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MH-65E - EPs, Aero, SAR and STAN Checks > MH-65E EPs NOV 2020 > Flashcards

MH-65E EPs NOV 2020 Flashcards

1
Q

Two or more of the following symptoms:

  • Loss of MGB lubrication indicated on the EICAS page by
  • MGB OIL P
  • MGB PMP MAIN
  • MGB PMP AUX
  • MGB CHIP
  • Yaw kicks, abnormal MGB noises, or unusually high power requirements.
A

MGB FAILURE IMMINENT

=MGB Section=

Corrective Action:

  1. LAND/DITCH IMMEDIATELY

WARNING

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

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2
Q

One of the following symptoms:

  • Drop in MGB oil pressure indicated on the EICAS page by:
  • MGB OIL P
  • Low MGB oil pressure
  • Possible rise in MGB oil temperature
  • Loss of MGB lubication indicated on the EICAS page by:
  • MGB OIL P
  • MGB PMP MAIN
  • MGB PMP AUX
  • MGB oil pressure at zero
  • Possible rise in MGB oil temperature
  • MGB CHIP
  • MGB oil pressure greater than 80 psi
  • Abnormal MGB noises
A

MGB MALFUNCTION

=MGB Section=

Corrective Action:

Non-memory

NOTE

“flight…should be sustainable for ~25 mins”

“note and verbalize the flight regime, airspeed, and current torque setting”

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3
Q

Symptoms:

  • MGB PMP MAIN
  • MGB oil pressure decrease
  • MGB oil temperature increase
A

MGB PMP MAIN

=MGB Section=

Corrective Action:

Non-memory

Note

MGB lubication will continue via aux pump at lower pressure and without oil cooler.

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4
Q

Symptoms:

  • MGB OIL TEMP
  • Abnormal rise in MGB oil temperature
A

MGB OIL TEMP

-MGB Section-

Corrective Action:

Non-memory

NOTES

MGB overheat may not be evident over 120 KIAS

Operations at speeds below 120 KIAS may not provide adequate cooling

Minimize hovering and ground operations

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5
Q

Symptom:

  • MGB PMP AUX
A

MGB PMP AUX

-MGB Section-

Corrective Action:

Non-memory

NOTE

During normal operations, the aux pump of the MGB is not used for lubrication

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6
Q

Any one of the following symptoms:

  • MGB OIL P
  • MGB oil pressure in red or zero (May be accompanied by MGB exceedance in CDU due to shared transducer)
  • MGB OIL TEMP
  • MGB oil temperature in red or zero
A

MGB INDICATING SYSTEM FAILURE

-MGB Section-

Corrective Action:

Non-Memory

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7
Q

Symptom:

  • PFD TRQ exceeds 100%

Possible symptoms:

  • MGB QT captured on the CDU ASE ECMS EXCEEDANCE page
A

MGB OVERTORQUE

MGB Section

Corrective action:

Non-memory

Notes (more not listed)

  • If no MGB QT exceedance is captured…may proceed on the assigned mission
  • Verify magnitude of overtorque via the ECMS
  • Write up all overtorques, even those that don’t capture (flight regime, max TQ value, duration, pedal input)
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8
Q

Symptom:

  • MGB FIRE light illuminated

Possible symptoms:

  • Illumination of associated MGB related warnings and cautions
  • MGB OIL P
  • MGB OIL TEMP
  • MGB PMP MAIN
  • MGB PMP AUX
  • Loss of MGB oil pressure and/or rise in temperature
  • Drop in fuel and/or hydraulic pressure
  • AC electrical system malfunctions
A

MGB FIRE

-Fires section-

Corrective Action:

  1. CONFIRM FIRE

If fire confirmed:

  1. LAND/DITCH IMMEDIATELY

If fire not confirmed:

  1. LAND AS SOON AS POSSIBLE

Warning

  • Due to potential for fire near hydraulics, may result in loss of a/c control
  • Light may indicate fire, overheat, or short
  • Since to ability to fight fire in MGB, immediate action should be taken to confirm the fire
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9
Q

Symptoms:

  • Engine FIRE light illuminated
  • Red warning light illuminated on the corresponding EFSL
  • Flames and/or smoke coming from engine compartment

Possible symptoms:

  • ENG1 FUEL P, ENG2 FUEL P
  • ENG1 OIL P, ENG2 OIL P
  • ENG1 OIL TEMP, ENG2 OIL TEMP
  • ENG1 CHIP, ENG2 CHIP
  • Electrical system malfunctions
A

ENGINE COMPARTMENT FIRE INFLIGHT
-Fire section-
Corrective Action (affected engine):

  1. CONFIRM FIRE
    NOTE
    Due to engine location…turn to look for smoke
  2. SINGLE-ENGINE PROFILE-ESTABLISH

If fire confirmed (affected engine:

  1. FCS - CONFIRM; IDLE, CONFIRM; OFF
  2. EFSL - CONFIRM; OFF
  3. BOOST PUMPS - CONFIRM; OFF
  4. PRI FIRE EXTINGUISHER BUTTON - CONFIRM; PUSH

After 60 seconds:

  1. SEC FIRE EXTINGUISHER BUTTON - CONFIRM; PUSH

If fire still persists:

  1. LAND/DITCH IMMEDIATELY

If fire no longer evident:

  1. LAND AS SOON AS POSSIBLE

If fire not confirmed:

  1. LAND AS SOON AS PRACTICABLE

Warning

  • Potential loss of the airframe is not sufficient cause to continue flight
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10
Q

Symptoms:

  • Engine FIRE light illuminated
  • Hand or voice signals from ground crew
  • Red warning lighgt illuminated on the corresponding EFSL
A

ENGINE COMPARTMENT FIRE ONDECK

-Fires section-

Corrective Action:

  1. CONFIRM FIRE
  2. FCSs - OFF
  3. EFSLs - OFF
  4. BOOST PUMPS - OFF

If fire confirmed (affected engine:

  1. PRI FIRE EXTINGUISHER BUTTON - CONFIRM; PUSH
  2. SEC FIRE EXTINGUISHER BUTTON - CONFIRM; PUSH
  3. EMERGENCY ELECTRICAL CUTOFF
  4. ROTOR BRAKE
  5. EVACUATE
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11
Q

Symptoms:

  • Smoke/fumes/sparks originating from a single component inside the cabin
A

INTERNAL FIRE (CABIN, ELECTRICAL, AND/OR AVIONICS)

-Fires section-

Corrective Action:

1. CONFIRM/SURPRESS FIRE
2. AFFECTED EQUIPMENT - OFF
3. AFFECTED CIRCUIT BREAKERS - PULL
4. HEAT/COOL SWITCHES - OFF
5.RAM AIR, DOOR, WINDOW - CLOSED
6. WHEELS/FLOATS - AS REQUIRED

If electrical or avionics fire persists:

7. EMERGENCY ELECTRICAL CUTOFF

If electrical or avionics fire persists:

8. LAND/DITCH IMMEDIATELY

If fire goes out:

9. LAND AS SOON AS POSSIBLE

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12
Q

INTERNAL FIRE

NOTES WARNINGS CAUTIONS

A

Warnings:
(FLAT-C: Floats, lights, AFCS, tail hyd, Comms)**

  • If the crew determines the fire is in the avionics rack, pull the av rack blower circuit breaker (av rack R9 No.2)
  • The severity of the fire and actual flight conditions will dictate [whether to secure power; still have SFI but no AFCS or MFDs}..prior to reaching VMC
  • If you secure all power, you lose floats, ALL comms (internal/external) and will get considerable feedback in pedals. (FLAT-C: Floats, lights, AFCS, tail hyd, Comms)
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13
Q

SMOKE AND FUME ELIMINATION

A

SMOKE AND FUME ELIMINATION

-Fires section-

Corrective Action:

  1. HEAT/COOL SWITCHES - OFF
  2. RAM AIR, DOOR, WINDOW - OPEN

Continued non-memory

NOTES

Could use SEAS bottle

Objectionable odors might be experienced due to internal oil leaks; enter in ALMIS

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14
Q

Symptoms:

  • TOT rises rapidly after FCS has been placed in the OFF position
  • TOT does not decrease after FCS has been placed in the OFF position

NOTE

If the engine does not shutdown with FCS OFF, FADEC will shut down 5-6 seconds later [via stop electro valve].

After engine shutdown is complete, TOT may increase slowly due to temperature soak-back.

A

ENGINE POST-SHUTDOWN FIRE

-FIRES section-

Corrective action (affected engine):

  1. EFSL - CONFIRM: OFF

-CAUTION-

Operation of the crank button with the EFSL pulled will damage engine fuel pump

If high TOT still evident after 10 seconds:

2. CRANK BUTTON - DEPRESSS

If TOT continues to rise or does not decrease

3. EMERGENCY ELECTRICAL CUTOFF
4. ROTOR BRAKE
5. EVACUATE

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15
Q

Symptom:

  • Fire detector FAIL light illuminated
A

FIRE DETECTOR FAILURE
-Fires section-
Corrective Action:

Non-memory

NOTE

FAIL indicates an open circuit

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16
Q

Symptom:

  • L EXT or R EXT
A

L EXT or R EXT (FIRE SUPRESSION FAILURE)
-Fires section-
Corrective Action:

Non-memory

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17
Q

Symptom:

  • Known or suspected aircraft damage
  • Abnormal vibrations

WARNING

Known or suspected aircraft damge that appears minor on the surface may in fact involve structural or flight control components

NOTE

A reduction in airspeed between 75 to 100 KIAS may reduce vibrations

A

KNOWN OR SUSPECTED AIRCRAFT DAMAGE/ABNORMAL VIBRATIONS
-AIRCRAFT DAMAGE OR ABNORMAL VIBRATIONS section-
Corrective Action:

If severe vibrations and/or drastically altered flight characteristics:

1. LAND/DITCH IMMEDIATELY

WARNING

<span>The potential loss of the airframe…is not sufficient cause to continue flight</span>

If moderate vibrations:

**2. LAND AS SOON AS POSSIBLE
**
If slight vibrations of unknown origin or aircraft damage is known or suspected

  1. LAND AS SOON AS PRACTICABLE
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18
Q

Symptom:

  • Windscreen cracked
A

WINDSCREEN CRACKS

-AIRCRAFT DAMAGE OR ABNORMAL VIBRATIONS section-

Corrective Action:

Non-memory

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19
Q

Symptoms:

  • Any uncommanded left yaw not attributable to mechanical failure of the tail rotor drive system
A

UNCOMMANDED LEFT YAW

-MAIN/TAIL ROTOR section-

Corrective Action:

1. PEDALS - FULL RIGHT DEFLECTION

2. CYCLIC - FORWARD

3. COLLECTIVE - REDUCE

WARNING

Pulling collective at the bottom can could aggrevate or reinitiate ULY

4. NR - HI

NOTE

Consideration should be given to having PM switch to HI

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20
Q

Symptoms:

  • TGB CHIP
A

TGB CHIP

-MAIN/TAIL ROTOR section-

Corrective Action:

1. LAND AS SOON AS POSSIBLE

WARNING

Pilots shall establish a safe altitude and airspeed for possible loss of t/r thrust

NOTE

If accompanied by strong medium frequency vibes, plan your approach for possible loss of t/r thrust

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21
Q

Symptoms:

  • Immediate, rapid left yaw acceleration

Possible symptoms:

  • Tail rotor pedals movable without effect
  • Abnormal vibrations or noise from the tail section (loss of thrust or fixed pitch)
  • Cannot move pedals (fixed pitch)
A

LOSS OF TAIL ROTOR THRUST WHILE HOVERING

-MAIN/TAIL ROTOR section-

Corrective Action:

1. EFSLs - OFF

2. ATTITUDE (maintain landing attitude)

3. COLLECTIVE (cushion the landing)

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22
Q

Possible symptoms:

  • TGB CHIP
  • Uncommanded yaw to the left or right
  • Tail rotor pedals movable without effect (loss of thrust)
  • Abnormal vibration or noise from the tail section (loss of thrust or fixed pitch)
  • Cannot move pedals (fixed pitch)
A

LOSS OF TAIL ROTOR THRUST OR FIXED TAIL ROTOR PITCH IN FORWARD FLIGHT

-MAIN/TAIL ROTOR section-

Corrective Action:

Non-memory

WARNING

If no suitable landing site, might have to power-off autorotate

CAUTION

Changing NR to HI could exacerbate

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23
Q

POWERED LANDING WITH TAIL ROTOR MALFUNCTION

NOTES, WARNINGS, CAUTIONS

A

CAUTIONs

Excessive cyclic movement on deck…could cause rotor to contact turtle back, vert stabilizer

With collective up and little weight on the tires, light brake application could cause tire blowout/rapid reduction on collective will cause yaw to the right

NOTE

Differential braking may be used to steer

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24
Q

Symptom:

  • If NR >380 RPM (10 Hz chopped tone)
A

NR OVERSPEED

-MAIN/TAIL ROTOR section-

Corrective action:

Non-memory

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25
Q

Symptoms:

  • NR HI with NR switch in NORMAL
  • NR >365 RPM with the NR switch in NORMAL
A

NR HI MALFUNCTION

-MAIN/TAIL ROTOR section-

Corrective Action:

Non-memory

CAUTION

Extended operation above Vy could damage aircraft systems

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26
Q

Possible symptoms:

  • NR fluctuates abnormally or indicates zero
  • PRI NR FAIL
  • SEC NR FAIL
  • NR DISAGREE
  • Low NR audio may sound with an actual NR above 345 RPM
A

NR INDICATING SYSTEM MALFUNCTION

-MAIN/TAIL ROTOR section-

Corrective Action:

Non-memory

NOTE

Inaccurate NR audio tones may be provided if both sources fail

When AUTO is selected, CAAS will auto switch to secondary if pri fails

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27
Q

Symptoms:

  • Low NR aural warning
  • NR - Decaying
  • Engine out indications on the EICAS page
  • Engine parameters - Both engines decreasing
  • Possible right yaw
A

AUTOROTATION PROCEDURE

-ENGINES section-

Corrective Action:

1. NR

2. AIRSPEED

3. TURN

4. FLARE

5. COLLECTIVE

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28
Q

Symptoms:

  • FADEC 1 FAIL or FADEC 2 FAIL
  • Engine status light on overhead quadrant
  • PFD TRQ display switches to OEI GOV mode
  • Affected engine will not respond to collective movement due to fuel flow metering being frozen at the rate present when the FADEC failed
A

FADEC FAIL

-ENGINES section-

Corrective Action:

1. TRNG SWITCH - FLT

2. FADEC BACKUP SWITCH (affected engine) - CONFIRM; BACKUP

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29
Q

FADEC FAIL NOTES, WARNINGS, & CAUTIONS

A

Warnings

  • Rapid reduction of the collective with a FADEC 1 FAIL could overspeed N2& shutdown the engine
  • EBCAU operation [even an engine in TRNG IDLE] will cause N1 matching without regard to the opposite engine N1 setting

Note

  • While FADEC N1 matching is assured, there will be [lag]
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30
Q

Symptoms:

  • Aircraft ondeck in unsafe condition
A

ENGINE SHUTDOWN PROCEDURE ONDECK
-ENGINE section-
Corrective Action:

1. EFSLs - OFF

2. EMERGENCY ELECTRICAL CUTOFF

CAUTION

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

3. ROTOR BRAKE

4. EVACUATE

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31
Q

Possible symptoms:

  • FADEC 1 FAIL or FADEC 2 FAIL on TDL 1/2 page
  • Insufficient voltage (<17 VDC)
  • GOV LVL 1 or GOV LVL 2 on TDL 1/2 page
  • No rise in N1 and/or TOT within 10 seconds
  • TOT rises rapidly and/or appears that it will exceed 750*C (hot start) FADEC will automatically shut down the engine during start if TOT exceeds 840*C
  • The main rotor does not turn prior to 25% N1
  • The N2 exceeds NR
  • Engine does not reach 45% N1 by 30 seconds and is no longer accelerating
  • ENG 1 OIL or ENG 2 OIL P on the TDL 1/2 page and remains present at 70% N1
A

ENGINE START EMERGENCIES
-ENGINES section-
Corrective Action:

1. FCS - OFF

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32
Q

Possible symptoms:

  • DIF N1 aural warning
  • DIF N1
  • NR droop
  • Low NR aural warning
  • TRQ, TOT, N1, and N2 decreasing
  • PFD TRQ indications switch to OEI limits and scaling
  • Abnormal engine parameters
  • Red X displayed over engine parameters
  • As engine spools down, additional symptoms will become evident (e.g. generator failire, ENG 1 OIL P warning, ENG 2 OIL P warning, engine status lights on overhead quadrant)
  • ECS disengages
A

FLAMEOUT
-ENGINES section-
Corrective Action:
Non-memory - [BIG 4]

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33
Q

Symptoms:

  • ENG 1 CHIP or ENG 2 CHIP
A

ENG CHIP

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

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34
Q

Symptoms:

  • Loud noises from the engine area
  • N2 significant’y above NR
  • DIF N1 aural warning
  • DIF N1
  • NR droop
  • Low NR aural warning
  • TRQ, TOT, N1, and N2 decreasing
  • PFD TRQ indications switch to OEI limits and scaling
  • Abnormal engine parameters
  • Red X displayed over engine parameters
  • As engine spools down, additional symptoms will become evident (e.g. generator failire, ENG 1 OIL P warning, ENG 2 OIL P warning, engine status lights on overhead quadrant)
  • ECS disengages
A

ENGINE GEARBOX/OUTPUT SHAFT FAILURE

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTES

  • When N2 reaches 429 (+/-) RPM, the FADEC will operate the stop electrovalve via the BIM
  • The boost pumps on the failed engine side must be ON to drive the transfer ejectors
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35
Q

Possible symptoms:

  • ENG 1 OIL P or ENG 2 OIL P with the engine oil pressure decreasing or reading zero
  • Engine oil pressure fluctuates, increases, or decreases abnormally
  • Engine oil pressure less than 25 psi
  • Engine status light illuminated on overhead quadrant
A

ENG OIL P

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTE

  • Oil pump failure may be proceeded by an initial increase in pressure
  • The boost pumps on the failed engines must be ON to drive the transfer ejectors
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36
Q

Symptoms:

  • ENG 1 FUEL P or ENG 2 FUEL P
A

ENG FUEL P

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTE

  • The boost pumps on the failed engines must be ON to drive the transfer ejectors
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37
Q

Possible symptoms:

  • Popping or rumbling noises
  • TOT increases/fluctuates
  • TRQ and N1 decreases
  • Airframe vibration/shuddering
A

ENGINE SURGE OR COMPRESSOR STALL

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTE

  • The boost pumps on the failed engines must be ON to drive the transfer ejectors
  • If additional power is required for landing, the affected FCS may be switched to FLT position
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38
Q

Possible symptoms:

  • DIF N1
  • DIF N1 aural warning
  • NR droop
  • Low NR aural warning
  • PFD TRQ display switches to OEI GOV Mode
  • N1 difference between both engines is greater than 6%
  • CHK TORQUE advisory
A

N1 DIVERGENCE/PARTIAL POWER LOSS

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTES

  • 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
  • A CHK TORQUE advisory will appear when torque differential is > 7.5%- torque doubling of the higher value will display, possibly showing erroneous overtorque
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39
Q

Symptoms:

  • ENG 1 OIL TEMP or ENG 2 OIL TEMP and increase in corresponding engine oil temperature above 115*C
A

ENG OIL TEMP

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTE

  • If only one engine has an overheat condition, consider placing it in idle
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40
Q

Symptoms:

  • GOV LVL 2
A

GOV LVL 2

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

WARNING

  • A minor FADEC failure involving a loss of DECU crosstalk communication (BALAN.A) may result in NR stabilizing below 345 RPM. Collective reduction may not return NR to normal parameters; consider placing NR HI and performing a running landing

NOTE

  • Depending on the nature of the failure, the CDU ASE ECMS page may provide correct values for Q, TOT, or N1
  • FEDEC logic is designed to cancel the Training mode with a GOV LVL 2
  • If a GOV LVL 2 is visible, scroll to CDU ASE Engine Faults page to determine the status of the failure
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41
Q

Symptoms:

  • GOV LVL 1
A

GOV LVL 1

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTE

  • Level 1 FADEC failures may lead to erroneous Torque, TOT, or N1 indications while using the Training mode.
  • If a GOV LVL 1 is visible, the crew can scroll to the CDU ASE Engine Faults page to determine the status of the failure
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42
Q

Any one of the following symptoms:

  • Engine 1 or 2 oil pressure indication goes to full scale, zero, or displays red dashes in the engine data display on the EICAS page
  • Engine 1 or 2 oil temperature indication goes to full scale, zero, or displays red dashes in the engine data display on the EICAS page
  • ENG 1 OIL P or ENG 2 OIL P
  • ENG 1 OIL TEMP or ENG 2 OIL TEMP
A

ENGINE INDICATING SYSTEM FAILURE

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTE

  • Additional symptoms constitute secondary indications of a more serious malfunction and the appropriate emergency procedure should be followed
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43
Q

RESTARTING ENGINE INFLIGHT

A

RESTARTING ENGINE INFLIGHT

-ENGINES section-

Corrective Action:

Non-memory - [BIG 4]

NOTE

  • If time allows, wait 30 seconds before attempting a restart
  • The boost pumps on the failed engine must be ON to drive the ejectors
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44
Q

Symptoms:

  • P TRIM, R TRIM, or Y TRIM
  • Uncommanded aircraft displacement
A

AFCS SERIES ACTUATOR HARDOVER/PARALLEL SERVO HARDOVER

-AUTOMATIC FLIGHT CONTROL SYSTEM Section-

Corrective action:

Non-memory

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45
Q

Possible symptoms:

  • PRI SERVO P
  • SERVO JAM
  • SERVO LIMIT
  • LIMIT lights illuminated (may not illuminate during reduced power flight)
  • PRI HYD pressure <720 psi or >986 psi on the EICAS page (yellow or red)
  • High-pitched noise from transmission area
  • Stiffness in flight controls
A

PRIMARY HYDRAULIC (PRI HYD) SYSTEM MALFUNCTION

-HYDRAULICS section-

Corrective Action:

Non-memory

WARNING

  • Failiure of both hydraulic systems will result in loss of a/c control

CAUTIONS

  • Cruise airspeed 75-100 KIAS
  • The Primary Regulation Manifold has a pressure relief valve of 1,305 psi to keep below servo design limit of 1,523
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46
Q

Possible symptoms:

  • SEC SERVO P
  • SEC HYD LO P
  • SERVO JAM
  • SEC HYD ISOLATE (if low fluid condition exists)
  • SEC HYD pressure <720 psi or >986 psi on the EICAS page (yellow or red)
  • High-pitched noise from transmission area
  • Stiffness in flight controls
  • Feedback in pedals
A

SECONDARY HYDRAULIC (SEC HYD) SYSTEM MALFUNCTION

-HYDRAULICS section-

Corrective Action:

Non-memory

1 Warning - Loss of a/c control

2 Cautions -

  • 75-100 KIAS
  • removing power to 2,000-psi opens the valve

2 Notes

  • Reasons for TAIL HYD ISO switch to be off
  • BLT are lost, along with elec power to hoist
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47
Q

SECONDARY HYDRAULIC (SEC HYD) SYSTEM MALFUNCTION WARNINGS, NOTES, & CAUTIONS

A

WARNING:

  • Failure of both hydraulic systems will result in loss of a/c control
  • Running electric pump too long could cause a fire

CAUTIONS:

  • Cruise airspeed 75-100 KIAS
  • Pulling the SEC HYD circuit breaker secures power to 2,000-psi isolation valve, opening it

Notes:

  • You lose BLT, left body of tail rotor servo, and electrical power to the hoist
  • Placing TAIL HYD ISOLATE switch to CUTOFF prevents further loss of fluid caused by:
  • dynamic attitudes
  • residual fluid from emergency blow down
  • Also prevents accidental gear retraction
  • Blow down will cause burning electrical smell
  • You shouldn’t lose TALON accumulator pressure when lowering gear in isolate condition
48
Q

SECONDARY HYDRAULIC (SEC HYD) SYSTEM MALFUNCTION WARNINGS, NOTES, & CAUTIONS +PROMPTS ONLY+

A

WARNING:

  • Loss of a/c control
  • Fire

CAUTIONS:

  • 75-100 KIAS
  • 2,000 opens

Notes:

  • BLT & E Hoist
  • TAIL HYD ISO
  • TALON
49
Q

Any one of the following symptoms:

  • SEC HYD HI P
  • SEC HYD LO P
A

SEC HYD HI/LO P

-HYDRAULICS section-

Corrective Action:

Non-memory

Note

  • Rescue hoist will be slow with reduction in system pressure
  • Remaining brake pressure will be indicated on accumulator pressure gauge
50
Q

Symptoms:

  • SERVO JAM
  • 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 uncontrollable control hardover/lockup

Note

  • The SERVO JAM may clear with change in flight; does not mean the problem has cleared.
51
Q

Any ONE of the following symptoms:

  • PRI/SEC HYD PRESSURE indications on the EICAS page go to full scale, zero, or are blanked.
  • PRI SERVO P
  • SEC SERVO P
A

HYDRAULIC INDICATING SYSTEM FAILURE

-HYDRAULICS section-

Corrective Action:

Non-memory

52
Q

Symptoms:

  • Loss of all AC powered equipment
  • All MFDs failed
  • Both alternator FAIL lights illuminated
  • Loss of cockpit instrument lighting
  • GPPU1 and GPPU2 (PSM) failed
  • VPM failed
  • AFCS pitch and roll channels disengaged
  • ECS inoperattive
A

TOTAL LOSS OF AC ELECTRICAL POWER

-ELECTRICAL SYSTEM section-

Corrective Action:

1. TRANSFER SCAN TO SFI - AS REQUIRED

53
Q

Symptoms:

  • BATT TEMP
  • SFI Battery FAULT light
  • Smoke and/or fumes from radome or vent
  • Noises from radome
A

BATTERY OVERTEMPERATURE

(AIRCRAFT OR SFI)

-ELECTRICAL SYSTEM section-

If the BATT TEMP is present

Corrective Action:

1. BATT RELAY SWITCHES - BOTH OFF

2. SFI ACFT - OFF

If BATT TEMP is not present and the SFI FAULT light is illuminated with smoke from radome

3. SFI BATT AND ACFT - OFF

If symptoms persist

4. LAND AS SOON AS POSSIBLE

54
Q

BATTERY OVERTEMPERATURE

(AIRCRAFT OR SFI)

NOTES, WARNINGS, & CAUTIONS

A

WARNING

  • Securing the BATT RELAY switches will not stop or reverse thermal runaway
  • Don’t direct CO2 into battery compartment

CAUTION

  • If BATT TEMP warning is no longer displayed, BATT RELAY switches should remain off unless battery power is absolutely necessary

Note

  • In the event of a dual generator failure, the T/R cannot power either DC bus with the batter switches OFF
  • A No. 2 DC generator failure with the No. 2 BATT RELAY switch off will create a SEC HYD ISOLATE condition/feedback in pedals
  • The backup battery will power the SFI for a minimum of 30 minutes
55
Q

Possible symptoms:

  • Alternator FAIL light illuminated
  • Loss of MFDs No. 1 and 3 or No.2 and 4
  • 26 VAC FAIL 1 or 26 VAC FAIL 2
  • 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
A

AC BUS SHORT

-ELECTRICAL SYSTEMS section-

Corrective action

Non-memory

WARNING

  • Resetting AC circuit breakers carries significant risk of fire and should not be attempted
56
Q

TOTAL LOSS OF AC ELECTRICAL POWER
NOTES, WARNINGS, CAUTIONS

A

WARNING

  • Resetting AC system circuit breakers carries a significant risk of igniting an electrical fire

CAUTION

  • As a result of losing all MFDs, RADALT tones will be lost

Note

  • Engine torque and NR available on CDU ECMS page
  • Barometric altimeter and RADALT can be read on CDU PROG page 2/3
  • If the two AC systems did not fail concurrently, attempt to recover LAST system to fail first; if unknown, go 1 > 2.
57
Q

Possible symptoms:

  • Associated generator FAIL light illuminated
  • Associated battery relay OPEN light illuminated
  • Loss of all equipment on one main DC bus
  • Copilot CCP inoperative for No. 1 Copilot DC BUS Failure and Pilot CCP inoperative for No. 2 Pilot DC BUS Failure
  • Laundry list of EICAS/MFD fail indications
A

DC BUS SHORT

-ELECTRICAL SYSTEMS section-

Corrective action

Non-memory

WARNING

  • A loss of No. 1 Copilot DC Bus will cause an unrecoverable loss of the transponder

Notes

  • A loss of No. 2 Pilot DC Bus will result in considerable feedback in the pedals due to the TAIL HYD ISOLATE condition
  • A loss of No. 1 Copilot DC Bus will result in loss of cyclic artificial feel
  • When in EGI REV, the aircraft may not properly respond to FD steering commands due to reduced series actuator authority
  • The AFCS computer requries signals from both EGIs for YAW channel
58
Q

Possible symptoms:

  • TRM OFF
  • P TRIM, R TRIM, or Y TRIM
  • TRIM chevron illuminated on AFCS control panel
  • Unable to trim aircraft using cyclic beep TRIM switch
A

AUTOMATIC TRIM FAILURE (MANUAL/AUTOMATIC)

-AUTOMATIC FLIGHT CONTROL SYSTEM Section-

Corrective action:

Non-memory

Note

  • Loss of power to the AFCS computer will result in trim failure
  • If using the FD, trim in the direction of attitude command displacement on the ADI.
  • If the Y TRIM caution remains on the EICAS page, the pedals should be adjusted to extinguish it.
59
Q

DC BUS SHORT

NOTES, WARNINGS, & CAUTIONS

A

WARNING

  • A loss of No. 1 Copilot DC Bus will cause an unrecoverable loss of the transponder

Notes

  • A loss of No. 2 Pilot DC Bus will result in considerable feedback in the pedals due to the TAIL HYD ISOLATE condition
  • A loss of No. 1 Copilot DC Bus will result in loss of cyclic artificial feel
  • When in EGI REV, the aircraft may not properly respond to FD steering commands due to reduced series actuator authority
  • The AFCS computer requries signals from both EGIs for YAW channel
60
Q

Symptom:

  • Both BATT RLY OPEN lights illuminated
A

BATTERY BUS SHORT

-ELECTRICAL SYSTEMS section-

Corrective action

Non-memory

61
Q

Symptom:

  • One BATT RLY OPEN light illuminated
A

BATTERY RELAY FAILURE

-ELECTRICAL SYSTEMS section-

Corrective action

Non-memory

Note

  • A battery start of the corresponding engine will not be possible until the fault is corrected.
62
Q

Possible symptoms:

  • FUEL FILT 1
  • FUEL FILT 2
A

FUEL FILT

-FUEL section-

Corrective action

If FUEL FILT 1 and FUEL FILT 2:

1. LAND AS SOON AS POSSIBLE

Continued non-memory

CAUTION

  • Unles absolutely necessary, do NOT transfer fuel
  • The FUEL FILT light indicates pressure differential. A reduction in power demand may clear light; does not indicate problem has been corrected.
63
Q

Symptoms:

  • 26 VAC FAIL 1 or 26 VAC FAIL 2
  • AFCS
  • PITCH and ROLL (with associated channels disengaged)
A

26 VAC FAIL

-ELECTRICAL SYSTEMS section-

Corrective action

Non-memory

WARNING

  • Resetting AC circuit breakers carries significant risk of fire and should not be attempted
64
Q

Symptoms:

  • Generator FAIL light illuminated
  • BTC CLOSED light illuminated
A

GENERATOR FAILURE

-ELECTRICAL SYSTEMS section-

Corrective action

Non-memory

WARNING

  • The loadmeter should be monitored for BOTH generators; a failed generator presents a potential fire hazard

Note

  • A single generator or the emergency T/R in the event of a dual generator failure can provide normal DC power requirements
65
Q

Symptoms:

  • Unable to transfer fuel from one system to the other
  • Fuel XFER PUMP circuit breakers (2) popped (pilot aft panel R2 No. 11 and copilot panel R1 No. 3)
A

FUEL TRANSFER PUMP FAILURE

-FUEL section-

Corrective action

Non-memory

WARNING

  • Due to potential for fire, do not reset fuel XFER PUMP circuit breakers
66
Q

Possible symptoms:

  • SFI battery FAULT light illuminated
  • SFI battery ON light illuminated
A

SFI BATTERY FAULT/ON

-ELECTRICAL SYSTEMS section-

Corrective action

Non-memory

CAUTION

  • When powered only by the SFI standby battery as indicated by the SFI battery ON light, a minimum of 30 minutes of SFI operations remain
67
Q

Symptoms:

  • FEED TANK 1 or FEED TANK 2 with fuel indicated in the system
  • The EICAS and TDL page fuel boost pump pressure fluctuates, drops to zero, increases or decreases abnormally, or displays red dashes in the digital display
  • L BOOST PUMP or R BOOST PUMP P
A

BOOST PUMP/EJECTOR/INDICATOR FAILURE

-FUEL section-

Corrective action

Non-memory

WARNING

  • Due to the potential for fire, do not reset boost pump circuit breakers

CAUTION

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

Notes

  • In the left system, the unusable fuel may be as much as 280 lbs, and in the right system as much as 60 lbs
  • Above unusable fuel, fuel can still enter the feed tanks via their flapper valve. At or below the unusable fuel level, the FEED TANK1 or FEED TANK 2 warning may mean as little as 5 minutes remaining before flameout.
  • FEED TANK 1 or FEED TANK 2 warning may not illuminate at high fuel levels.
  • Illumination of FEED TANK 1 or FEED TANK 2 warning lights during a crosswind hover may indicate leaking feed tank covers. If the lights can be extinguished by leveling the aircraft, the mission may be completed. Note symptoms and a/c attitude in ALMIS.
68
Q

Symptoms:

  • The EICAS page FUEL QTY 1, FUEL QTY 2, or TOTAL does not indicate as expected, blanks, or dashes out
A

FUEL QUANTITY INDICATING SYSTEM FAILURE

-FUEL section-

Corrective action

Non-memory

Note

  • All CAAS performance numbers incorporating fuel quantity (aircraft weight, bingo, torque margin, max range, etc.) will be affected in the event of a fuel quantity indicating system failure
69
Q

Symptoms:

  • Fuel transferring to one side without apparent transfer pump activation
A

UNCOMMANDED FUEL TRANSFER

-FUEL section-

Corrective action

Non-memory

70
Q

FUEL JETTISON PROCEDURE

NOTES, WARNINGS, CAUTIONS

A

FUEL JETTISON PROCEDURE

-FUEL section-

Corrective action

Non-memory

Note

  • All CAAS performance numbers incorporating fuel quantity (aircraft weight, bingo, torque margin, max range, etc.) will be affected in the event of a fuel quantity indicating system failure
71
Q

BOOST PUMP/EJECTOR/INDICATOR FAILURE

NOTES, WARNINGS, AND CAUTIONS

A

WARNING

  • Due to the potential for fire, do not reset boost pump circuit breakers

CAUTION

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

Notes

  • In the left system, the unusable fuel may be as much as 280 lbs, and in the right system as much as 60 lbs
  • Above unusable fuel, fuel can still enter the feed tanks via their flapper valve. At or below the unusable fuel level, the FEED TANK1 or FEED TANK 2 warning may mean as little as 5 minutes remaining before flameout.
  • FEED TANK 1 or FEED TANK 2 warning may not illuminate at high fuel levels.
  • Illumination of FEED TANK 1 or FEED TANK 2 warning lights during a crosswind hover may indicate leaking feed tank covers. If the lights can be extinguished by leveling the aircraft, the mission may be completed. Note symptoms and a/c attitude in ALMIS.
72
Q

Symptoms:

  • Attitude and heading disappear from both PFDs
  • Loss of position and ACP information

EICAS Page:

  • AFCS
  • PITCH, ROLL, and YAW (with associated channel disengaged)
  • NAV FAIL
  • vLRU STAT

MFD STAT Page:

  • EGI1 and EGI2
  • GPS1 and GPS2
  • INU1 and INU2
A

DUAL EGI FAILURE

-CAAS Section-

Corrective action:

If VMC cannot be maintained:

1. TRANSFER SCAN TO SFI - AS REQUIRED

Continued non-memory

73
Q

DUAL EGI FAILURE

NOTES, WARNINGS, CAUTIONS

A

-CAAS Section-

Notes

  • VOR, TAC, and DF needles still work on MFD NAV
  • Fly straight and level during in-motion alignment
  • ENABLE NAV may be selectable prior to INU NAV READY annunciation on EICAS
  • When in EGI REV, the FD directed series actuators have reduced authority
  • AFCS computer neeeds both EGIs for yaw
  • Hardover protection is not possible during EGI REV operations
74
Q

Symptoms:

  • CDU1 and CDU2 inoperative

EICAS Page:

  • GOV LVL 2, ENG PARM DEGR, vLRU STAT, GUIDE MODE OFF, NO NAV DB1, and NO NAV DB2

MFD STAT Page:

  • CDU1, CDU2, ADC1, ADC2, AMS, VPM, and NAV/COMM
  • Loss of flight manager (flight plan management, flight plan guidance, NAV radio/sensor control, NAV database management, PERF computations)
  • ADC, RALT, and TCAS fail indications
  • Red dashes in PFD TQ, NR, and EICAS engine data
A

DUAL CDU FAILURE

-CAAS Section-

Corrective action:

Non-memory

Note

  • COMM and NAV radios will remain tuned to the frequencies in use when dual CDU failure occured.
75
Q

Symptoms:

  • CDU1 or CDU2 inoperative

EICAS Page:

  • GOV LVL 2, ENG PARM DEGR, vLRU STAT, NO NAV DB1, or NO NAV DB2

MFD STAT Page:

  • CDU1 or CDU2
  • ADC1 or ADC2

Possible symptom:

  • FD Modes disengaged
A

SINGLE CDU FAILURE

-CAAS Section-

Corrective action:

Non-memory

76
Q

Symptoms:

  • Affected side PFD cross side source indicator displayed if other EGI source is valid

EICAS Page:

  • AFCS
  • PITCH, ROLL, and YAW
  • EGI1 NAV FAIL or EGI1 NAV FAIL
  • GPS1 NAV FAIL or GPS2 NAV FAIL
  • vLRU STAT

MFD STAT Page:

  • EGI1 and EGI2
  • GPS1 and GPS2
  • INU1 and INU2
A

SINGLE EGI FAILURE

-CAAS Section-

Corrective action:

Non-memory

77
Q

SINGLE EGI FAILURE

NOTES, WARNINGS, CAUTIONS

A

-CAAS Section-

CAUTION

  • Pulling the wrong EGI circuit breaker will induce a dual EGI failure

Notes

  • AFCS computer neeeds both EGIs for yaw
  • When in EGI REV, the FD directed series actuators have reduced authority
  • Fly straight and level during in-motion alignment
  • ENABLE NAV may be selectable prior to INU NAV READY annunciation on EICAS
  • INU NAV READY annunciation may not display on EICAS. Once INUs are aligned and the EGIs sense motion, CAAS will automatcially switch to NAV Mode.
  • Hardover protection is not possible during EGI REV operations
78
Q

Possible symptoms:

  • Blank, distorted, or display lockup of affected MFDs

EICAS Page:

  • vLRU STAT

MFD STAT Page:

  • MFD1, DP1, and MP1
  • MFD2, DP2, and MP2
  • MFD3, DP3, and MP3
  • MFD4, DP4, and MP4

If MFD 1 and MFD4 (both system manaders) are failed:

  • All AMS and MSN LRUs in white on MFD STAT page
  • CDU STAT, SNSR, Index-Power, FD, Data Load, EMCON, and Timers are unavailable
  • FD command bars removed from PFD
  • Blue Lines through all FD mode selections on MFD NAV page.
A

MFD FAILURE

-CAAS Section-

Corrective action:

Non-memory

79
Q

MFD FAILURE

NOTES, WARNINGS, CAUTIONS

A

-CAAS Section-

Notes

  • If failure of MFD1/4 occurs inflight, MFD2/3 automatically displays the PFD. In both cases, EICAS will display FD DISAGREE
  • With an MFD1 and MFD4 failure, the FD modes will disengage fully (both visually on the PFD and commanded via the FD manager).
80
Q

Possible symptoms:

  • Loss of all FD cues

PFD Page:

  • HDG goes from magnetic to true
  • Loss of bearing needles
  • Loss of RADALT
  • Loss of NR indications
  • Loss of TRQ indications
  • All items on MFD STAT page white
A

DUAL GPPU FAILURE

-CAAS Section-

Corrective action:

Non-memory

Note

  • Engine torque can still be monitored on the CDU ECMS page.
81
Q

Symptoms:

  • vLRU STATUS

MFD STAT Page:

  • GPPU1, PSM1, DTU or
  • GPPU2, PSM2, DTU

Possible symptoms:

  • Loss of FD cues
A

SINGLE GPPU FAILURE

-CAAS Section-

Corrective action:

Non-memory

Note

  • During a GPPU1 failiure, BALT and HDG modes may disengage as EICAS switches DECU reference from LAN A to LAN B. Once DECU reference is switched over, BALT and HDG can be reengaged.
  • To restore map data on the side with the failed GPPU, select map data from the side with the operating GPPU.
82
Q

Symptoms:

  • vLRU STATUS
  • MSN CARD?

MFD STAT Page:

  • DTU
A

DTU FAILURE

-CAAS Section-

Corrective action:

Non-memory

83
Q

Possible Symptoms:

MFD STAT page:

  • DCU1 and DCU2
  • ADC1 and ADC2
  • TCAS
  • IFF
  • TACAN
  • EGI1 and EGI2
  • INU1 and INU2

PFD page:

  • Pitch and collective FD cues disappear
  • Loss of NR indication

EICAS page:

  • IFF/M4
  • IFF/M5
  • GOV LVL 1
  • AFCS
  • BINGO FUEL
  • vLRU STATUS
  • FD UCPL
  • GUID MODE OFF
  • Loss of all ENG and MGB pressure readings and temperature indications
  • Loss of volt meter indications
  • Loss of HYD pressure indications
  • Loss of fuel quantity indications
A

DUAL DCU FAILURE

-CAAS Section-

Corrective action:

Non-memory

84
Q

DUAL DCU FAILURE

NOTES WARNINGS CAUTIONS

A

Note

  • Any analog signal that would normally trigger an EICAS advisory (warning, caution, or advisory) will be inoperative or fail. For instance, AFCS will show disengaged on EICAS, but the AFCS panel will show engaged and is fully functional.
85
Q

Symptoms:

EICAS page:

  • vLRU STATUS

MFD STAT page:

  • DCU1, ADC1 or DCU2, ADC2

Note

  • The ADCs provide data both directly to the MFDs (for PFD information) and to the CDUs (via the DCUs). Therefore, the MFD STAT page will display the ADC as failed (because of a break in the connection between the CDU and ADC) when the DCU fails, although valid ADC data is being displayed on the PFD.

If the FLT XFER is on the same as the failed DCU:

  • FD modes disengaged.

Note

  • All FD modes can be regained when flight transfer moved to the side of the operating ADC.
A

SINGLE DCU FAILURE

-CAAS Section-

Corrective action:

Non-memory

86
Q

Symptoms:

  • Loss of airspeed, BARALT, and TCAS indications on PFD
  • ADC1 and ADC2 on PFDs

EICAS page:

  • GUIDANCE MODE OFF
  • vLRU STATUS

MFD STAT page:

  • ADC1 and ADC2
A

DUAL ADC FAILURE

-CAAS Section-

Corrective action:

Non-memory

87
Q

Symptoms:

  • Yellow ADC cross-side source indicator on PFDs
  • vLRU STATUS

MFD STAT page:

  • ADC1 or ADC2
A

SINGLE ADC FAILURE

-CAAS Section-

Corrective action:

Non-memory

88
Q

Possible symptoms:

  • Erratic or erroneous barometric altimeter indications on any PFD or the SFI
  • Erratic or erroneous airspeed indications on any PFD on the SFi

EICAS page:

  • ALT DISAGREE
  • A/S DISAGREE

Note

  • The Flight Director utilizes ADC inputs from the ADC selected on the side with FLT XFER.
A

PITOT STATIC SYSTEM FAILURE

-CAAS Section-

Corrective action:

Non-memory

Note

  • Static port blockage could be an indication of airframe icing.
  • If both static ports are suspected blocked, the crew can elect to switch the static bypass switch in the cabin on the upper left of avionics rack. This removes normal static pressure inputs to the pilots ADC (ADC2) and sends cabin internal pressure to ADC2.
89
Q

Possible symptoms:

  • vLRU STATUS on the EICAS page
  • STAT page - any of the components show a failed or unknown status
  • Loss of associated component
A

INDIVIDUAL COMPONENT FAILURES

-CAAS Section-

Corrective action:

Non-memory

90
Q

Possible symptoms:

  • SFI attitude differs from the PFD attitude
  • Red X on SFI attitude, altitude, or heading display
  • Airspeed, altitude, or heading differ from PFD
A

SFI FAILURE

-CAAS Section-

Corrective action:

Non-memory

Note

  • Allow 60 to 90 seconds for the SFI to complete the alignment process. Straight and level unaccelerated flight should be maintained for the duration of the alignment process.
  • The SFI is required for all IMC flight operations.
91
Q

Possible symptoms:

  • AFCS
  • PITCH, ROLL, YAW, and COLL (with associated channel disengaged)
  • TRIM OFF
  • FD UCPL
  • Voice alert, “FLIGHT DIRECTOR UNCOUPLED” once
A

AFCS SERIES ACTUATOR OR COMPUTER FAILURE

-AUTOMATIC FLIGHT CONTROL SYSTEM Section-

Corrective action:

Non-memory

92
Q

AFCS SERIES ACTUATOR OR COMPUTER FAILURE
NOTES, WARNINGS, CAUTION

A

Note

  • The pitch and roll channels are redundently powered from the left (No. 1 copilot) and right (No. 2 pilot) main DC buses. The yaw and collective channels are only powered from the right (No. 2 pilot) main DC bus. Pulling the pilot aft AFCS circuit breaker will result in loss of the yaw and collective channels in addition to those already failed.
  • After channel disengagement, continued illumination of P TRIM, R TRIM, or Y TRIM cautions indicates the respective series actuator is not centered and the associated flight control (cyclic or pedals) will be displaced. The result may be reduced control authority. The AFCS is unable to execute FD commands in disabled channels.
93
Q

Possible symptoms:

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

COLLECTIVE PARALLEL SERVO HARDOVER OR FAILURE

-AUTOMATIC FLIGHT CONTROL SYSTEM Section-

Corrective action:

Non-memory

WARNING

  • Depending on the extent of the parallel servo failure, the collective may require significant force to change positioning or collective movement may not be possible.
94
Q

Possible symptoms:

  • Unable to maintain cyclic stick positioning using cyclic SYNC/TRIM RELEASE switch with overhead TRIM switch ON.

OR

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

CYCLIC ARTIFICIAL TRIM FAILURE (FEEL/TRIM) FAILURE

-AUTOMATIC FLIGHT CONTROL SYSTEM Section-

Corrective action:

Non-memory

CAUTION

  • Without the electromagnetic clutches of the feel/trim units engaged, the AFCS and FD are ineffective in pitch and roll. If FD usage is necessary, the crew may elect to pull the feel trim circuit breaker (pilot aft panel R2 No. 8), effectively removing power and placing the cyclic artificial feel trim in its engaged failed safe position. The FD will then have the ability to drive the pitch and roll channels.
95
Q

PRIMARY HYDRAULIC (SEC HYD) SYSTEM MALFUNCTION WARNINGS, NOTES, & CAUTIONS

A

WARNING:

  • Failure of both hydraulic systems will result in loss of a/c control

CAUTIONS:

  • Cruise airspeed 75-100 KIAS is recommended to reduce control loading
  • The Primary Regulation Manifold has a pressure relief valve to limit pressure to 1,305 psi (below the servo design limit of 1,523psi). If the relief valve fails, it will manifest as excessive pressure on the EICAS page.
96
Q

Possible symptoms:

  • Voice alert, “RADALT FAIL” continuously repeats
  • Undesired movement of the collective
  • RADALT is failed appears on both PFDs
  • RALT annunciation on MFD STAT page
A

RADAR ALTIMETER CYCLE OR FAILURE

-AUTOMATIC FLIGHT CONTROL SYSTEM Section-

Corrective action:

Non-memory

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 downwind cycle of the indicator that will result in an increase in collective and possible overtorque.
97
Q

Possible Symptoms:

  • Complete loss of audio (all stations)
  • VOX inoperative on all stations
  • No radio transmit capability
  • ICU failure light on all LPCAPs
  • Constant squeal or hum heard in headset

MFD STAT page:

  • CAP1, CAP2, CAP3, CAP4

EICAS page:

  • Check LRU STATUS
A

ICU FAILURE

-COMMUNICATION SYSTEM Section-

Corrective action:

Non-memory

NOTE

In the backup mode, the pilot can only transmit on CM1 and the copilot can only transmit on HF.

98
Q

Possible Symptoms:

  • Loss of transmit and/or receive capability from one crew station
  • Loss of normal digital ICS functions from one crew station

MFD STAT page (one of the following):

  • CAP1, CAP2, CAP3, CAP4
A

LPCAP FAILURE

-COMMUNICATION SYSTEM Section-

Corrective action:

Non-memory

NOTE

In the backup mode, the pilot can only transmit on CM1 and the copilot can only transmit on HF.

99
Q

Possible Symptoms:

  • Annunciation of Check STATUS on EICAS
  • Loss of transmit/receive capability
  • NO GO on CDU STAT page for failed system
  • Failed system displayed in red on MFD STAT page
  • Check mark next to failed radio on CDU SNI COMMS page
A

TRANSMITTER AND RECEIVER FAILURE

-COMMUNICATION SYSTEM Section-

Corrective action:

Non-memory

NOTE

A failure of only the FM or COMM2 data bus converter unit will result in the inability to change the existing frequency

100
Q

Possible Symptoms:

  • Lateral vibration when performing run on/off maneuvers or during high-speed taxiing, these vibrations may be quite violent
A

NOSEWHEEL SHIMMY DAMPER FAILURE

-LANDING GEAR Section-

Corrective action:

  1. LIFT AIRCRAFT OFF GROUND IMMEDIATELY OR REDUCE TAXI SPEED

CAUTION

Excessive aft cyclic movement on touch down or after landing can cause rotor head to contact the turtle back cowling, the tail stinger to contact the ground, and/or the main rotor blades to contact the vertical stabilizer.

101
Q

Possible Symptoms:

  • Amber light or absence of green lights on landing gear indicator with landing gear handle in down position
  • Gear visually checked not in down position
  • Blue landing gear down light not illuminated
  • LDG LOCK advisory not displayed on the EICAS page
A

WHEELS FAIL TO EXTEND

-LANDING GEAR Section-

Corrective action:

Non memory

CAUTION:

Leave the emergency landing gear extension handle up

NOTE:

When wheels are blown down you may get a burning electrical smell from the squib.

102
Q

Possible Symptoms:

  • Three green lights on landing gear indicator when airborne with handle in UP position
  • AFCS is ineffective in pitch and roll and the collective will not accept FD inputs
  • Amber light remains on or illuminates intermittently with handle in UP position
A

WHEELS FAIL TO RETRACT

-LANDING GEAR Section-

Corrective action:

Non memory

NOTE:

The wheels will not retract if the nose weight-on-wheels microswitch is disconnected, the landing gear actuator locks are installed, or the nosewheel is not centered.

103
Q

Symptoms:

  • HEATER O/HEAT
  • ECS circuit breaker popped on copilot panel
A

HEATER OVERHEAT

-ECS Section-

Corrective action:

Non memory

CAUTION:

  • HEATER O/HEAT may indicate a fire hazard
  • Do not turn HEAR on until the cause of the overheat has been determined. Closed heater nozzles may cause an overheat.

NOTE:

A bleed air leak could also cause a warning light due to excessive temperature in the aft cabin overhead or near the FADEC computer placing the HEAT selector switch to OFF will close the bleed air shutoff valve

104
Q

Symptoms:

  • AV RACK O/HEAT

Possible Symptoms:

  • FREON HI PRESS
  • Little of no airflow from the cockpit/cabin air nozzles
  • Discharge air from cockpit/cabin air nozzles at cabin ambient temperature
A

AV RACK O/HEAT

-ECS Section-

Corrective action:

Non memory

CAUTION:

  • If moisture is present outside the cockpit (i.e rain or IMC), the COOLING MANIFOLD LEVERS must be closed to prevent ambient air from being blown into the intakes of the MFDs if the RAM AIR LEVER is opened.
105
Q

Symptom:

  • Little or no airflow from cockpit/cabin air nozzles.
A

ECS FAILURE

-ECS Section-

Corrective action:

Non memory

106
Q

Symptoms:

  • FREON HI PRESS
  • Discharge air from cockpit/cabin air nozzles at cabin ambient temperature
A

FREON HI PRESS

-ECS Section-

Corrective action:

Non memory

CAUTION:

If moisture is present outside the cockpit…close the COOLING MANIFOLD LEVERS if the RAM AIR LEVER is opened.

Note

If the condenser inlet pressure is excessive, the compressor will disengage and the FREON HI PRESS illuminates. The COOL system will continue to operate providing recirculated cabin air to the AV RACK.

107
Q

LOST RS (DAY)

A
  1. MARK AND RECORD POSITION
  2. TRANSITION AND ESTABLISH RIGHT ORBIT
  3. LOOK AND LISTEN FOR RS SIGNAL
  4. WHEN VISUAL - RESUME HOVER POSITION

If these procedures fail to locate the RS:

  1. COMPLETE LEAVING RS ON SCENE PROCEDURE
108
Q

LOST RS (DAY) SIGNALS

A
  1. Radio, prebriefed frequency
  2. Smoke
  3. Mirror
109
Q

LOST RS (NIGHT)

A
  1. MARK AND RECORD POSITION
  2. FLASH LANDING/HOVER LIGHT
  3. LOOK AND LISTEN FOR RS SIGNAL
  4. WHEN VISUAL - CEASE FLASHING LIGHT

If these procedures fail to locate the RS:

  1. COMPLETE LEAVING RS ON SCENE PROCEDURE
110
Q

LOST RS (NIGHT) SIGNALS

A
  1. Radio, prebriefed frequency
  2. Flare
  3. Strobe light
111
Q

EMERGENCY RECOVERY OF RS

A
  1. RESCUE BASKET - IF RIGGED AND EMPTY
  2. BARE HOIST HOOK - IF BASKET NOT READILY AVAILABLE
  3. WITH THE ASSISTANCE OF THE FM, THE RS SHALL ENTER THE CABIN BACKWARDS

WARNING:

If the aircrew observes a hazard to the RS in the water, hoisting the RS should be initiated by placing the rescue device between the RS and the hazard

Note:

The RESCUE BRIEF is not required if the IN TROUBLE NEED ASSITANCE signal is observed

If two or more RS are in the water and the basket is sent down, the RSs may disconnect the basket and come up via the V-ring.

112
Q

LEAVING THE RS ON SCENE

A
  1. MARK AND RECORD POSITION
  2. DEPLOY LIGHTED RAFT
  3. DEPLOY DMB
  4. Continued non-memory

NOTE:

Deploy whatever you can spare to help enhance their survivability

113
Q

EMERGENCY EGRESS

A
  1. WAIT
  2. HOLD
  3. JETTISON
  4. CORDS
  5. HARNESS
  6. EGRESS
  7. INFLATE
114
Q

LAND/DITCH IMMEDIATELY

A
  1. WHEELS - AS REQUIRED
  2. FLOATS - AS REQUIRED
  3. SLIDING DOOR - AS REQUIRED
  4. LAND / DITCH
  5. EFSLs - BOTH OFF
  6. ROTOR BRAKE (land only) - ON
  7. EMERGENCY EGRESS - EXECUTE
115
Q

Symptom:

  • Cabin sliding door does not fully open or will not secure in the closed position
A

MALFUNCTIONING CABIN SLIDING DOOR

DITCHING / EGRESS / ENTRANCE Section

Corrective action:

Non-memory

WARNING

A malfunctioning cabin sliding door presents an egress hazard. Over water operations below 200 ft should not be conducted with a malfunctioning door.

116
Q

Symptom:

Any unusual, undesirable, or unsafe aircraft attitude

A

UNUSUAL ATTITUDE RECOVERY

Corrective Action:

  1. LEVEL THE WINGS
  2. NOSE ON THE HORIZON
  3. CENTER THE BALL
  4. POWER - ADJUST TO MAINTAIN LEVEL FLIGHT
117
Q

Symptom:

Unplanned entry into IMC from VMC

A

INADVERTENT IMC

Corrective Action:

  1. ANNOUNCE - “INADVERTENT IMC”
  2. ESTABLISH AN INSTRUMENT SCAN
  3. ESTABLISH A SAFE ALTITUDE, AIRSPEED, AND HEADING.
  4. External communication- as required

MH-65E - EPs, Aero, SAR and STAN Checks (5 decks)

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