MH-65E EPs NOV 2020

Question 1

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.

Answer 1

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.

Question 2

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

Answer 2

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”

Question 3

Symptoms:

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

Answer 3

MGB PMP MAIN

=MGB Section=

Corrective Action:

Non-memory

Note

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

Question 4

Symptoms:

• MGB OIL TEMP
• Abnormal rise in MGB oil temperature

Answer 4

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

Question 5

Symptom:

• MGB PMP AUX

Answer 5

MGB PMP AUX

-MGB Section-

Corrective Action:

Non-memory

NOTE

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

Question 6

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

Answer 6

MGB INDICATING SYSTEM FAILURE

-MGB Section-

Corrective Action:

Non-Memory

Question 7

Symptom:

• PFD TRQ exceeds 100%

Possible symptoms:

• MGB QT captured on the CDU ASE ECMS EXCEEDANCE page

Answer 7

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)

Question 8

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

Answer 8

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

Question 9

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

Answer 9

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:

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

After 60 seconds:

7. SEC FIRE EXTINGUISHER BUTTON - CONFIRM; PUSH

If fire still persists:

8. LAND/DITCH IMMEDIATELY

If fire no longer evident:

9. LAND AS SOON AS POSSIBLE

If fire not confirmed:

10. LAND AS SOON AS PRACTICABLE

Warning

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

Question 10

Symptoms:

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

Answer 10

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:

5. PRI FIRE EXTINGUISHER BUTTON - CONFIRM; PUSH
6. SEC FIRE EXTINGUISHER BUTTON - CONFIRM; PUSH
7. EMERGENCY ELECTRICAL CUTOFF
8. ROTOR BRAKE
9. EVACUATE

Question 11

Symptoms:

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

Answer 11

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

Question 12

INTERNAL FIRE

NOTES WARNINGS CAUTIONS

Answer 12

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)

Question 13

SMOKE AND FUME ELIMINATION

Answer 13

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

Question 14

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.

Answer 14

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

Question 15

Symptom:

• Fire detector FAIL light illuminated

Answer 15

FIRE DETECTOR FAILURE
-Fires section-
Corrective Action:

Non-memory

NOTE

FAIL indicates an open circuit

Question 16

Symptom:

• L EXT or R EXT

Answer 16

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

Non-memory

Question 17

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

Answer 17

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

3. LAND AS SOON AS PRACTICABLE

Question 18

Symptom:

• Windscreen cracked

Answer 18

WINDSCREEN CRACKS

-AIRCRAFT DAMAGE OR ABNORMAL VIBRATIONS section-

Corrective Action:

Non-memory

Question 19

Symptoms:

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

Answer 19

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

Question 20

Symptoms:

• TGB CHIP

Answer 20

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

Question 21

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)

Answer 21

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)

Question 22

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)

Answer 22

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

Question 23

POWERED LANDING WITH TAIL ROTOR MALFUNCTION

NOTES, WARNINGS, CAUTIONS

Answer 23

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

Question 24

Symptom:

• If NR >380 RPM (10 Hz chopped tone)

Answer 24

NR OVERSPEED

-MAIN/TAIL ROTOR section-

Corrective action:

Non-memory

Question 25

Symptoms: * NR HI with NR switch in NORMAL * NR \>365 RPM with the NR switch in NORMAL

Answer 25

**NR HI MALFUNCTION** -MAIN/TAIL ROTOR section- Corrective Action: Non-memory CAUTION Extended operation above Vy could damage aircraft systems

Question 26

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

Answer 26

**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

Question 27

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

Answer 27

**AUTOROTATION PROCEDURE** -ENGINES section- Corrective Action: **1. NR** **2. AIRSPEED** **3. TURN** **4. FLARE** **5. COLLECTIVE**

Question 28

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

Answer 28

**FADEC FAIL** -ENGINES section- Corrective Action: **1. TRNG SWITCH - FLT** **2. FADEC BACKUP SWITCH (affected engine) - CONFIRM; BACKUP**

Question 29

## Footnote **FADEC FAIL NOTES, WARNINGS, & CAUTIONS**

Answer 29

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]

Question 30

Symptoms: * Aircraft ondeck in unsafe condition

Answer 30

**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**

Question 31

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

Answer 31

**ENGINE START EMERGENCIES** -ENGINES section- Corrective Action: **1. FCS - OFF**

Question 32

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

Answer 32

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

Question 33

Symptoms: * ENG 1 CHIP or ENG 2 CHIP

Answer 33

**ENG CHIP** -ENGINES section- Corrective Action: Non-memory - [BIG 4]

Question 34

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

Answer 34

**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

Question 35

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

Answer 35

**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

Question 36

Symptoms: * ENG 1 FUEL P or ENG 2 FUEL P

Answer 36

**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

Question 37

Possible symptoms: * Popping or rumbling noises * TOT increases/fluctuates * TRQ and N1 decreases * Airframe vibration/shuddering

Answer 37

**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

Question 38

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

Answer 38

**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

Question 39

Symptoms: * ENG 1 OIL TEMP or ENG 2 OIL TEMP and increase in corresponding engine oil temperature above 115\*C

Answer 39

**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

Question 40

Symptoms: * GOV LVL 2

Answer 40

**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

Question 41

Symptoms: * GOV LVL 1

Answer 41

**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

Question 42

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

Answer 42

**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

Question 43

## Footnote **RESTARTING ENGINE INFLIGHT**

Answer 43

**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

Question 44

Symptoms: * **P TRIM, R TRIM,** or **Y TRIM** * Uncommanded aircraft displacement

Answer 44

**AFCS SERIES ACTUATOR HARDOVER/PARALLEL SERVO HARDOVER** -AUTOMATIC FLIGHT CONTROL SYSTEM Section- Corrective action: Non-memory

Question 45

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

Answer 45

**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

Question 46

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

Answer 46

**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

Question 47

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

Answer 47

**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

Question 48

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

Answer 48

**WARNING:** * Loss of a/c control * Fire **CAUTIONS:** * 75-100 KIAS * 2,000 opens **Notes:** * BLT & E Hoist * TAIL HYD ISO * TALON

Question 49

Any one of the following symptoms: * **SEC HYD HI P** * **SEC HYD LO P**

Answer 49

**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

Question 50

Symptoms: * **SERVO JAM** * Flight control loading may increase

Answer 50

**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.

Question 51

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**

Answer 51

**HYDRAULIC INDICATING SYSTEM FAILURE** -HYDRAULICS section- Corrective Action: Non-memory

Question 52

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

Answer 52

**TOTAL LOSS OF AC ELECTRICAL POWER** -ELECTRICAL SYSTEM section- Corrective Action: **1. TRANSFER SCAN TO SFI - AS REQUIRED**

Question 53

Symptoms: * **BATT TEMP** * SFI Battery **FAULT** light * Smoke and/or fumes from radome or vent * Noises from radome

Answer 53

**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**

Question 54

**BATTERY OVERTEMPERATURE** **(AIRCRAFT OR SFI)** **NOTES, WARNINGS, & CAUTIONS**

Answer 54

**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

Question 55

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

Answer 55

**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

Question 56

## Footnote **TOTAL LOSS OF AC ELECTRICAL POWER NOTES, WARNINGS, CAUTIONS**

Answer 56

**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.

Question 57

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

Answer 57

**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

Question 58

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

Answer 58

**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.

Question 59

**DC BUS SHORT** **NOTES, WARNINGS, & CAUTIONS**

Answer 59

**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

Question 60

Symptom: * Both BATT RLY **OPEN** lights illuminated

Answer 60

**BATTERY BUS SHORT** -ELECTRICAL SYSTEMS section- Corrective action Non-memory

Question 61

Symptom: * One BATT RLY **OPEN** light illuminated

Answer 61

**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.

Question 62

Possible symptoms: * **FUEL FILT 1** * **FUEL FILT 2**

Answer 62

**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.

Question 63

Symptoms: * **26 VAC FAIL 1** or **26 VAC FAIL 2** * **AFCS** * **PITCH** and **ROLL** (with associated channels disengaged)

Answer 63

**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

Question 64

Symptoms: * Generator **FAIL** light illuminated * **BTC CLOSED** light illuminated

Answer 64

**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

Question 65

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)

Answer 65

**FUEL TRANSFER PUMP FAILURE** -FUEL section- Corrective action Non-memory **WARNING** * Due to potential for fire, do not reset fuel XFER PUMP circuit breakers

Question 66

Possible symptoms: * SFI battery **FAULT** light illuminated * SFI battery **ON** light illuminated

Answer 66

**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

Question 67

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**

Answer 67

**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.

Question 68

Symptoms: * The EICAS page FUEL QTY 1, FUEL QTY 2, or TOTAL does not indicate as expected, blanks, or dashes out

Answer 68

**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

Question 69

Symptoms: * Fuel transferring to one side without apparent transfer pump activation

Answer 69

**UNCOMMANDED FUEL TRANSFER** -FUEL section- Corrective action Non-memory

Question 70

## Footnote **FUEL JETTISON PROCEDURE** **NOTES, WARNINGS, CAUTIONS**

Answer 70

**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

Question 71

**BOOST PUMP/EJECTOR/INDICATOR FAILURE** **NOTES, WARNINGS, AND CAUTIONS**

Answer 71

**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.

Question 72

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**

Answer 72

**DUAL EGI FAILURE** -CAAS Section- Corrective action: If VMC cannot be maintained: **1. TRANSFER SCAN TO SFI - AS REQUIRED** Continued non-memory

Question 73

## Footnote **DUAL EGI FAILURE** **NOTES, WARNINGS, CAUTIONS**

Answer 73

-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

Question 74

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

Answer 74

**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.

Question 75

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

Answer 75

**SINGLE CDU FAILURE** -CAAS Section- Corrective action: Non-memory

Question 76

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**

Answer 76

**SINGLE EGI FAILURE** -CAAS Section- Corrective action: Non-memory

Question 77

## Footnote **SINGLE EGI FAILURE** **NOTES, WARNINGS, CAUTIONS**

Answer 77

-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

Question 78

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.

Answer 78

**MFD FAILURE** -CAAS Section- Corrective action: Non-memory

Question 79

## Footnote **MFD FAILURE** **NOTES, WARNINGS, CAUTIONS**

Answer 79

-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).

Question 80

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

Answer 80

**DUAL GPPU FAILURE** -CAAS Section- Corrective action: Non-memory Note * Engine torque can still be monitored on the CDU ECMS page.

Question 81

Symptoms: * **vLRU STATUS** MFD STAT Page: * **GPPU1, PSM1, DTU** or * **GPPU2, PSM2, DTU** Possible symptoms: * Loss of FD cues

Answer 81

**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.

Question 82

Symptoms: * **vLRU STATUS** * **MSN CARD?** MFD STAT Page: * **DTU**

Answer 82

**DTU FAILURE** -CAAS Section- Corrective action: Non-memory

Question 83

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

Answer 83

**DUAL DCU FAILURE** -CAAS Section- Corrective action: Non-memory

Question 84

**DUAL DCU FAILURE** **NOTES WARNINGS CAUTIONS**

Answer 84

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.

Question 85

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.

Answer 85

**SINGLE DCU FAILURE** -CAAS Section- Corrective action: Non-memory

Question 86

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**

Answer 86

**DUAL ADC FAILURE** -CAAS Section- Corrective action: Non-memory

Question 87

Symptoms: * Yellow ADC cross-side source indicator on PFDs * **vLRU STATUS** MFD STAT page: * **ADC1** or **ADC2**

Answer 87

**SINGLE ADC FAILURE** -CAAS Section- Corrective action: Non-memory

Question 88

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.

Answer 88

**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.

Question 89

Possible symptoms: * **vLRU STATUS** on the EICAS page * STAT page - any of the components show a failed or unknown status * Loss of associated component

Answer 89

**INDIVIDUAL COMPONENT FAILURES** -CAAS Section- Corrective action: Non-memory

Question 90

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

Answer 90

**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.

Question 91

Possible symptoms: * **AFCS** * **PITCH, ROLL, YAW,** and **COLL** (with associated channel disengaged) * **TRIM OFF** * **FD UCPL** * Voice alert, "FLIGHT DIRECTOR UNCOUPLED" once

Answer 91

**AFCS SERIES ACTUATOR OR COMPUTER FAILURE** -AUTOMATIC FLIGHT CONTROL SYSTEM Section- Corrective action: Non-memory

Question 92

## Footnote **AFCS SERIES ACTUATOR OR COMPUTER FAILURE NOTES, WARNINGS, CAUTION**

Answer 92

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.

Question 93

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.

Answer 93

**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.

Question 94

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)

Answer 94

**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.

Question 95

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

Answer 95

**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.

Question 96

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

Answer 96

**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.

Question 97

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

Answer 97

**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.

Question 98

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

Answer 98

**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.

Question 99

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

Answer 99

**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

Question 100

Possible Symptoms: * Lateral vibration when performing run on/off maneuvers or during high-speed taxiing, these vibrations may be quite violent

Answer 100

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.

Question 101

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

Answer 101

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.

Question 102

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

Answer 102

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.

Question 103

Symptoms: * HEATER O/HEAT * ECS circuit breaker popped on copilot panel

Answer 103

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

Question 104

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

Answer 104

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.

Question 105

Symptom: * Little or no airflow from cockpit/cabin air nozzles.

Answer 105

ECS FAILURE -ECS Section- Corrective action: Non memory

Question 106

Symptoms: * FREON HI PRESS * Discharge air from cockpit/cabin air nozzles at cabin ambient temperature

Answer 106

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.

Question 107

**LOST RS (DAY)**

Answer 107

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: 5. **COMPLETE LEAVING RS ON SCENE PROCEDURE**

Question 108

**LOST RS (DAY) SIGNALS**

Answer 108

1. Radio, prebriefed frequency 2. Smoke 3. Mirror

Question 109

**LOST RS (NIGHT)**

Answer 109

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: 5. **COMPLETE LEAVING RS ON SCENE PROCEDURE**

Question 110

**LOST RS (NIGHT) SIGNALS**

Answer 110

1. Radio, prebriefed frequency 2. Flare 3. Strobe light

Question 111

**EMERGENCY RECOVERY OF RS**

Answer 111

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.

Question 112

**LEAVING THE RS ON SCENE**

Answer 112

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

Question 113

**EMERGENCY EGRESS**

Answer 113

1. **WAIT** 2. **HOLD** 3. **JETTISON** 4. **CORDS** 5. **HARNESS** 6. **EGRESS** 7. **INFLATE**

Question 114

**LAND/DITCH IMMEDIATELY**

Answer 114

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**

Question 115

Symptom: * Cabin sliding door does not fully open or will not secure in the closed position

Answer 115

**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.

Question 116

Symptom: Any unusual, undesirable, or unsafe aircraft attitude

Answer 116

**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**

Question 117

Symptom: Unplanned entry into IMC from VMC

Answer 117

**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