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USCG MH-65D ZDB > MH65D 2016 New Red Book > Flashcards

MH65D 2016 New Red Book Flashcards

1
Q

The term LAND/DITCH IMMEDIATELY is defined as:

A

executing a landing or ditching without delay due to the seriousness of the malfunction. The primary consideration is to assure the survival of occupants of the aircraft.

WARNING
The potential loss of the airframe after aircrew egress is not sufficient cause to continue flight.

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2
Q

The term LAND AS SOON AS POSSIBLE is defined as:

A

executing a landing at the first site at which a safe landing can be made. The primary consideration is the urgency of the emergency.

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3
Q

The term LAND AS SOON AS PRACTICABLE means:

A

extended flight is not recommended. The landing site and duration of flight is at the discretion of the Pilot-in-Command.

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4
Q

The term ABORT MISSION means

A

that the aircraft shall not proceed on its assigned mission and should return to its desired recovery base.

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5
Q

When speaking in terms of circuit breakers, CHECK means:

A

Note status of affected circuit breaker (out or in). No further action necessary.

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6
Q

When speaking in terms of circuit breakers, CHECK/RESET means:

A

Ensure that affected circuit breaker is in. If affected circuit breaker is popped, attempt to reset circuit breaker once.

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7
Q

When speaking in terms of circuit breakers, CYCLE means:

A

Pull affected circuit breaker, wait 15 seconds, and reset circuit breaker.

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8
Q

When speaking in terms of circuit breakers, PULL means:

A

Manually open (pull) affected circuit breaker.

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9
Q

TWO or more of the following Symptoms:

  1. Complete loss of MGB lubrication indicated by:
    a) MGB PRESS warning light illuminated
    b) MGB PMP MAIN caution light illuminated
    c) MGB PMP AUX caution light illuminated
    d) XMSN OIL pressure at zero on VEMD
  2. Yaw kicks, abnormal MGB noises, or unusually high power requirements.
  3. GB CHIP warning light with a MGB CHIP annunciation on the VEMD FUEL/CAUTION page.
A 
MGB FAILURE IMMINENT
=Main Gearbox Section=
Corrective Action:
1. 200-FOOT CHECKLIST - COMPLETE
2. LAND/DITCH IMMEDIATELY.
WARNING
The potential loss of the airframe after aircrew egress is not sufficient cause to continue flight.
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10
Q

Any ONE of the following Symptoms:

  1. Drop in XMSN OIL pressure indicated by:
    a) MGB PRESS warning light illuminated
    b) Low XMSN OIL pressure
  2. Complete loss of MGB lubrication indicated by:
    a) MGB PRESS warning light illuminated
    b) MGB PMP MAIN caution light illuminated
    c) MGB PMP AUX caution light illuminated
    d) XMSN OIL pressure at zero on VEMD
    Possible Symptom:
    Abnormal rise in MGB XMSN OIL temperature.
  3. GB CHIP warning light with a MGB CHIP annunciation on the VEMD Caution/Fuel page.
  4. Abnormal MGB noises.
A

MGB MALFUNCTION
=Main Gearbox Section=
Corrective Action:
No memory items

=NOTE=
In order to determine whether or not power requirements have increased for a MGB problem, the pilot should note and verbalize the flight regime, airspeed, and current FLI power setting at the onset of the malfunction to establish a baseline for later comparison.

=NOTE=
Single malfunctions while serous do not indicate that a MGB failure is imminent. Flight without MGB oil lubrication should be sustainable for approximately 25 minutes.

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11
Q

Symptoms:

  1. MGB PMP MAIN caution light illuminated.
  2. XMSN OIL pressure decrease.
  3. XMSN OIL temperature increase.
A 
MGB PUMP MAIN FAILURE
=Main Gearbox Section=
Corrective Action:
No memory items
=NOTE=
MGB lubrication will continue to be provided by the auxiliary pump.  The auxiliary pump operates at a lower pressure and bypasses the oil cooler.
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12
Q

Symptom:

1. MGB PMP AUX caution light illuminated

A 
MGB PUMP AUXILIARY FAILURE
=Main Gearbox Section=
Corrective Action:
No memory items
=NOTE=
During normal operation, the auxiliary pump of the MGB lubricating system is not used for lubrication.  A failure will indicate a loss of redundancy in case of main pump failure.
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13
Q

Symptoms:
1. OIL TEMP arming light illuminated AND increase in XMSN OIL temperature above 120 degrees C on the VEMD.

NOTE: The OIL TEMP warning light is shared by temperature switches from the MGB and both engines. Pilots shall reference the VEMD Vehicle Page to determine which system is at fault and follow the appropriate emergency procedure.

  1. If no secondary indications, see MGB INDICATING SYSTEM FAILURE Page 3-10.
A

MGB OVERHEAT
=Main Gearbox Section=
Corrective Action:
No memory items

=NOTES=

1) MGB overheat may not be evident at airspeeds above 120 KIAS
2) Operations at speeds below 120 KIAS may not provide sufficient airflow through the oil cooler for effective cooling.
3) Minimize hovering and ground operations due to loss of cooling airflow.

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14
Q

Symptoms:

1. XMSN OIL pressure on VEMD greater than 80 psi.

A

MGB HIGH-PRESSURE
=Main Gearbox Section=
Corrective Action:
No memory items

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15
Q

Any ONE of the following symptoms:

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

MGB INDICATING SYSTEM FAILURE
=Main Gearbox Section=
Corrective Action:
No memory items

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16
Q

(Hover Flight and Transition Flight between 0 and 80 KIAS)
Symptom:
1. FLI exceeds 10.0.

Possible Symptoms:
2. MGB QT capture on the Engine Exceedance page.

  1. Aural “gong” tone and illumination of the limit light.
A 
MGB OVERTORQUE
=Main Gearbox Section=
Corrective Action:
1. REDUCE TORQUE TO WITHIN LIMITS, WHEN ABLE.
(continued non-memory)
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17
Q

(Cruise Flight)
Symptom:
1. FLI exceeds 8.8.

Possible Symptoms:
2. MGB QT capture on the Engine Exceedance page.

  1. Aural “gong” tone and illumination of the limit light.
A 
MGB OVERTORQUE
=Main Gearbox Section=
Corrective Action:
1. REDUCE TORQUE TO WITHIN LIMITS, WHEN ABLE.
(continued non-memory)
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18
Q

Symptom:
1. MGB FIRE warning light illuminated

Possible Symptoms:
2. Illumination of MGB related warning and caution lights

  1. Loss of XMSN OIL pressure and/or rise in temperature.
  2. Drop in fuel or hydraulic pressure
  3. Electrical system malfunctions

WARNING:
Due to the potential for fire damage to the flight control servos and/or the associated hydraulic lines, a fire in this compartment may result in complete loss of aircraft control.

A 
MGB FIRE
=Fires Section=
Corrective Action:
1. ATTEMPT TO CONFIRM PRESENCE OF FIRE (alert crew).
2. 200-FOOT CHECKLIST - COMPLETE

If fire confirmed:
3. LAND/DITCH IMMEDIATELY
=WARNING=
The potential loss of the airframe is not sufficient cause to continue flight.

If fire NOT confirmed:
3. LAND AS SOON AS POSSIBLE.
=WARNING=
a) Illumination of the MGB FIRE warning light may indicate a fire, overheat condition, or a short circuit in the detection system.
b) Since no fire extinguishing system is provided for the MGB compartment, immediate action should be taken to confirm the presence of fire.

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19
Q

Symptoms:

  1. Engine FIRE warning light illuminated.
  2. Red warning light on the corresponding EFSL.
  3. Flames and/or smoke coming from engine compartment.
  4. Electrical system malfunctions.
A

ENGINE COMPARTMENT FIRE INFLIGHT
=Fires Section=
Corrective Action:
1. ATTEMPT TO CONFIRM THE PRESENCE OF FIRE (alert crew).
2. SINGLE ENGINE FLIGHT PROFILE- ESTABLISH.

If fire confirmed:

  1. FCS (affected engine) - CONFIRM; IDLE; CONFIRM; OFF.
  2. EFSL (affected engine) - CONFIRM; OFF.
  3. BOOST PUMPS (affected engine) - OFF.
  4. PRI FIRE EXTINGUISHER BUTTON (affected engine) - CONFIRM; PUSH.
  5. SEC FIRE EXTINGUISHER BUTTON (affected engine) - PUSH.
  6. 200-FOOT CHECKLIST - COMPLETE.

If fire still persists:
9. LAND/DITCH IMMEDIATELY.

If fire no longer evident:
9. LAND AS SOON AS POSSIBLE.

If fire not confirmed:
3. LAND AS SOON AS PRACTICABLE (non memory)

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20
Q

While on deck:
Symptoms:
1. Engine FIRE warning light illuminated.
2. Possible hand or voice signals from ground crew.
3 Red warning light illuminated on corresponding EFSL.

A 
ENGINE COMPARTMENT FIRE ONDECK
=Fires Section=
Corrective Action:
1. ATTEMPT TO CONFIRM PRESENCE OF FIRE (alert crew).
2. FCS - BOTH OFF.
3. EFSL - BOTH OFF.
4. BOOST PUMPS - ALL OFF.

If fire confirmed:

  1. PRI FIRE EXTINGUISHER BUTTON (affected engine) - CONFIRM; PUSH.
  2. SEC FIRE EXTINGUISHER BUTTON (affected engine) - PUSH.
  3. EMERGENCY ELECTRICAL CUTOFF - OFF.
  4. ROTOR BRAKE - ON.
  5. EVACUATE AIRCRAFT.
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21
Q

Symptoms:

  1. Smoke/fumes/sparks originating from a single component inside the cabin.
  2. Smoke/fumes/sparks originating from an unknown component inside the cabin.
A

INTERNAL FIRE (CABIN, ELECTRICAL AND/OR AVIONICS)
=Fires Section=
Corrective Action:
1. DESIGNATE CREWMEMBER TO FIGHT FIRE.
2. AFFECTED EQUIPMENT - OFF.
3. CIRCUIT BREAKERS - PULL (for affected circuits).

Note:
An avionics fire will be fought by disconnecting enough camlocks on the avionics rack pannel to allow access for the fire extinguisher nozzle. Short blasts are advised to preserve extinguishing agent in case of reflash. Close rack panel and monitor for reflash.

  1. RACK BLOWER CIRCUIT BREAKER - PULL (for avionics rack fire only - avionics rack panel R5 No. 4).
  2. HEAT/COOL SWITCHES - OFF.
  3. RAM AIR, DOORS, & CP WINDOW - CLOSED.
  4. 200-FOOT CHECKLIST - COMPLETE.

If electrical or avionics fire persists:
8. EMERGENCY ELECTRICAL CUTOFF - OFF.

If electrical or avionics fire persists:
9. LAND/DITCH IMMEDIATELY.
=WARNING=
The potential loss of the airframe after aircrew egress is not sufficient cause to continue flight.

If fire goes out:
10. LAND AS SOON AS POSSIBLE.

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22
Q

SMOKE AND FUME ELIMINATION

A
  1. HEAT/COOL SWITCHES - OFF.
  2. RAM AIR, CABIN SLIDING DOOR, AND CP WINDOW - OPEN.

(Think cross/genuflect- ^v>

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23
Q

Symptoms:
1. TOT rises rapidly after FCS has been placed in the OFF position

  1. TOT does not decrease within 10 seconds after FCS has been placed in the OFF position.
A 
ENGINE POST-SHUTDOWN FIRE
=Fires Section=
Corrective Action:
1. FADEC CONTROL SWITCH - CHECK OFF.
2. BOOST PUMPS - CHECK OFF.
3. EFSL (affected engine) - OFF.

If high TOT still evident after 10 seconds:
4. CRANK BUTTON - DEPRESS UNTIL TOT DECREASES.

If TOT continues to rise or does not decrease:

  1. EMERGENCY ELECTRICAL CUTOFF - OFF.
  2. ROTOR BRAKE - ON.
  3. EVACUATE AIRCRAFT.
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24
Q

Symptom:

1. Fire detector FAIL light illuminated

A

FIRE DETECTOR FAILURE
=Fires Section=
Corrective Action:
Non-memory

=NOTE=
An open circuit in the fire detection system will result in FAIL light illumination.

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25
Q

Symptom:

1. L EXT or R EXT caution light illuminated

A

FIRE SUPPRESSION FAILURE
=Fires Section=
Corrective Action:
Non-memory

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26
Q

Possible Symptoms:
1. Known or suspected aircraft damage

  1. Abnormal vibrations.

=WARNING=
Known or suspected aircraft damage that appears minor on the surface may in fact involve structural or flight control components. It is imperative that known or suspected damage be thoroughly investigated prior to continuing flight.

=NOTE=
A reduction in airspeed between 75-100 KIAS may reduce vibrations and improve flight characteristics (weather, flight conditions, and distance from landing area permitting).

A

KNOWN OR SUSPECTED AIRCRAFT DAMAGE/ABNORMAL VIBRATIONS
=Aircraft Damage/Abnormal Vibrations Section=
Corrective Action:
1. 200-FOOT CHECKLIST - COMPLETE.
=WARNING=
The potential loss of the airframe after aircrew egress is not sufficient cause to continue flight.

If SEVERE vibrations and/or drastically altered flight characteristics:
2. LAND/DITCH IMMEDIATELY.

If MODERATE vibrations:
2. LAND AS SOON AS POSSIBLE

If SLIGHT vibrations of unknown origin or aircraft damage is known or suspected.
2. Land as soon as practicable.

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27
Q

Symptom:

1. Windscreen crack evident.

A

WINDSCREEN CRACKS
=Aircraft Damage/Abnormal Vibrations Section=
Corrective Action:
Non-memory

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28
Q

Symptom:

1. If NR >380 RPM (10 Hz chopped tone).

A

NR OVERSPEED
=Main/Tail Rotor Section=
Corrective Action:
1. REDUCE NR TO WITHIN LIMITS, WHEN ABLE.
(landing criteria given depending on degree of exceedance)

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29
Q

Symptoms:

  1. NR HI caution light illuminated with NR switch in NORMAL.
  2. NR >365 RPM with the NR switch in NORMAL
A

VARIABLE NR MALFUNCTION
=Main/Tail Rotor Section=
Corrective Action:
Non-memory

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30
Q

Symptom:

1. NR gauges fluctuate abnormally or indicates zero.

A 
NR INDICATING SYSTEM FAILURE
=Main/Tail Rotor Section=
Corrective Action:
Non-memory
=NOTE=
The Low NR audio may still function even when both NR indicators fail.
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31
Q

Symptom:

1. Any uncommanded left yaw not attributable to mechanical failure of the tail rotor drive system.

A

UNCOMMANDED LEFT YAW (ULY)
=Main/Tail Rotor Section=
Corrective Action:
1. IMMEDIATE FULL RIGHT PEDAL
2. ALTITUDE/OBSTACLES PERMITTING, SMOOTHLY APPLY FORWARD CYCLIC TO INCREASE FORWARD AIRSPEED.
3. ALTITUDE PERMITTING, REDUCE COLLECTIVE.
=WARNING=
If a large descent rate develops close to the ground/water, the subsequent large collective increase required to arrest the descent prior to groundwater contact may aggravate or reinitiate ULY.

  1. NR SWITCH - HI.
    =NOTE=
    Consideration should be given to having the PM switch the NR to HI while the PF executes the initial corrective action.
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32
Q

Symptom:

1. GB CHIP warning light illuminated and a TGB CHIP annunciation on the VEMD CAUTION/FUEL page.

A

TGB CHIP DETECTED
=Main/Tail Rotor Section=
Corrective Action:
1. ESTABLISH SAFE ALTITUDE/AIRSPEED FOR POSSIBLE LOSS OF TAIL ROTOR THRUST.

  1. LAND AS SOON AS POSSIBLE.

=NOTE=
If accompanied by strong medium frequency vibrations or abnormal noise from the tail section, plan your approach for the possible loss of tail rotor thrust.

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33
Q

Possible Symptoms:

  1. GB CHIP warning light illuminated (loss of thrust) with a TGB CHIP annunciation on the VEMD CAUTION/FUEL page.
  2. Uncommanded yaw to the left
  3. Tail rotor pedals movable without effect (loss of thrust)
  4. Abnormal vibration or noise from the tail section (loss of thrust or fixed pitch).
  5. Cannot move pedals (fixed pitch).
A

LOSS OF TAIL ROTOR THRUST IN FORWARD FLIGHT OR FIXED TAIL ROTOR PITCH
=Main/Tail Rotor Section=
Corrective Action:
1. DIRECTIONAL CONTROL UTILIZING CYCLIC AND COLLECTIVE.
(continued non-memory)

=WARNING=
If a suitable surface is not available, a power-off authoritative landing to the best available area may be required.

=CAUTION=
Changing the NR switch from its current setting may exacerbate a tail rotor malfunction based on a high or low fixed pitch setting and is not recommended.

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34
Q

Symptom:
1. IMMEDIATE, rapid left yaw acceleration.
Possible Symptoms:
2. Tail rotor pedals movable but with no apparent effect.
3. Abnormal vibration or noise from the tail section.
4. GB CHIP warning light illuminated and a TGB CHIP annunciation on the VEMD CAUTION/FUEL page.

A 
LOSS OF TAIL ROTOR THRUST WHILE HOVERING
=Main/Tail Rotor Section=
Corrective Action:
1. EFLs - BOTH OFF.
2. MAINTAIN LANDING ATTITUDE.
3. COLLECTIVE - CUSHION THE LANDING.
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35
Q 
Possible Symptoms:
(while in a hover or transitioning to/from)
1. DIF N1 aural warning.
2. DIF N1 warning light illuminated
3. NR droop
4. Low NR horn
5. Abnormal engine parameters
6. TRQ, TOT, N1, and N2 decreasing.
(cont.)
A

SINGLE - ENGINE FAILURE INFLIGHT TO INCLUDE: LOW HOVER, HIGH HOVER, AND TAKEOFF/LANDING TRANSITION
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4
If suitable landing area is immediately available:
2. ASSUME LANDING ATTITUDE, ELIMINATE YAW AND DRIFT PRIOR TO TOUCHDOWN.
If suitable landing area is not immediately available:
2. COLLECTIVE - ADJUST TO MAXIMUM POWER, MAINTAIN NR ABOVE 345 RPM.
3. AIRSPEED - CLIMB AT Vx or Vy.
4. NR/OEI - SET AS NECESSARY
5. ANALYZE.

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36
Q 
Possible Symptoms:
(in flight)
1. DIF N1 aural tone
2. DIF N1 warning light illuminated
3. NR droop
4. Low NR horn
5. Abnormal engine parameters
6. TRQ, TOT, N1, and N2 decreasing.
(cont.)
A 
FLAMEOUT
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4.
(continued non-memory)

FEON are all just "COMPLETE THE BIG 4"
[flameout, engine geabox/output shaft failure, n1 divergence/partial power loss]
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37
Q 
Possible Symptoms:
1. N2 significant above NR.
2. Zero TRQ on malfunctioning engine.
3. Loud noises from the engine area.
4. DIF N1 aural warning
5. DIF N1 warning light illuminated
6. NR droop.
7. Low NR horn.
NOTE
When N2 reaches 429 +/- 4 RPM, the FADEC will operate the stop electro-valve via the BIM and shut down the engine.
A 
ENGINE GEARBOX / OUTPUT SHAFT FAILURE
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4.
(continued non-memory)

FEON are all just “COMPLETE THE BIG 4”
[flameout, engine geabox/output shaft failure, n1 divergence/partial power loss]

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38
Q

Possible Symptoms:

  1. ENG 1 OIL P or ENG 2 OIL P warning light illuminated with engine oil pressure decreasing or reading zero.
  2. Engine pressure fluctuates, increases, or decreases abnormally.
  3. Engine oil pressure less than 25 psi.
  4. Engine status light illuminated.

=NOTE=
Oil pump failure resulting in the above symptoms may be preceded by an initial increase in oil pressure above 100 psi, accompanied by a CHECK CDU annunciation.

A 
ENGINE LUBRICATION SYSTEM FAILURE
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4.
2. FCS (affected engine) - CONFIRM; IDLE, CONFIRM; OFF.
(continued non-memory)

=NOTE=
The boost pumps on the failed side must be ON to drive the transfer ejectors.

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39
Q

Symptoms:

  1. ENG 1 CHIP or ENG 2 CHIP warning light illuminated.
  2. ENGINE CHIP annunciation on the VEMD CAUTION/FUEL page.
A 
ENGINE CHIP DETECTED
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4.
2. FCS (affected engine) - CONFIRM; IDLE.

If ABNORMAL IDLE indications:
3. FCS (affected engine) - CONFIRM; OFF.
(continued non-memory)

=NOTE=
The boost pumps on the failed side must be ON to drive the transfer ejectors.

=NOTE=
If additional power is required for landing, affected FCS may be switched to FLT position.

40
Q 
Possible Symptoms:
(in flight)
1. Popping or rumbling noises.
2. TOT increases/fluctuates.
3. TRQ and N1 decreases.
4. Airframe vibrations/shuddering.
A

ENGINE SURGE OR COMPRESSOR STALL INFLIGHT
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4.

If ABNORMAL ENGINE indications and affected engine can be identified:
2. FCS (affected engine) - CONFIRM; IDLE.

If ABNORMAL IDLE indications:
3. FCS (affected engine) - CONFIRM; OFF.
(continued non-memory)

=NOTE=
The boost pumps on the failed side must be ON to drive the transfer ejectors.

=NOTE=
If additional power is required for landing, affected FCS may be switched to FLT position. A surge may reoccur at any time.

41
Q 
Possible Symptoms:
(on deck)
1. Popping or rumbling noises.
2. TOT increases/fluctuates.
3. TRQ and N1 decreases.
4. Airframe vibrations/shuddering.
A 
ENGINE SURGE OR COMPRESSOR STALL ONDECK
=Engines Section=
Corrective Action:
1. FCS (affected engine) - OFF.
(continued non-memory)
42
Q

Symptoms:

  1. DIF N1 warning light illuminated.
  2. DIF N1 aural horn.
  3. Possible NR droop
  4. Low NR horn.
  5. OEI GOV Mode on VEMD.
  6. N1 difference between both engines is greater than 6%.
A 
N1 DIVERGENCE/PARTIAL POWER LOSS
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4.
(continued non-memory)

=NOTE=
The N1 of the malfunctioning engine determines the FLI page displayed. If the N1 is greater than 40%, the OEI GOV Mode page will be displayed. If the N1 is less than 40%, the OEI Mode page will be displayed.

FEON are all just “COMPLETE THE BIG 4”
[flameout, engine geabox/output shaft failure, n1 divergence/partial power loss]

43
Q

Symptoms:

  1. FADEC 1 FAIL or FADEC 2 FAIL caution light illuminated.
  2. Engine status light.
  3. OEI GOV Mode page displayed.
  4. Affected engine will not respond to collective movement due to fuel flow metering being frozen at the rate present when the FADEC failed.
A

MAJOR FADEC/GOVERNOR FAILURE (LEVEL 3)
=Engines Section=

FADEC FAIL, FREEZE!!

Corrective Action:
1. COMPLETE THE BIG 4.
=CAUTION=
Reduction of collective before selection of the FADEC Backup Switch could result in an overspeed condition and possible engine shutdown by the BIM

  1. TRNG SWITCH - FLT.
    =WARNING=
    The FADEC BACKUP switch shall not be in BACKUP when an engine is at TRNG IDLE as N1 matching will occur without regard to the opposite engine’s current N1 setting.
  2. FADEC BACKUP SWITCH (affected engine) - CONFIRM; BACKUP.
    =NOTE=
    While FADEC N1 matching is assured, there will be some acceleration delay on the engine in BACKUP mode.
    (continued non-memory)
44
Q

Symptom:
1. GOV caution light illuminated.

Possible Symptoms:

  1. FLI DEGR annunciation of the VEMD
  2. TRQ, TOT, or N1 value missing with TRQ, TOT, or N1 label in boldface yellow type.
  3. One or both VEMD screens off or failed.
  4. NO BINGO annunciation on CDU.
  5. LANE 1/2 FAILED > PRESS OFF 1/2.
  6. CROSS TALK FAILED > PRESS OFF 1/2.
  7. STAT page FAIL line: BARO.
A 
MINOR FADEC/GOVERNOR FAILURE (LEVEL 2)
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4.
(continued non-memory)

=WARNING=
A minor FADEC failure involving a loss of DECU cross-talk communication (i.e., BALAN.A fault) may result in NR decreasing and stabilizing below the continuous operating range (<345 RPM). Collective reduction may not return the NR to normal parameters, but both engines should produce sufficient power to maintain level flight. Corrective action should be based on a careful analysis of TRQ, N1, and TOT and not solely upon NR. Consideration should be given to placing the NR switch to HI and performing a running landing.

45
Q

Symptom:

1. Fail code on VEMD System Status page.

A

FADEC FAILURE (LEVEL 1)
=Engines Section=
Corrective Action:
(non-memory)

46
Q

Symptom:
1. OIL TEMP warning light illuminated AND increase in ENG1 and/or ENG2 OIL temperature on the VEMD above 115 degrees C.
NOTE
If OIL TEMP warning light illuminated with no secondaries, treat as MGB INDICATING SYSTEM FAILURE.

A 
ENGINE OVERHEAT
=Engines Section=
Corrective Action:
(non-memory)
=NOTE=
If only one engine has an overheat condition consideration should be given to bringing the affected engine to IDLE.
47
Q

ENGINE SHUTDOWN PROCEDURE INFLIGHT

A

=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4.
(continued non-memory)

48
Q

Symptom:

1. Aircraft ondeck in unsafe condition.

A 
EMERGENCY SHUTDOWN PROCEDURE ONDECK
=Engines Section=
Corrective Action:
1. EFSLs - BOTH OFF.
2. EMERGENCY ELECTRICAL CUTOFF - OFF.

=CAUTION=
Application of the rotor brake above 170 RPM may result in a fire.

  1. ROTOR BRAKE - ON.
  2. EVACUATE AIRCRAFT
49
Q

Possible Symtoms:

  1. FADEC 1 FAIL or FADEC 2 FAIL caution light illuminated
  2. Insufficient voltage (<17 VDC)
  3. TOT digital value is underscored in red.
  4. No rise in N1 and/or TOT within 10 seconds.
  5. TOT rises rapidly and/or appears that it will exceed 750 degrees C (hot start).
  6. The main rotor does not turn prior to 25% N1.
  7. Engine does not reach 45% N1 by 30 seconds and is no longer accelerating.
  8. ENG 1 OIL P or ENG 2 OIL P warning light does not extinguish prior to 70% N1.
  9. N2 needle passes the NR needle.
A 
ENGINE START EMERGENCIES
=Engines Section=
Corrective Action:
1. FADEC CONTROL SWITCH - OFF.
(continued non-memory)

=CAUTION=
If OAT is below 0*C, dry crank the engine for 20 seconds to remove fuel prior to subsequent start attempt

•NOTE•
Do not attempt a subsequent start until the reason for the abort has been investigated and corrected

50
Q

Any ONE of the following Symptoms:

  1. ENG OIL 1 or 2 pressure indication goes to full scale, zero, or is blanked.
  2. ENG OIL 1 or 2 temperature indication goes to full scale, zero, or is blanked.
  3. VEHICLE PARAMETER OVER LIMIT annunciation on the VEMD. (This annunciation will no longer appear if the Vehicle page is selected. Selecting any other page will cause annunciation to flash if failure condition still exists.)
  4. ENG 1 OIL P or ENG 2 OIL P warning light illuminated.
A

ENGINE INDICATING SYSTEM FAILURE
=Engines Section=
Corrective Action:
(non-memory)

51
Q 
Symptoms:
(in flight)
1. Low NR horn - ON.
2. NR - DECAYING
3. Engine parameters - BOTH ENGINES DECREASING
4. Possible right yaw.
A

DUAL ENGINE FAILURE INFLIGHT (AUTOROTATION PROCEDURE)
=Engines Section=
Corrective Action:
1. COMPLETE THE BIG 4 (airspeed 75-105 KIAS)
2. TURN TOWARDS DESIRED LANDING AREA AND/OR INTO THE WIND.
3. AT 200 FT RADALT - WHEELS RECHECK.
4. AT 125 FT RADALT - INITIATE FLARE. CONTROL THE RATE TO ARRIVE AT 20 DEGREES NOSEUP AT 75 FOOT RADALT; INFLATE FLOATS AS REQUIRED.
5. MAINTAIN FLARE UNTIL DESIRE AIRSPEED IS REACHED - 30 KT PLUS HALF THE WIND SPEED.
6. ASSUME FIVE DEGREE NOSEUP, WINGS-LEVEL LANDING ATTITUDE.
7. AT 25 FT RADALT - COLLECTIVE (cushion the landing).

52
Q

Possible Symptoms:

  1. PRI SERVO P warning light illuminated
  2. SERVO JAM warning light illuminated
  3. LIMIT lights illuminated (may not illuminate during reduced power flight).
  4. HYD2 PRESS <720 psi.
  5. SERVO LIMIT annunciation on the VEMD CAUTION/FUEL page.
  6. High-pitched noise from transmission area.
  7. Stiffness in flight controls.
  8. Feedback in pedals.
A 
PRIMARY HYDRAULIC (HYD 2) SYSTEM MALFUNCTION
=Hydraulics Section=
Corrective Action:
1. CRUISE AIRSPEED - 75 TO 100 KIAS.
(continued non-memory)
53
Q

Possible Symptoms:

  1. SEC SERVO P warning light illuminated
  2. SEC HYD LO PRESS warning light illuminated.
  3. SERVO JAM warning light illuminated
  4. SEC HYD ISOLATE warning light illuminated (if low fluid condition exists).
  5. HYD1 PRESS <720 psi.
  6. High-pitched noise from transmission area.
  7. Stiffness in flight controls.
  8. Feedback in pedals.
A 
SECONDARY HYDRAULIC (HYD 1) SYSTEM MALFUNCTION
=Hydraulics Section=
Corrective Action:
1. CRUISE AIRSPEED - 75 TO 100 KIAS.
(continued non-memory)
54
Q

Any ONE of the following Symptoms:

  1. SEC HYD HI PRES warning light illuminated.
  2. SEC HYD LO PRES warning light illuminated.
A

SECONDARY HYDRAULIC (HYD 1) PRESSURE HIGH/LOW
=Hydraulics Section=
Corrective Action:
1. LANDING GEAR HANDLE - DOWN (wheels confirm down).

55
Q

Symptoms:

  1. SERVO JAM warning light illuminated.
  2. Flight control loading may increase.
A

SERVO JAM
=Hydraulics Section=

Corrective Action:
(non-memory)

=WARNING=
Subsequent seizing of the backup distributor valve will result in control lockup or uncontrollable handover (pitch, roll, or yaw).
=NOTE=
In certain conditions, the SERVO JAM warning may extinguish. This DOES NOT mean that the problem has cleared.

56
Q

Any ONE of the following Symptoms:

  1. HYD1 or HYD 2 pressure indication on VEMD goes to full scale, zero, or is blanked.
  2. PRI SERVO P warning light illuminated.
  3. SEC SERVO P warning light illuminated.
A

HYDRAULIC INDICATING SYSTEM FAILURE
=Hydraulics Section=
Corrective Action:
(non-memory)

57
Q

Symptoms:
1. AFCS pitch and roll disengaged.
2. Pilot and copilot ADIs failed.
3. Loss of cockpit instrument lighting.
4. Loss of all AC powered equipment.
5. STAT page FAIL line:
a. EGI, HDG 1, EGI 2, HDG 2 (EGIs are aligned and
working normally).
b. TACAN (provides distance only on BDI,
direction/distance on MFD bearing needles).

A 
DUAL AC BUS FAILURE
=Electrical Section=
Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
(continued non-memory)
58
Q

Possible Symptoms:
1. One 26 VAC FAIL light illuminated.
2. AFCS pitch and roll disengaged.
3. ADI failed on one side of the instrument panel.
4. All equipment on one main AC bus inoperative and/or loss of components powered by single phase 115 and 26 VAC from the respective transformer.
5. Alternator FAIL light illuminated.
6. BTC CLOSED light illuminated.
7. STAT page FAIL line:
a. EGI, HDG 1, EGI 2, HDG 2 (EGIs are aligned and
working normally).
b. TACAN (provides distance only on BDI,
direction/distance on MFD bearing needles)

A

AC SYSTEM FAILURE (MAIN AC BUS SHORT, ALTERNATOR, ALTERNATOR CONTROL UNIT (ACU), OR 115/26 VAC SYSTEM FAILURE)
=Electrical Section=
Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT.
2. 26 VAC XFER SWITCH - MOVE IN THE DIRECTION OF THE ILLUMINATED FAIL LIGHT.

=NOTE=
Components powered through the 115/26 VAC XFER relay may be recovered. Other 115 VAC components cannot be recovered including: No. 1 system {Pilot} - ECS, instrument lights; No 2. system {CP} - radar [26VAC antenna drive], instrument lights.

  1. AFCS - REENGAGE.
    (continued non-memory)
59
Q

Possible Symptoms:

  1. Loss of all equipment on one main DC bus…
  2. SERVO JAM, SEC HYD ISOLATE, and HEATER O/HEAT warning lights illuminated (No. 2 Pilot DC Bus Short only). Landing gear system will have hydraulic power and will extend normally with landing gear handle activation.
  3. Loss of radar display on MFD2 (No. 2 Pilot DC Bus Short only).
  4. Associated generator FAIL light illuminated.
  5. Associated battery relay OPEN light illuminated.
  6. See EGI FAILURE EP for additional symptoms due to loss of an EGI.
A 
MAIN DC BUS SHORT
=Electrical Section=
Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT.
2. AFFECTED AUDIO CONTROL PANEL(S) - ALTN (FM audio control panel to ALTN for No. 1 Copilot DC Bus Short)
3. AFCS GYRO SELECTOR SWITCH - MOVE IN THE DIRECTION OF THE OPERATING EGI
4. AFCS - REENGAGE.
(continued non-memory)
60
Q

Symptoms:

  1. Generator FAIL light illuminated.
  2. BTC CLOSED light illuminated.
A

GENERATOR FAILURE
=Electrical Section=
Corrective Action:
(non-memory)

61
Q

Possible Symptoms:

  1. BATT TEMP warning light illuminated.
  2. Smoke and/or fumes from radome or vent.
  3. Noises from radome.
A 
BATTERY OVER TEMPERATURE/THERMAL RUNAWAY
=Electrical Section=
Corrective Action:
1. BATTERY RELAY SWITCHES - BOTH OFF.
(continued non-memory)
WARNING
Securing the BATT RELAY switches WILL NOT stop or reverse a battery over temperature/thermal runaway.
62
Q

Symptom:

1. Both BATT RLY OPEN lights illuminated.

A

BATTERY BUS SHORT CIRCUIT
=Electrical Section=
Corrective Action:
(non-memory)

63
Q

Symptom:

1. One BATT RLY OPEN light illuminated.

A

BATTERY RELAY FAILURE
=Electrical Section=
Corrective Action:
(non-memory)

64
Q

Symptom:

1. ENG 1 FUEL P or ENG 2 FUEL P warning light illuminated.

A 
ENGINE FUEL PRESSURE LOW
=Fuel Section=
1. COMPLETE THE BIG 4
If ABNORMAL ENGINE indications:
2. FCS (affected engine) - CONFIRM; IDLE, CONFIRM; OFF.
(continued non-memory)
65
Q

Symtom:

1. FUEL FILT 1 and/or FUEL FILT 2 caution lights illuminated.

A 
FUEL FILTER CONTAMINATION
=Fuel Section=
Corrective Action:
If both FUEL FILTER caution lights illuminated:
1. LAND AS SOON AS POSSIBLE
(continued non-memory)
66
Q

Symtoms:

  1. FEED TANK 1 or FEED TANK 2 warning light illuminated with fuel indicated in the system.
  2. Caution/fuel page fuel boost pump pressure fluctuates, drops to zero, increases or decreases abnormally, or blanks with bold faced yellow type.
  3. FUEL PARAMETER OVERLIMIT on VEMD FLI if Caution/Fuel page is not displayed.
A 
BOOST PUMP/EJECTOR/INDICATOR FAILURE
=Fuel Section=
Corrective Action:
1. BOOST PUMPS (AFFECTED SYSTEM) - BOTH ON.
(continued non-memory)

=WARNING=
Due to potential for fire, do not reset boost pump circuit breakers

=CAUTION=
If operating above 8,000’ ft MSL both boost pumps shall be on to prevent a possible feed tank failure.

67
Q

Possible Symptoms:
1. Unable to transfer fuel from one system to the other.
2. Fuel XFER PUMP circuit breakers (2) popped (pilot aft panel R2 No. 11 and copilot panel R1 No. 3).
WARNING
Due to the potential for fire, do not reset fuel XFER PUMP circuit breakers.

A

FUEL TRANSFER PUMP FAILURE
=Fuel Section=
Corrective Action:
(non-memory)

68
Q

Symptom:

1. Fuel transferring to one side without apparent transfer pump activation.

A

UNCOMMANDED FUEL TRANSFER
=Fuel Section=
Corrective Action:
(non-memory)

69
Q

Symptom:

1. System indicator blanks, fails to change during flight, fluctuates, or reads 50% and 50% or 0% and 0%.

A

FUEL QUANTITY INDICATING SYSTEM FAILURE
=Fuel Section=
Corrective Action:
(non-memory)

70
Q

200’ CHECKS from memory:

A

WHEELS
NR/OEI
FLOATS
SLIDING DOOR

(we need to fuck sluts)

71
Q

The BOLD FACE steps for THE BIG 4 are:

A
  1. NR
  2. AIRSPEED/ALTITUDE
  3. WHEELS/FLOATS
  4. ANALYZE

The intent of the BIG 4 is for the pilot to state the steps, verbalize the intended target or desired state for that step, and complete the necessary procedure to stay within parameters.

72
Q

The 30-second OEI HI is automatically selected by the FADEC in any of the following malfunctions:

A

BACKUP mode selected on one engine
Major FADEC failure
Engine failure
N1 divergence of >6%

73
Q

If the TRNG switch is in IDLE and either engine is degraded, _______ is automatically selected by FADEC

A

2-min OEI LO

74
Q

=WARNING=

LOSS OF BOTH HYDRAULIC SYSTEMS WILL RESULT IN

A

LOSS OF AIRCRAFT CONTROL

75
Q

Above the unusable level, fuel will continue to enter the affected feeder tank via the flapper valve. At or below the unusable fuel level, illumination of the FEED TANK 1 or FEED TANK 2 warning light may means as little as _______ remaining before engine flameout.

A

5 MINUTES

76
Q

HIFR EMERGENCY BREAKAWAY

A
  1. CREW - ALERTED “BREAKAWAY, BREAKAWAY, BREAKAWAY.”
  2. EMERGENCY QUICK-DISCONNECT HANDLE - PULL

=CAUTION=
To prevent damage to the aircraft and a possible fuel spill, the hoist cable should not be sheared while the HIFR nozzle is connected. Use the emergency quick disconnect only during a HIFR EMERGENCY BREAKAWAY.

77
Q

Symptoms:

  1. AFCS caution light illuminated on the WCA panel
  2. AFCS pitch, roll, and yaw channels disengaged with AMAP channels flashing
  3. ATT flag visible and rate-of-turn pointer out of view on affected ADI.
  4. Red HDG failure flag on affected MFD (all display pages).
  5. Yellow CMW annunciation on the unaffected MFD.
  6. STAT page FAIL line: EGI2, HDG2
  7. FD UCPL on AMAP
  8. FD command bars/pointers disappear.
  9. Loss of AFCS HDG retention
  10. Invalid TACAN bearing indications
  11. Loss of radar stabilization
A

EGI FAILURE
[CP (EGI2) Failure]

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:

  1. FLIGHT CONTROLS - STABILIZE AIRCRAFT.
  2. EGI GYRO SELECTOR SWITCH - MOVE IN THE DIRECTION OF THE OPERATING EGI.
  3. AFCS PITCH AND ROLL - REENGAGE.

=NOTE=
The AFCS computer requires signals from both EGIs for YAW channel operation/engagement.

(continued non-memory)

78
Q

Symptoms:

  1. AFCS caution light illuminated on the WCA panel
  2. AFCS pitch, roll, and yaw channels disengaged with AMAP channels flashing
  3. ATT flag visible and rate-of-turn pointer out of view on affected ADI.
  4. Red HDG failure flag on affected MFD (all display pages).
  5. Yellow CMW annunciation on the unaffected MFD.
  6. STAT page FAIL line: EGI1, HDG1
  7. Invalid VOR indications (ILS/LOC not affected).
A

EGI FAILURE
[PILOT (EGI1) Failure]

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:

  1. FLIGHT CONTROLS - STABILIZE AIRCRAFT.
  2. EGI GYRO SELECTOR SWITCH - MOVE IN THE DIRECTION OF THE OPERATING EGI.
  3. AFCS PITCH AND ROLL - REENGAGE.

=NOTE=
The AFCS computer requires signals from both EGIs for YAW channel operation/engagement.

(continued non-memory)

79
Q

Symptoms:

  1. Uncommanded movement about the pitch and/or roll axis.
  2. Both ADIs do not indicate true aircraft attitude.
  3. ATT flags on both ADIs
  4. Red HDG failure flag on both MFDs (all display pages).
  5. STAT page FAIL line: EGI1, HDG1, EGI2, HDG2
A

DUAL EGI FAILURE

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
2. AFCS PITCH AND ROLL CHANNELS - DISENGAGE
(continued non-memory)

80
Q

Possible Symptoms:

  1. Affected FD command bar/pointer out of view
  2. FD flags on both ADIs
  3. Disparity between CP airspeed indicator and the MFD IAS readout with loss of turn coordination.
A

DETECTED FD FAILURE

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
(continued non-memory)

81
Q

Symptom:

1. Deviation of the aircraft from the desired flight path with FD command bar/pointer centered.

A

UNDETECTED FD FAILURE

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
(continued non-memory)

82
Q

Possible Symptoms:

  1. AFCS caution light illuminated.
  2. One or more AFCS channels disengaged with associated channel lights on AMAP flashing.
  3. P TRIM, R TRIM, or Y TRIM light may be illuminated on AMAP.
  4. TRIM OFF light may be illuminated.
A

AFCS COMPUTER OR SERIES ACTUATOR FAILURE

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
(continued non-memory)

83
Q

Symptoms:

  1. Uncommanded aircraft displacement
  2. P TRIM, R TRIM, or Y TRIM light illuminated on AMAP.
A

AFCS SERIES ACTUATOR HARDOVER (UNDETECTED) / PARALLEL SERVO HARDOVER

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:

  1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
  2. ACFS CHANNEL - DISENGAGE
84
Q

Possible Symptoms:

  1. Uncommanded collective movement during coupled FD operation when using a collective mode.
  2. Binding/resistance or inability to change collective position without FD modes engages.
A

COLLECTIVE PARALLEL SERVO HARDOVER OR FAILURE

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
1. COLLECTIVE - C-SYNC DEPRESS AND STABILIZE

(continued non-memory)

85
Q

Possible Symptoms:

  1. AFCS TRM OFF light illuminated on AMAP
  2. TRIM chevron extinguished on AFCS panel.
  3. P TRIM or R TRIM
A

AUTOMATIC TRIM FAILURE (AFCS ENGAGED)

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
(non-memory)

86
Q

Symptoms:

  1. Unable to trim aircraft using cyclic beep TRIM switch
  2. AFCS TRM OFF light illuminated on AMAP
  3. TRIM chevron extinguished on AFCS panel.
A

MANUAL TRIM FAILURE (AFCS DISENGAGED)

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
(non-memory)

87
Q

Possible Symptoms:
1. Unable to maintain cyclic stick positioning using cyclic SYNCH/TRIM RELEASE switch with overhead TRIM switch ON.

OR

  1. The cyclic has no artificial force feel (electromagnetic clutch disengaged).
A

CYCLIC ARTIFICIAL FEEL (FEEL/TRIM) FAILURE

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
(continued non-memory)

88
Q 
Possible Symptoms:
1. Undesired movement of the collective
2. RADALT cycles, freezes, or masks.
3. FD collective command pointer centered
4. Annunciation of check STATUS on CDU
5. STAT page FAIL line: RALT
...continued
A

RADAR ALTIMETER (RADALT) CYCLE OR FAILURE

=EGI, FLIGHT DIRECTOR, AND AFCS Section=

Corrective Action:
1. COLLECTIVE C-SYNC - DEPRESS AND STABILIZE

=WARNING=
During FD hover mode operation a RADALT cycle will be sensed as a climb with a corresponding reduction in collective and loss of altitude followed by a downward cycle of the indicator that will result in an increase in collective and possible overtorque.

89
Q

Symptoms:

  1. NO DATA annunciation on both CDUs or both screens frozen
  2. Loss of all avionics components except communication radios.
A

DUAL DATA BUS LOCKUP

=FMS and COMMS Section=

Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT

=WARNING=
Securing either AVIONICS switch will secure power to the respective EGI.

90
Q

Symptoms:

  1. Annunciation of check STATUS on CDU
  2. STAT page FAIL line: BUSA or BUSB
A

SINGLE DATA BUS FAILURE

=FMS and COMMS Section=

Corrective Action:
(non-memory)
=NOTE=
Loss of a single data bus will not impact FMS operation

91
Q

Possible Symptoms:
1. Loss of all avionics components on either the Pilot or Copilot Bus or loss of an entire Manual Shed DC Bus.

Copilot Bus:
AFCS
BDI
CDU2
COMM2
FDS
MDL
IFF
EHSI
DCP2
EGI2
SIU
TCN
A

SINGLE AVIONICS (ELECTRICAL) BUS FAILURE

=FMS and COMMS Section=

Corrective Action:

  1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
  2. AFCS GYRO SELECTOR SWITCH - MOVE IN THE DIRECTION OF THE OPERATING EGI
  3. AFCS PITCH AND ROLL - REENGAGE

=NOTE=
The AFCS computer requires signals from both EGIs for yaw channel operation/engagement.
(continued non-memory)

92
Q

Possible Symptoms:
1. Loss of all avionics components on either the Pilot or Copilot Bus or loss of an entire Manual Shed DC Bus.

PILOT Bus:
ADF
AFCS
EHSI
DCP1
CDU1
NAV (VOR)
RADALT
RRU
EGI1
SCC1
SIU
SATCOM
A

SINGLE AVIONICS (ELECTRICAL) BUS FAILURE

=FMS and COMMS Section=

Corrective Action:

  1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
  2. AFCS GYRO SELECTOR SWITCH - MOVE IN THE DIRECTION OF THE OPERATING EGI
  3. AFCS PITCH AND ROLL - REENGAGE

=NOTE=
The AFCS computer requires signals from both EGIs for yaw channel operation/engagement.
(continued non-memory)

93
Q 
Symptoms:
1. Loss of the following:
RADALT push-to-test
Low altitude warning tones
BDI functions
A

SIGNAL INTERFACE UNIT FAILURE

=FMS and COMMS Section=

Corrective Action:
(non-memory)

94
Q

Symptoms:
1. Affected CDU display blank (possible NO DATA or FUNCTION NOT AVAILABLE annunciation on CDU).

  1. CDU annunciations:
    check STATUS
    NO BINGO
  2. STAT page FAIL line: CDU1 or CDU2
  3. Loss of BINGO, RNG, and MRNG values on CDU
A

CONTROL DISPLAY UNIT (CDU) FAILURE {single}

=FMS and COMMS Section=

Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
(continued non-memory)

95
Q

Symptoms:
1. Both CDU displays blank (possible NO DATA or FUNCTION NOT AVAILABLE annunciation on CDU).

  1. All FMS information will be lost to MFDs
  2. Loss of RADALT low altitude warning tones and visual indications (i.e. 40- and 200-foot).

=NOTE=
NAVAIDS and Comms radios will remain tuned to last frequency
If power is regained after a dual CDU failure, IFF defaults to STBY
Radar scan-to-scan integration will be lost with a CDU1 failure.

A

CONTROL DISPLAY UNIT (CDU) FAILURE {dual}

=FMS and COMMS Section=

Corrective Action:
1. FLIGHT CONTROLS - STABILIZE AIRCRAFT
(continued non-memory)

USCG MH-65D ZDB (18 decks)

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