EP

Question 1

ENGINE MALFUNCTION IN FLIGHT

Answer 1

*1. Control Nr.

Warning
Flying with greater than 110% torque with one engine inoperative may result in unrecoverable decay og Nr in the event of a dual engine failure.

• 2. CONTGCY PWR switch - ON.
• 3. Single engine conditions - Establish.
• 4. ENG ANTI-ICE switches - as required.

Warning
With engine anti-ice on, up to 18% torque available is lost. Torque may be reduced as much as 49% with improperly operating engine inlet anti-ice valves.

• 5. External cargo/stores/fuel - Jettison/dump, as required.
• 6. Identify malfunction.

Question 2

ABORT START

Answer 2

To abort start:

*1. PCL - OFF.
*2. ENGINE IGNITION switch - OFF.
If engine oil pressure is indicated.
*3. Starter - Engage.
4. Starter - disengage after 30 seconds and TGT below 540 C.

Question 3

ENGINE MALFUNCTION DURING HOVER/TAKEOFF

Answer 3

*1. Control Nr.
*2. CONTGCY PWR switch - ON.
If a suitable landing site exists or unable to transition to forward flight:
*3. Set level attitude, eliminate drift, cushion landing.
If able to transition to forward flight
*4. Engine Malfunction in Flight emergency procedure - Perform.

Question 4

(#1/#2) FUEL FLTR BYPASS OR (#1/#2) FUEL PRESS CAUTION

Answer 4

*1. Fuel selector lever (affected engine) - XFD (DIR if currently in XFD).
2. Land as soon as practicable.
If affected engine indications are abnormale:
3. Engine Malfunction in Flight Procedure - Perform.

Question 5

1 and #2 FUEL FLTR BYPASS OR #1 AND #2 FUEL PRESS CAUTION

Answer 5

*1. Land as soon as possible.
*APU Emergency Start procedure - Perform.
Warning
Be prepared for dual-engine failure. Recommended airspeed is 80 KIAS to minimize Nr droop should dual-engine failure occur.

Note
Consideration should be given to performing applicable steps of the Immediate Landing/Ditching emergency procedure.

Question 6

COMPRESSOR STALL

Answer 6

*1. Engine Malfunction in Flight emergency procedure - Perform.

2* PCL (malfunctioning engine) - IDLE.
If TGT decreases an stall clears:
3. PCL - slowly advance to FLY.
If stall remains cleared:
4. Land as soon as practicable. Avoid rapid collective movement.
If TGT continues to rise, Ng decreases below normal idle speed, or any other malfunction is indicated:
5. Engine Shutdown in Flight emergency procedure - perform.

Question 7

ENGINE HIGH-SPEED SHAFT FAILURE

(#1/#2) DRIVESHAFT FAIL

Answer 7

CAUTION
Following a high-speed shaft failure, the engine will overspeed, the Np overspeed system will flame out the engine, and the auto-ignition system will activate the relight feature. The engine Np governor will eventually bring Np down toward 100%. The engine must be manually shut down to prevent further damage.
*1. Engine Malfunction in Flight Emergency procedure - Perform.
*2 PCL (malfunctioning engine) OFF.
3. Land as soon as practicable.
Consideration should be given to performing the following:
4. Engine Shutdown in Flight emergency procedure.
5. Single-Engine Landing emergency procedure.

Question 8

ENGINE HIGH-SIDE FAILURE IN FLIGHT

(#1/#2) ENG SPEED HI

Answer 8

*1. Engine Malfunction in Flight Emergency procedure - Perform.

NOTE

Ng does not pass through the e
EDECU and is a highly reliable signal.

Torque signal may be erratic or drop off for high side conditions driven be EDECU failure.

• 2. PCL (malfunctioning engine) - Retard to set:
     a. Torque 10% below good engine, or
     b. Matched Ng, or
     c. Matched TGT.

3. Land as soon as practicable.

Question 9

ENGINE HIGH-SIDE FAILURE ON DECK

(#1/#2) ENG SPEED HI

Answer 9

*1. PCLs - IDLE.

Question 10

ENGINE LOW-SIDE FAILURE
(#1/#2) ENG SPEED LOW

OR

ENG SPEED LOW

Answer 10

*1. Engine Malfunction in Flight Emergency procedure - Perform.

2. PCL (malfunctioning engine) - momentarily advance to LOCKOUT, then retard to set:
   a. Torque 10% below good engine, or
   b. Matched Ng, or
   c. Matched TGT.
3. Land as soon as practicable.

Question 11

ENGINE TORQUE OR TGT SPIKING/FLUCTUATIONS

TORQUE SPLIT

Answer 11

If an engine instrument is spiking/fluctuating and inducing secondary indications in Ng, Np and/or Nr:
*1. Engine Malfunction in Flight Emergency procedure - Perform.
If fuel contamination is suspected:
*2. Land as soon as possible.

WARNING

PCL movement during engine fluctuations may precipitate an engine failure. Consider performing APU Emergency Start procedure prior to manipulating the PCL. Maintaining a low power setting when moving the PCL will minimize the Nr decay rate if the malfunctioning engine fails.

If engine electronic circuitry is suspected:

3. PCL (malfunctioning engine) - Momentarily advance to LOCKOUT, then retard to set:
   a. Torque 10% below good engine, or
   b. Matched Ng, or
   c. Matched TGT.

If fluctuations persist:
4. PCL (engine in LOCKOUT) - Retard to idle, then retur to FLY.

5. Repeat Steps 3 and 4. for other engine, as required.

If an engine instrument is spiking/fluctuationg with no secondary indications:

6. Land as soon as practicable.

Question 12

DUAL-ENGINE FAILURE

Answer 12

• 1. Autorotation - Establish.
• 2. Immediate Landing/Ditching emergency procedure - perform.

If time and altitude permits:
*3. Engine Air Restart emergency procedure - Perform.

Question 13

SINGLE-ENGINE FAILURE IN FLIGHT
(#1/#2) ENG OUT

AND

TORQUE SPLIT

Answer 13

*1. Engine Malfunction in Flighetform.
emergency procedure -
2. Land as soon as practicable.
Consideration should be given to
performing the following:
3. Engine Shutdown in Flight emergency
procedure.
4. Engine
Air
Restart
procedure.
emergency
5. Single-Engine
Landing
emergency
procedure.

Question 14

ENGINE AIR RESTART

Answer 14

*1. APU Emergency Start procedure - As required.
*2. ENGINE IGNITION switch - NORM.
*3. Fuel selector lever - DIR or XFD
*4. PCL - OFF.
*5. Starter - Engage, motor engine.
“6. PCL - IDLE (TGT 80 °C or less, if time
permits).
*7. PCL) - Advance to FLY after starter
dropout.

WARNING

If APU is unavailable, and a
crossbleed start is necessary,
maximum
torque
available
will be reduced during the
start sequence.
Depending
on operating conditions, level
SOURCE

Question 15

APU EMERGENCY START

Answer 15

*1. ECS
OFF.
*2. AIR SOURCE ECS/START switch
APU.
*3. FUEL PUMP switch - APU BOOST.
*4. APU CTRL switch - ON.
*5. APU GENERATOR switch -
ON.

Question 16

EXTERNAL ENGINE FIRE

Answer 16

*1. Confirm fire.
*2. Engine Malfunction in Flight
emergency procedure - Perform.
*3. PCL (affected engine) - OFF.
*4. Engine T-handle (affected engine) - Pull.
*5. FIRE EXTGH switch MAIN
(RESERVE if required or ac power is
off).
If airborne and fire continues:
*6. Land immediately.
If fire appears extinguished:
*7. Land as soon as possible.
8. Single-Engine
Landing emergency procedure - Perform.
9. Fire extinguisher
- Discharge into
engine compartment.

Question 17

INTERNAL ENGINE FIRE

Answer 17

*1. Starter - Engage. Motor engine.
2. Portable fire extinguisher - As required
3. Starter - Secure (once TGT
decreases below 540 °C).

Question 18

APU FIRE

FIRE

Answer 18

*1. APU T-handle - Pull.
*2. Confirm fire.
*3. FIRE EXTGH switch - RESERVE
(MAIN if required and available).
If airborne and fire continues:
*4. Land immediately.
If fire appears extinguished:
*5. Land as soon as possible.
If on ground:
*6. Fire extinguisher - As required.
7. FUEL PUMP switch - OFF.
8. APU CTRL switch - OFF

Question 19

COCKPIT FIRE/CABIN FIRE

Answer 19

If source is known:
*1. Affected power switches and circuit breakers - OFF/Pull.
*2. Portable fire extinguisher - As required.
If fire continues or source is unknown:
*3. Cabin/doors/vents/ECS
Close/OFF, as required.
*4. Unnecessary electrical equipment and circuit breakers - OFF/Pull.
If fire continues:
*5. Land as soon as possible.

WARNING

Loss of electrical power
to the engine will result in
engine anti-ice activation
regardless of ENG ANTI-ICE
or DE-ICE MASTER switch
position, reducing maximum
torque available by up to
18%. With a malfunctioning
inlet anti-ice valve, torque
available can be reduced
by as much as 49%.
6. Stabilator - Manually slew to zero.
7. NO. 1 and NO. 2 GENERATOR switches - OFF, as required.
8. BATT switch - OFF, as required.
If fire is extinguished:
9. Smoke and Fumes Elimination
emergency procedure - Perform.
10. Land as soon as practicable.

Question 20

SMOKE AND FUMES ELEMINATION

Answer 20

• 1. Airspeed - Adjust, as required.
• 2. Doors/windows/vents - Open
• 3. Aircraft - Yaw, as required.

Question 21

HYDRAULIC SYSTEM WARNING

HYD

Answer 21

*1. Land immediately.

Question 22

1 AND #2 HYD PUMP FAILURE

#1 HYD PUMP
AND
#2 HYD PUMP
AND
#1+#2 HYD PUMP FAIL
AND
BACK UP PUMP ON

Answer 22

• 1. Restrict flight control movement.

* 2. Land as soon as possible.

Question 23

BOOST SERVO HARDOVER

Answer 23

*1. PAC call -
“BOOST. BOOST. BOOST”
*2. SAS/BOOST pushbutton - Off.

Question 24

1 PRIMARY SERVO OR #1 TRANSFER MODULE LEAK

AND

AND

BACK UP PUMP ON

Answer 24

*1. SERVO switch - 1ST OFF.
*2. Land as soon as practicable.
If the BACKUP RSVR LOW caution also
appears or the backup pump fails:
*3. Land as soon as possible.

Note
Be prepared for loss of tail
rotor control.

If the #2 PRI SERVO PRESS caution
and/or HYD warning appears:
*4. Land immediately.

Question 25

#2 PRIMARY SERVO OR #2 TRANSFER MODULE LEAK ``` #2 RSVR LOW AND #2 HYD PUMP AND BACK UP PUMP ON ```

Answer 25

*1. SERVO switch - 2ND OFF. *2. Land as soon as practicable. Note Failure to ensure BACKUP PUMP switch is in AUTO or ON position prior to landing with a #2 HYD PUMP caution present will result in loss of pilot assist servos when the weight on wheels switch is activated. If the BACKUP RSVR LOW caution also appears or backup pump fails: *3. Land as soon as possible. Note Be prepared for loss of the pilot-assist servos. If the #1 PRI SERVO PRESS caution and/or HYD warning appears: *4. Land immediately.

Question 26

UTILITY PUMP CAUTIONS UTILITY HYD PUMP UTILITY HYD PUMP HOT UTILITY HYD RSVR LOW

Answer 26

*1. Stop dome. 2. UTILITY HYD PUMP switch - OFF. 3. Raise/seat dome using AUX ELEC raise. 4. Land as soon as practicable.

Question 27

Main transmission malfunction

Answer 27

``` Possible indications of main transmission imminent failure may include: yaw attitude excursions with no control input, an increase in power required for a fixed collective setting, failure of a main generator or hydraulic pump, increased noise, increased vibration levels, or abnormal fumes in the cabin. ```

Question 28

MADCD

Answer 28

The following should be performed for all emergencies: 1. Maintain control of the aircraft. 2. Alert crew. 3. Determine the precise nature of the problem. 4. Complete the applicable emergency procedure or take action appropriate for the problem. 5. Determine landing criteria and land as required.

Question 29

Landing critias

Answer 29

Land immediately: Execute a landing without delay. Land as soon as possible: Execute a landing at the first site at which a safe landing can be made. Land as soon as practicable: Extended flight is not recommended. The landing site and duration of flight are at the discretion of the PIC.

Question 30

Warning diffinition

Answer 30

Explanatory information about an operating procedure, practice, Or condition, etc., that may result in injury, death, or loss of aircraft if not carefully observed or followed.

Question 31

Caution diffinition

Answer 31

Explanatory information about an operating procedure, practice, or condition, etc., that may result in damage to equipment if not carefully observed or followed.

Question 32

Note diffinition

Answer 32

Explanatory information about an operating procedure, practice, or condition, etc., that must be emphasized.

Question 33

GROUND RESONANCE/UNUSUAL VIBRATIONS ON DECK

Answer 33

``` If ground resonance is encountered and a safe takeoff is possible: *1. Takeoff immediately. *2. Unusual Vibrations in emergency procedure - Perform If ground resonance is not encountered, or a safe takeoff is not possible: *3. Collective - Lower. *4. PCLS - OFF. *5. Rotor brake : Apply as required. Flight WARNING • Ground resonance can occur rapidly (within three seconds), and produce violent lateral, vertical, and circular vibrations resulting in difficulty reaching PCs, pilot-induced oscillations and possible dynamic rollover. • Failure to ensure that ground personnel are clear of the rotor arc and aircraft is free from the deck or chains may result in loss of aircraft or ground personnel. ```

Question 34

TAIL/INTERMEDIATE TRANSMISSION MALFUNCTION Warnings

Answer 34

``` WARNING High power settings require maximum performance of the tail rotor drive system and may precipitate ultimate drive failure. ``` ``` Consideration should be given to transiting at an altitude sufficient to enter an autorotation and performing the applicable steps of the Immediate Landing/Ditching emergency procedure. ```

Question 35

Loss of tail rotor control Warnings

Answer 35

``` WARNING • Following the appearance of the #1 TAIL RTR SERVO caution without the associated BACK UP PUMP ON and #2 TAIL RTR SERVO ON advisories, the aircraft will demonstrate normal yaw responses in flight regimes that do not require excessive tail rotor performance; however, at slower airspeeds, below approximately 40 KIAS, more pronounced effects of loss of tail rotor control may become more apparent. ``` After touchdown, rapid reduction of collective or PCs may cause excessive and uncontrollable yaw rates. ``` • If an uncontrolled right yaw develops at too low of an airspeed, loss of waveoff capability may result. Increasing collective may increase the yaw to unrecoverable rates Performing Loss Of Tail Rotor Drive (Altitude And Airspeed Not Sufficient To Establish Autorotation) procedure may be required. ```