes, allow a minimum of ______ between start attempts and ______ minutes after the _____ attempt.

A

60 seconds

30 minutes after the 5th attempt

88
Q

Post shutdown fire boldface:

A

1) FADEC CONTROL SWITCHES- CHECK OFF
2) BOOST PUMPS - CHECK OFF

If high TOT is still evident after 10 seconds:

3) EFSL - OFF
4) CRANK BUTTON - DEPRESS UNTIL TOT DECREASES

If TOT continues to rise or does not decrease:

5) EMERGENCY ELECTRICAL CUTOFF - OFF
6) ROTOR BRAKE - ON
7) EVACUATE AIRCRAFT

89
Q

MAJOR FADEC FAILURE boldface:

A

1) COMPLETE THE “BIG 4”
2) TRAINING SWITCH - FLT
3) FADEC BACKUP SWITCH (affected engine) CONFIRM - BACKUP

90
Q

PRI HYD SYSTEM FAILURE boldface

A

1) CRUISE AIRSPEED 75-100 KIAS

2) AVOID ABRUPT MANEUVERS

91
Q

An aural “gong” will sound when Torque 1+2= _______%.

92
Q

I love hitting the starter “crank” button. How long do I have to wait after I used it only once for 20 seconds?

A

5 minutes

20 seconds per attempt
3 attempts
5 minutes between attempts
30 minutes after the 3rd attempt

93
Q

The low NR audio will/will not function when the NR indicator fails.

A

Will still function

94
Q

The components powered by the Battery Bus include:

A 
Landing gear emergency extension
Emergency hoist control
Hoist shear
Horn
Left fire extinguisher
Right fire extinguisher
Overhead lights
Clock

Gear, shear, horn, clock, control, lights, fire

USCG MH-65D ZDB (18 decks)

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