TH-73A Emergency Procedures

Question 1

Indications of an engine failure:

Answer 1

1. NR, N2, N1, ITT, and torque rapidly decreasing.
2. Left yaw.
3. ENG OUT warning CAS message and aural warning.
4. ROTOR LOW warning CAS message and aural warning.

Question 2

ENGINE FAILURE HOVER IGE CMI

Answer 2

Legend: ENG OUT CAS warning message.

Cause/Remarks: This EP encompasses engine failures from a hover in ground effect up to 30 KIAS.

1. Collective-Maintain initially then increase to cushion touchdown.
2. Pedals-Control yaw rate.
3. Cyclic-Adjust to obtain level skid attitude.

Question 3

ENGINE FAILURE TAKEOFF

Answer 3

Legend:
ENG OUT warning CAS message

Cause/remarks:
This EP refers to engine failures after takeoff above 30 KIAS.

1. Collective-Lower immediately to stop Nr decay.
2. Pedals-Control yaw rate.
3. Autorotative Landing-Complete.

Question 4

ENGINE FAILURE HOVER OGE

Answer 4

Legend:
ENG OUT warning CAS message

Cause/remarks:
If altitude permits, consider increasing airspeed to at least 60 KIAS.

1. Collective-Lower immediately to stop NR decay.
2. Pedals-Control yaw rate.
3. Cyclic-Forward to increase airspeed.
4. Autorotative Landing-Complete.

Question 5

ENGINE FAILURE CRUISE

Answer 5

Legend:
ENG OUT warning CAS message

Cause/remarks:
None.

1. Collective-Lower immediately to stop NR decay.

C: Keep rotor speed between 90 and 110% NR.

2. Pedals-Control yaw rate.
3. Cyclic-Adjust to desired airspeed.

N: Airspeed for minimum rate of descent is 70 KIAS.
N: Airspeed for maximum glide distance is 100 KIAS.

If time and altitude permit:
4. MAYDAY-Transmit.
5.Transponder-7700.
6. Engine Restart in Flight-As required.

If engine remains off/failed:
7. Autorotative Landing-Complete.

Question 6

ENGINE RESTART IN FLIGHT

Answer 6

Legend:
None.

Cause/remarks:
N: Engine restart has not been tested in flight.

C: When the cause of engine failure is due to mechanical failure, do not attempt a restart.

1. GEN switch-OFF.
2. Twist grip-OFF.
3. START push-button-Press and release.
   When N1 reaches 10-20%:
4. Twist grip-IDLE.
   When starter drops out and N1 61 +/- 1%:
5. Twist grip-FLT.
6. GEN switch-ON.

Question 7

Is the autorotative landing procedure in NATOPS specific to aircraft parameters?

Answer 7

No, it is not. It is generic and not specific to aircraft gross weight, environmental conditions, altitude, landing surface characteristics, etc.

Question 8

What NR should autorotative flare initiation begin?

Answer 8

101-103%

Question 9

What is the recommended pitch rate and pitch limit for an autorotation?

Answer 9

Recommended pitch rate is 5-7 per second up to a maximum of 30 deg nose up.

Question 10

What should an effective flare do?

Answer 10

Reduce the rate of descent to approximately 500 fpm and forward speed to approximately 30 KIAS by the time the aircraft reaches 20 to 30 ft.

Question 11

What are the requirements for touchdown airspeed and rate of descent?

Answer 11

Acceptable touchdown speed is highly dependent on the landing surface characteristics, but must be less than 50 kts. Rate of descent at touchdown should be less than 400 fpm.

Question 12

AUTOROTATIVE LANDING

Answer 12

Legend:
None.

Cause/remarks:
None.

At approximately 150 feet:
1. Cyclic-Flare to reduce forward airspeed.
At approximately 20-30 feet:
2. Collective-Increase to reduce rate of descent.
3. Cyclic-Forward to obtain skid level attitude.
4. Collective-Continue application to cushion touchdown.
5. Pedals-Maintain direction.

C: In case of contact on the aft portion of the landing skid, avoid counteracting the pitch down with cyclic.

6. Emergency shutdown-Complete.

Question 13

ENGINE OIL PRESSURE LOW

Answer 13

Legend:
ENG OIL PRESS caution CAS message
ENG OIL PRESS warning CAS message

Cause/remarks:
Indications:
-ENG OIL PRESS warning message with tone.
-ENG OIL PRESS caution message with tone.
-N1 decreasing

W: This emergency may result in engine failure.

Engine oil pressure below 40 psi or 40-80 psi and decreasing:
1. Reduce power.
2. Monitor engine parameters.
3. Land as soon as possible.

N: Engine oil pressure may enter the cautionary range during autorotations.

Question 14

ENGINE OIL TEMPERATURE HIGH

Answer 14

Legend:
ENG OIL HOT warning CAS message

Cause/remarks:
Indications:
-ENG OIL HOT warning message and tone.
-Engine oil temperature above 115 deg C.

1. Reduce power.
2. Monitor engine parameters.
3. Land as soon as possible.

Question 15

When is the ABORT START procedure used?

Answer 15

The ABORT START procedure is intended for any abnormality during the start sequence, including an igniter failure, a hot start, or a hung start.

Question 16

ABORT START

Answer 16

Legend:
ITT LIMIT warning CAS message

Cause/remarks:
-ITT fails to rise after twist grip rotated to IDLE.
-ITT rises more slowly than normal and N1 stabilizes lower than normal.
-ITT rapidly increasing through 870 deg C.
-Smoke, flames or fire from engine exhaust.

C: An excessive rise in ITT, ITT rapidly accelerating through 870 deg C, and/or low battery voltage on starter engagement, indicates an increased potential for a hot start and may require aborting the start to preclude exceeding ITT start limits.

C: Monitor engine start and if light off does not occur within 10 seconds after the twist grip is set to IDLE, abort the start.

1. Twist grip-OFF.
2. IGN switch-OFF.
3. STARTER pushbutton-Continue to operate until ITT decreases to normal range.
4. Fuel Panel switches-OFF/CLOSED.

C: Failure to utilize a GPU/battery cart on subsequent start attempts may result in a hot start.

Question 17

How is a compressor stall normally recognized?

Answer 17

A compressor stall is normally recognized by an audible pop accompanied by a possible increase in ITT and fluctuating N1 and TRQ. The compressor stall may be transient or steady.

Question 18

ENGINE COMPRESSOR STALL

Answer 18

Legend:
N/A

Cause/remarks:
-Loud banging or popping (similar to backfiring).
-Fluctuating N1 coupled with failure to respond to power demand.
-Reduction in torque (due to reduced airflow through engine).
-Abnormal ITT increase (due to mismatch between fuel flow and N1 speed).

Corrective action:

W:
This emergency may result in engine failure.

*1. Collective-Lower to clear the stall.
*2. Airspeed-60-70 KIAS level flight.
*3. Land as soon as possible.

N:
If some usable power exists but level flight cannot be maintained, that power may be utilized to effect a landing or minimize rate of descent enroute to a suitable site for autorotation.

Question 19

How is the engine droop compensator connected to the collective lever?

Answer 19

The mechanical droop compensator is connected to the collective lever through a linkage incorporating a shear section.

Question 20

What needs to be done if an engine droop compensator linkage binding occurs?

Answer 20

If engine droop compensator linkage binding occurs, an increased collective force of 8.8 pounds (4 kg) maximum will be necessary to cut the shear section.

Question 21

During an engine droop compensator binding, what will happen once the shear section is cut?

Answer 21

When the shear section has been cut, the collective force will return to normal level but the mechanical droop compensator (MEC) will be inoperative.

The EEC mode of operation will not be affected.

Question 22

Tell me about malfunction of the automatic fuel control system

Answer 22

If an automatic fuel control system malfunction arises in flight, the manual override system (MAN) can be used. The MAN overrides automatic control features associated with normal operation of the engine. The pilot will have to compensate for collective and pedal movements by rotating the twist grip.

Question 23

Malfunction of the Fuel Control System Blurb Warning and Note

Answer 23

W:
-When using the MAN, the engine response is directly related to the rate at which the engine throttle is rotated. Additional care is required during engine acceleration. Monitor cockpit indicators closely to avoid the possibility of over temperature, over torque, or engine surge.

N:
-An initial dead band (no engine response) may occur while operating in MAN.

Question 24

MALFUNCTION OF THE FUEL CONTROL SYSTEM (OVERSPEED)

Answer 24

Legend:
-ROTOR HIGH CAS warning message

Cause/remarks:
-Indications:
Uncommanded increase in engine power (N1, ITT), torque, N2, and NR.

Corrective action:
If the fuel control system malfunction causes an increased collective force in power (overspeed):

*1. Twist grip-Reduce until NR/N2 are in normal range.

W:
-N1 decreasing below 51% will cause engine flame out.

*2. Collective/Twist grip-Coordinate.
*3. Land as soon as possible.

N:
-An overspeed may result in an EEC failure.

Question 25

MALFUNCTION OF THE FUEL CONTROL SYSTEM (UNDERSPEED)

Answer 25

Legend: -ROTOR LOW warning CAS message Cause/remarks: -Uncommanded decrease in engine power (N1, ITT), torque, N2, and NR Corrective action: If the fuel control system malfunction causes a decrease in power (underspeed): *1. Collective-Lower to maintain NR. *2. MAN/NOR selector-MAN. *3. Twist grip-Slowly rotate toward MAX, as required. *4. Collective/Twist grip-Coordinate. W: -Rapid movement of the throttle in MAN may result in engine over temp, over torque, over speed or engine surge. -N1 decreasing below 51% will cause engine flame out. *5. Land as soon as possible.

Question 26

What is the only situation in which it is possible to get the Electronic Engine Control Degraded (EEC DEGRADED) caution CAS message?

Answer 26

It is only possible to get this CAS message on the ground with NR below 20%.

Question 27

ENGINE RBG CHIP

Answer 27

Legend: -ENG RGB CHIP caution CAS message Cause/remarks: Indications: -ENG RGB caution CAS message Corrective action: *1. Reduce power. *2. Check for secondary indications. If secondary indications exist: *3. Land as soon as possible. The use of CHIP BURNER switch when the relative oil pressure is below limits is prohibited. If no secondary indications: *4. CHIP BURNER switch-Activate and release. If the message does not extinguish or on the 4th ENG RGB CHIP message: *5. Land as soon as possible. N: -The CHIP BURNER switch shall not be used to suppress a chip caution light when the aircraft is on the ground. -The CHIP BURNER can be activated 3 times per flight.

Question 28

ENGINE AGB CHIP

Answer 28

Legend: -ENG AGB CHIP caution CAS message Cause/remarks: Indications: -ENG AGB CHIP caution CAS message Corrective action: *1. Reduce power. *2. Land as soon as possible. N: -CHIP BURNER is not available with an ENG AGB CHIP.

Question 29

What are the causes/remarks for a rotor underspeed?

Answer 29

Indications: -ROTOR LOW warning. -NR 75-76%.

Question 30

What are the causes/remarks of a rotor overspeed?

Answer 30

Indications: -ROTOR HIGH warning. -NR exceeding 108%.

Question 31

What are the three general types of the most common transmission system (main and tail rotor gearbox) failures?

Answer 31

1. Lubrication system failure (oil pump, ducts, nozzles, etc.) 2. Transmission component failure (gears, bearings, etc.) 3. Accessory component failure (hydraulic pumps, coolers, etc.)

Question 32

What crew sensory perceptions play an important role in the diagnosis of impending transmission system failures?

Answer 32

1. Abnormal mechanical noise. 2. Heavy vibration levels. 3. The smell of hot metal fumes.

Question 33

TRANSMISSION MALFUNCTION

Answer 33

Legend: -N/A Cause/remarks: -Indications: 1. XMSN OIL PRESS warning CAS message. 2. Transmission oil pressure below 30 psi. 3. XMSN OIL HOT warning CAS message. 4. Transmission oil temperature above 115 degrees C. 5. XMSN CHIP caution CAS message. Corrective action: W: -Possible indications of imminent transmission failure may include: yaw attitude excursions with no control input, an increase in power required for a fixed collective setting, increased noise, increased vibrations, or abnormal fumes. If failure is imminent: *1. Land immediately. If failure is not imminent: *2. Reduce power. *3. Monitor transmission parameters. *4. Land as soon as possible. N: Transiting at a minimum power required airspeed and low altitude may permit a quick flare and immediate landing in the event of an imminent transmission failure.

Question 34

TRANSMISSION CHIP

Answer 34

Legend: -XMSN CHIP cautions CAS message Cause/remarks: Indications: -XMSN CHIP caution CAS message. Corrective action: If XMSN CHIP message is illuminated: *1.Check for secondary indications. If secondary conditions exist: *2. Transmission Malfunction emergency procedure-Perform. The use of CHIP BURNER switch when the relative oil pressure is below limits is prohibited. If no secondary indications: *3. CHIP BURNER switch-Activate and release. If the message does not extinguish or on the 4th XSMN CHIP message: *4.Transmission Malfunction emergency procedure-Perform. N: -The CHIP BURNER switch shall not be used to suppress a chip caution light when the aircraft is on the ground. -The CHIP BURNER can be activated 3 times per flight.

Question 35

What two things may a tail rotor failure result in?

Answer 35

A complete loss of tail rotor control or in a jamming of the tail rotor pitch.

Question 36

Tell me about a complete loss of tail rotor control.

Answer 36

A tail rotor drive failure in a loss of yaw control with a consequent yaw to the right, which increases in rapidity at low forward airspeeds and high torque levels. A tail rotor drive failure may be accompanied by noise, vibration, or oscillation in the tail section. The vertical fin produces an anti-torque component which is a function of the forward speed and which assists in controlling the helicopter in low torque conditions. The action to be taken depends upon whether the helicopter is in hover or in forward flight. In both cases, the landing should be made at the lowest possible power or even with the engine out. While a tail rotor drive failure in hovering is immediately detected, the same failure may be less evident in the cruise.

Question 37

LOSS OF TAIL ROTOR THRUST IN A HOVER

Answer 37

Corrective action: *1. Twist grip-IDLE. *2. Cyclic-Eliminate drift. *3. Collective-Increase to cushion the landing. C: A slight rotation to the right can be expected on touchdown.

Question 38

LOSS OF TAIL ROTOR THRUST IN CRUISE FLIGHT

Answer 38

Cause/remarks: Significant residual torque may exist if the twist grip is left in IDLE. The precise moment appropriate for moving the twist grip to OFF is at the discretion of the crew. Corrective action: *1.Collective-Lower to eliminate yaw. *2. Airspeed-Adjust to reach a suitable landing site. N: An increase in power necessitates an increase in speed to prevent the helicopter from excessive yaw. *3. Autorotate. *4. Twist grip- OFF prior to touchdown.

Question 39

Tell me about jamming of Tail Rotor Pitch.

Answer 39

This condition produces an inability to change tail rotor thrust with pedals. Indications: 1. Helicopter response - No yaw response when pedals are moved. 2. Pedals - Locked. C: IF the pedals cannot be moved with a moderate amount of force, do not apply excessive force since a more serious malfunction could result. N: IF helicopter is in a trimmed flight condition when malfunction occurs, TQ and airspeed should be noted and helicopter flown to a suitable landing area. Combinations of torque and airspeed will yaw attitude and these should be adjusted to land the helicopter.

Question 40

Tell me about Fixed Pitch Hovering

Answer 40

Do not close engine throttle unless a severe right yaw occurs. If fixed tail rotor pitch is encountered during hovering, landing can be accomplished with greater safety under power-controlled flight rather than closing engine throttle and entering autorotations.

Question 41

Tell me about Fixed Pitch in Flight.

Answer 41

Fixed tail rotor pitch is described in 2 general ways: stuck left (high power) or stuck right (low power). Although not specifically stated, a stuck neutral position occurs with the tail rotor providing proper thrust for a HIGE main rotor torque setting (I.e. 5 ft hover possible with no yaw). An aircraft with a left yaw in a 5 ft hover has excessive tail rotor thrust for this flight condition (stuck left-high power). An aircraft with a right yaw in a 5 ft hover has insufficient tail rotor thrust for this flight condition. In all conditions, flying at minimum power required airspeed will yield a nose in the furthest left position possible. The nose will yaw further left in a stuck left condition. Increasing torque from here will cause the nose to move right until the torque on the main rotor is equivalent to the tail rotor thrust (anti-torque) where the aircraft will have no yaw and ball centered. Increasing collective behind this torque will cause the nose to yaw right of center. A controllability check at straight and level flight at altitude should be conducted to determine the degree and severity of the fixed pitch condition in level flight. Note torque required to eliminate yaw. In any case, execute a shallow approach to a sliding landing below 30 KGS or hover landing to the runway. If unable to slow below 30 KGS in case of a more severe stuck right-low power condition, the twist grip may be coordinated with collective to continue deceleration below 30 KGS and maintain nose alignment for touchdown. In case of a more severe stuck left-high power condition, an approach to a hover may not eliminate the left yaw.

Question 42

TAIL ROTOR CHIP

Answer 42

Legend: T/R BOX CHIP CAS caution message Cause/remarks: Indications: -TR BOX CHIP CAS caution message Corrective action: W: -Be prepared for a complete loss of tail rotor thrust. -High power settings may result in tail rotor gearbox failure. *1. Reduce power. *2. CHIP BURNER switch-Activate and release. If the message does not extinguish or on the 4th TR BOX CHIP message: *3. Land as soon as possible. Note: -The CHIP BURNER switch shall not be used to suppress a chip caution light when the aircraft is on the ground. -The CHIP BURNER switch can be activated 3 times per flight.

Question 43

Hydraulic System Emergency blurb

Answer 43

The helicopter is equipped with two independent hydraulic systems for cyclic and collective pitch control. Either system can deliver adequate power to control the helicopter. The tail rotor pedals are boosted by system N1 only.

Question 44

HYDRAULIC SYSTEM NO.1 OR NO. 2 PRESSURE LOSS

Answer 44

Legend: 1 (2) SERVO caution OR 1-2 SERVO caution Cause/remarks: Indications: -1 SERVO or 2 SERVO caution. -Hydraulic pressure of the affected system below 1200 psi. Corrective action: *1.Establish VMC. *2.Avoid rapid movement of flight controls. C: -Pull-up manuevers and bank angles beyond 25 degrees may result in excessive flight control loads. *3.Airspeed-Reduce smoothly below 90 KIAS. *4.Affected SERVO switch-OFF. *5.Land as soon as possible. N: -Tail rotor pedals are not boosted when the hydraulic system No. 1 fails. -Rapid power changes with 1 SERVO off can result in an excessive yaw that may not be controlled with unboosted pedals. -Unboosted pedals may be insufficient to counteract right yaw with strong right crosswinds.

Question 45

Main Rotor Servo Valve Jamming Blurb

Answer 45

The jamming of a servo valve of main rotor servo actuators can be detected only during the system check on ground before take-off when hydraulic systems are alternatively deactivated. Jamming of a servo valve on one of the main rotor servo actuators is detectable in flight by: 1.A force increase on the cyclic stick and collective lever. 2.A helicopter response which is not fully consistent with the control input during a maneuver.

Question 46

Automatic Flight Control System Emergencies Blurb

Answer 46

N: -The Helipilot indicators normally refer to Helipilot 1. Turning SAS 1 off, the Helipilot indicators will automatically switch to Helipilot 2. -Helipilot 2 pitch and roll linear actuator positions may be observed by pressing the SAS 2 PUSH push button on the Helipilot control panel. -Following one of the two Helipilot failures, cyclic four way trim switch and Autotrim are inoperative.

Question 47

BATTERY TEMPERATURE HIGH

Answer 47

Legend: BATTERY HOT warning CAS message Cause/remarks: -BATT HOT warning CAS message -Battery temperature exceeding limits. Corrective action: *1. BAT switch-OFF. *2. Land as soon as possible.

Question 48

EMERGENCY DC BUS FAILURE

Answer 48

Legend: 1 INV OFF caution 1 SAS OFF caution 1 VG caution XFER PUMP caution FUEL LOW caution ADSB FAIL caution Cause/remarks: 1. 1 INV OFF caution. 2. 1 SAS OFF caution. 3. 1 VG caution. 4. XFER PUMP caution. 5. FUEL LOW caution. 6. ADSB FAIL caution. 7. Torque indication failed. 8. Fuel Quantity indication failed. 9. Force Trim (magnetic brakes) failed, but no FT OFF advisory. 10. ICS failed with ACP in NORM. 11. Higher indicated ITT. Corrective action: If the EMER BUS circuit breaker has tripped, it may be reset (one attempt only) to potentially regain the Emergency Bus. If the Emergency Bus is regained, flight may be continued. *1.Land as soon as possible. C: -ITT reference signal lost. Reduce ITT limit by 30 degrees C. N: -ICS operation may be restored with ACP switched in BK-UP or EMER.

Question 49

FUEL PUMP 1 AND/OR FUEL PUMP 2 FAILURE

Answer 49

Legend: -1 (2) FUEL PUMP caution. Cause/remarks: Indications: -1 (2) FUEL PUMP caution. -1-2 FUEL PUMP caution. Corrective action: If both pumps fail with 0 psi: *1. Land as soon as possible. N: -Any flight time with both fuel pumps OFF or failed must be reported to maintenance. Ground operations with both fuel pumps OFF or failed need not be restricted.

Question 50

Transfer Pump Failure Blurb

Answer 50

The CAS caution message will illuminate if the right lower tank is empty or the transfer pump has failed. Once the fuel quantity is less than 120 kg, the right hand fuel quantity indication will have a yellow box and ‘X’ through the number.

Question 51

ENGINE FIRE IN FLIGHT

Answer 51

Legend: -ENG FIRE warning CAS message’ Cause/remarks: Indications: -ENG FIRE warning CAS message -Flames. -Smoke. Corrective action: W: -This emergency may result in engine failure. *1.Confirm fire. If fire is confirmed: *2.Land immediately. If fire is not confirmed: *3.Land as soon as possible. While on deck: *4.Emergency shutdown-Complete.

Question 52

Cockpit/Cabin Fire in Flight Blurb

Answer 52

An in-flight fire has no single set of detailed procedures that can address all the fire scenarios that are possible in flight. The most urgent action is to get the aircraft on ground as soon as possible with a reasonable degree of safety. Charging of EKB/tablets is a potential electrical source for a cockpit/cabin fire. Any evidence of tablet abnormal operation or overheating shall result in tablet disconnect from the power cord and tablet powering down.

Question 53

COCKPIT/CABIN FIRE IN FLIGHT

Answer 53

*1.Air Conditioner/Vent/Heater switches-OFF. *2.Vent knob-Push. *3.Airspeed-Adjust, as required. *4.Doors/Windows-Close. If electrical source suspected: *5.Unnecessary electrical equipment-Secure. *6.Fire extinguisher-As required. If fire persists: *7.Land immediately. C: -If the fire is not completely extinguished, increasing ventilation may aggravate the problem. If fire extinguishes: *8.Land as soon as possible. When on deck: *9.Emergency shutdown-Complete.

Question 54

SMOKE/FUME ELIMINATION

Answer 54

*1.VENT CKPT switch-ON. *2.Vent knob-Pull. *3.Airspeed-Adjust, as required. *4.Doors/Windows-Open. If smoke/fumes persist: *5.Slip or skid aircraft to eliminate smoke and fumes. *6.Land immediately. *7.Emergency Shutdown-Complete. If smoke/fumes extinguish: *8.Land as soon as possible.

Question 55

EMERGENCY SHUTDOWN

Answer 55

Cause/remarks: Indications: -ENG FIRE warning light. -Smoke, fuel, fumes, fire. -Indication from ground personnel. -Grinding noise or apparent drive train damage. Corrective action: *1.Twist grip-OFF. ‘*2.Fuel Panel switches-OFF/CLOSED. *3.Rotor brake-ON. *4.GEN switch-OFF. *5.BAT switch-OFF. When rotor stops: *6.Helicopter-Egress.

Question 56

IMMEDIATE LANDING/DITCHING

Answer 56

Cause/remarks: W: -Jettisoning the left cockpit door in forward flight may cause catastrophic damage to the tail rotor. -Failure to remain strapped in the aircraft until all violent motion stops may result in injury or incapacitation. Corrective action: *1.Crew and passengers-Alert. *2.Mayday-Transmit. *3.Transponder-7700. *4.Doors-Open/Jettison-As required. *5.Landing light/Search light-As required. When on deck: *6.Emergency shutdown-Complete. If water landing: *7.Underwater egress-Execute.

Question 57

UNDERWATER EGRESS

Answer 57

Cause/remarks: W: -Inflation of LPU inside of aircraft will impede egress. -Failure to jettison doors prior to water entry may prevent opening of doors until cabin fills with water. Cabin misalignment due to water landing may also prevent opening of doors. -Failure to disconnect ICS cords may impede egress. Corrective action: *1.SEBD-Don, as required. *2.Communication cords-Disconnect. *3.Doors-Open/jettison. *4.Place hand on known reference point. Once all violent motion has stopped: *5.Harness-Release. *6.Exit helicopter. After egress: *7.Swim clear and inflate LPU.

Question 58

Lightning Strike Blurb

Answer 58

When flying in proximity of thunderstorms, the helicopter may be struck lightning. If it is suspected that the helicopter has been struck by lightning, proceed with EP. If it suspected that the pilot side Pitot System has been damaged by lightning, proceed as per STATIC PORT OBSTRUCTION procedure. If it suspected that the helicopter has been struck by lightning this must be noted in the helicopter log book.

Question 59

LIGHTNING STRIKE

Answer 59

Corrective action: *1.Airspeed-Reduce below 80 KIAS. *2.Maneuver smoothly. *3.Land as soon as possible

Question 60

HOIST LOAD JETTISON

Answer 60

Legend: -HOIST CUT ARM CAS caution message Cause/remarks: -N/A Corrective action: *1.HOIST CUT push button guard-Lift. Verify HOIST CUT ARMD CAS message appears. *2.HOIST CUT push button-Press. N: -Cut cable as close to hoist as possible.

Question 61

RESCUE HOIST FAILURE

Answer 61

Legend: -HOIST CABLE LKD caution Cause/remarks: Indications: -HOIST CABL LKD caution. -HOIST control switches on the pilot/copilot cyclics and operator’s HOIST thumb wheel inoperative. Corrective action: *1.Cease hoisting. W: -If for any reason hoist stops during raising or lowering operations, do not attempt to free it by actuating the controller. Continued operation may cause total cable failure.

Question 62

HOIST CABLE FOULED

Answer 62

Legend: -HOIST CABLE caution Cause/remarks: Hoist cable and/or load fouled on part of aircraft, obstruction or terrain. Corrective action: *1.Pay out cable and attempt to free hang up.

Question 63

ROTOR BRAKE ON

Answer 63

Legend: -RTR BRK ON warning Cause/remarks: Indication: -ROTOR BRAKE ON warning. Corrective action: In flight: *1.Rotor brake lever-Verify OFF. *2.Land immediately. On the ground: *3.Rotor brake lever-Verify OFF. *4.Emergency shutdown-Complete.

Question 64

LOSS OF TORQUE SENSOR POWER

Answer 64

Cause/remarks: In any condition different from autorotation: -0% TRQ indication (PFD and MFD) -Disregard TRQ instruments indications. Corrective action: *1.Land as soon as possible.