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MH 60-r > EP > Flashcards

EP Flashcards

1
Q

ENGINE MALFUNCTION IN FLIGHT

A

*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.

    1. CONTGCY PWR switch - ON.
    1. Single engine conditions - Establish.
    1. 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.

    1. External cargo/stores/fuel - Jettison/dump, as required.
    1. Identify malfunction.
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2
Q

ABORT START

A

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.

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3
Q

ENGINE MALFUNCTION DURING HOVER/TAKEOFF

A

*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.

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4
Q

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

A

*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.

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5
Q

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

A

*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.

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6
Q

COMPRESSOR STALL

A

*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.

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7
Q

ENGINE HIGH-SPEED SHAFT FAILURE

(#1/#2) DRIVESHAFT FAIL

A

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.

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8
Q

ENGINE HIGH-SIDE FAILURE IN FLIGHT

(#1/#2) ENG SPEED HI

A

*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.

    1. PCL (malfunctioning engine) - Retard to set:
      a. Torque 10% below good engine, or
      b. Matched Ng, or
      c. Matched TGT.
  1. Land as soon as practicable.
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9
Q

ENGINE HIGH-SIDE FAILURE ON DECK

(#1/#2) ENG SPEED HI

A

*1. PCLs - IDLE.

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10
Q

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

OR

ENG SPEED LOW

A

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

  1. 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.
  2. Land as soon as practicable.
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11
Q

ENGINE TORQUE OR TGT SPIKING/FLUCTUATIONS

TORQUE SPLIT

A

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:

  1. 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.

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

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

  1. Land as soon as practicable.
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12
Q

DUAL-ENGINE FAILURE

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

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

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13
Q

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

AND

TORQUE SPLIT

A 
*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.
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14
Q

ENGINE AIR RESTART

A

*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
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15
Q

APU EMERGENCY START

A 
*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.
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16
Q

EXTERNAL ENGINE FIRE

A

*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.

17
Q

INTERNAL ENGINE FIRE

A

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

18
Q

APU FIRE

FIRE

A

*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

19
Q

COCKPIT FIRE/CABIN FIRE

A

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.
20
Q

SMOKE AND FUMES ELEMINATION

A
    1. Airspeed - Adjust, as required.
    1. Doors/windows/vents - Open
    1. Aircraft - Yaw, as required.
21
Q

HYDRAULIC SYSTEM WARNING

HYD

A

*1. Land immediately.

22
Q

1 AND #2 HYD PUMP FAILURE

#1 HYD PUMP
AND
#2 HYD PUMP
AND
#1+#2 HYD PUMP FAIL
AND
BACK UP PUMP ON
A
    1. Restrict flight control movement.

* 2. Land as soon as possible.

23
Q

BOOST SERVO HARDOVER

A

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

24
Q

1 PRIMARY SERVO OR #1 TRANSFER MODULE LEAK

AND

AND

BACK UP PUMP ON

A

*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.

25
Q

2 PRIMARY SERVO OR #2 TRANSFER MODULE LEAK

#2 RSVR LOW
AND
#2 HYD PUMP
AND
BACK UP PUMP ON
A

*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.

26
Q

UTILITY PUMP CAUTIONS

UTILITY HYD PUMP

UTILITY HYD
PUMP HOT

UTILITY HYD
RSVR LOW

A

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

27
Q

Main transmission malfunction

A 
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.
28
Q

MADCD

A

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.
29
Q

Landing critias

A

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.

30
Q

Warning diffinition

A

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.

31
Q

Caution diffinition

A

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

32
Q

Note diffinition

A

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

33
Q

GROUND RESONANCE/UNUSUAL VIBRATIONS ON DECK

A 
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.
34
Q

TAIL/INTERMEDIATE TRANSMISSION MALFUNCTION

Warnings

A 
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.
35
Q

Loss of tail rotor control

Warnings

A 
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.

MH 60-r (2 decks)

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