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21 Cards in this Set

  • Front
  • Back
  • 3rd side (hint)
Audio Tones:

Engine Out

Low Rotor RPM

Airspeed above VNE

FADEC Failure Continuous

Engine Out Fastpulsing tone

Low Rotor RPM Continuous tone

Airspeed above VNE Continuous"ting"
FADEC Failure Continuous "ding dong" tone
Engine Out, Low RPM, Above VNE, FADEC Fail
3-2. DEFINITIONS.
LAND AS SOON AS POSSIBLE
Land without delay at the nearest suitable area (I.e., open field) at which a safe approach and
landing is reasonably assured
3-2. DEFINITIONS.
LAND AS SOON AS PRACTICAL
Landing site and duration of flight are at discretion of pilot.
Extended flight beyond nearest approved landing area is not recommended.
3-3-A-1. ENGINE FAILURE HOVERING
PROCEDURE

1. Maintain heading and attitude
control.

2. Collective-Adjust to control NR
and rate of descent. Increase prior to ground contact to cushion landing.
1. Left yaw.

2.ENGINE OUT message, MASTER
W/C light! and RPM warning light


3.Engine instruments indicate power
loss.

4.MFD switches to ENGINE page.

5. Engine out audio activated when NG drops below 55%.

6. NR decreasing with RPM warning
light and audio on when NR drops
below 95%.
3-3-A-2. ENGINE FAILURE-IN FLIGHT
· PROCEDURE

1. Maintain heading and attitude
control.

2. Collective-Adjust as required to

maintain 85 to 107% NR·

NOTE:
Maintaining NR at high end of
operating range will provide
maximum rotor energy to
accomplish landing, but will cause
an increased rate of descent.

3. Cyclic-Adjust to obtain desired autorotative airspeed.

NOTE:
Maximum airspeed for steady state
autorotation is 100 KIAS. Minimum
rate of descent airspeed is 55 KIAS.
Maximum glide distance airspeed is
80 KIAS.

4. Attempt engine restart if ample
altitude remains (paragraph 3-3-B).

5. FUEL VALVE switch-OFF.

6. At low altitude
a. Throttle-Closed.
b. Flare to lose airspeed.

7. Apply collective as flare effect
decreases to further reduce forward
speed and cushion landing.
Upon ground contact, collective shall be reduced smoothly while
maintaining
cyclic in neutral or centered position.
8. Complete helicopter shutd own.
1. Left yaw.

2.ENGINE OUT message, MASTER
W/C light, and RPM warning light
illuminated.

3.Engine instruments indicate power loss.

4. MFD switches to ENGINE page.

5. Engine out audio activated when NG drops below 55%.

6. NR decreasing with RPM warning
light and audio on when NR drops
below 95%.
3-3-B. ENGINE RESTART IN FLIGHT

An engine restart may be attempted in flight if
time and altitude permit.

IF CAUSE OFFAILURE IS OBVIOUSLY MECHANICAL, AS
EVIDENCED BY ABNORMAL
METALLIC OR GRINDING SOUNDS,
DO NOT ATTEMPT A RESTART.
AUTO or MANUAL
3-3-B-1. RESTART-AUTOMATIC MODE

NO RESTART FAULT OR FADEC MANUAL LIGHTS ILLUMINATED.

· PROCEDURE:

1. Collective-Adjust to maintain 85 to
107% NR·

2. AIRSPEED-Adjust as desired.

NOTE :
Minimum rate of descent airspeed of 55 KIAS and minimum Nr will allow
pilot more time for air restart.

3. FUEL VALVE switch-ON.

4. Throttle-Cutoff.

5. START switch-Hold to start
position (start will latch after throttle
is placed to idle).

6. Nr-Between 12% and 50%.

7. Throttle-Idle.

8. PSI-Monitor start limitations.

9. Engine oil pressure-Check.

10. Throttle-Advance smoothly to FLY detent position.

If restart is unsuccessful, abort start and secure engine as follows:

11. Throttle-Closed.

12. FUEL VALVE switch-OFF.

13. Accomplish autorotative descent
and landing.
3-3-B-2. RESTART-MANUAL MODE
RESTART FAULT OR FADEC MANUAL LIGHTS ILLUMINATED.
· PROCEDURE

1. Collective-Adjust to maintain 85 to
107% NR·

2. AIRSPEED-Adjust as desired.

NOTE
Minimum rate of descent airspeed of 55 KIAS and minimum Nr will allow
pilot more time for air restart.

3. Throttle-Closed.

4. FADEC MODE switch-MAN.

5. FUEL VALVE switch-ON.

6. START switch Hold to start position (starter will not latch).

7. NG-12%.

8. Throttle-Slowly advance out of
cutoff and stop advancing throttle at
light off.

9. PSI-Allow to peak.

10. Throttle-Increase fuel flow by
modulating throttle to maintain MGT within limits.

11. START switch-Release at 50% Ng

12. Engine oil pressure-Check.

13. Throttle-Advance smoothly and
modulate to 100% Np

If restart is unsuccessful, abort start and secure engine as follows

14. Throttle-Closed.

15. FUEL VALVE switch-OFF.

16. Accomplish autorotative descent
and landing.
3-3-C. ENGINE UNDERSPEED
No caution/warning/advisory messages illuminated.
• INDICATIONS...
• PROCEDURE:

1.Collective — Adjust as required to maintain 85 to 107% NR.

2.Throttle — Confirm in FLY detent position.

3.Throttle — Position throttle to the approximate bezel position that coincides with the PSI indicated NG.

4.FADEC MODE switch — MAN.

5. NR — Maintain 95 to 100% with throttle and collective.

6.Land as soon as practical.
:
1. Decrease in PSI.
2. Subsequent decrease in NP.
3. Possible decrease in NR.
3-3-D. ENGINE OVERSPEED
No caution/warning/advisory messages illuminated.
• INDICATIONS:
• PROCEDURE:
1. Throttle — Retard.

2. NG or NP — Attempt to stabilize with throttle and collective.

3.FADEC MODE switch — MAN.

4. NR — Maintain 95 to 100% with throttle and collective.

CAUTION:
IF UNABLE TO MAINTAIN NR, NP, OR PSI, PREPARE FOR A POWER OFF LANDING BY LOWERING COLLECTIVE AND SHUTTING DOWN ENGINE.
1.Increase in NR.
2.Increase in NP.
3. Increase in PSI.
3-3E.
ENGINE COMPRESSOR STALL/ SURGE
• INDICATIONS:
• PROCEDURE:
1.Collective — Reduce power, maintain slow cruise flight.
2.PSI — Check for normal indications.
3.ENG ANTI ICE switch — ON.
4.PART SEP switch (if installed) — ON. 5.HEATER switch (if installed) — ON.

NOTE:
Severity of compressor stalls will dictate if engine should be shut down and treated as an engine failure. Violent stalls can cause damage to engine and drive system components, and must be handled as an emergency condition. Stalls of a less severe nature (one or two low intensity pops) may permit continued operation of engine at a reduced power level, avoiding condition that resulted in compressor stall.

If pilot elects to continue flight:

6.Collective — Increase slowly to achieve desired power level.

7.PSI — Monitor for normal response.

8.Land as soon as practical.

If pilot elects to shut down engine:

9. Enter autorotation.

10. Throttle — Closed.

11.FUEL VALVE switch — OFF.

12.Collective — Adjust as required to maintain 85 to 107% NR.

13.Cyclic — Adjust as required to maintain desired airspeed.

14. Prepare for power-off landing.
1. Engine pops.
2.High or erratic MGT.
3. Decreasing or erratic NG or NP.
4. PSI oscillations.
3-3-F. ENGINE HOT START/SHUTDOWN
• INDICATIONS:
PROCEDURE:

1. Throttle — Closed.

2.FUEL VALVE switch — OFF.

NOTE
Starter will remain engaged until MGT decreases to 150°C and then automatically disengage. Starter may be manually engaged by holding STARTER switch forward.

3.STARTER switch — Ensure starter is motoring engine until MGT stabilizes at normal temperature.

4. Shut down helicopter.
1. PSI needle increases rapidly.
2. Excessive MGT.
3. Visible smoke or fire.
3-3-G.ENGINE OIL PRESSURE LOW, HIGH, OR FLUCTUATING
• INDICATIONS:
• PROCEDURE:

1. Engine oil pressure below minimum.
a.Monitor engine oil pressure and temperature.
b.Land as soon as possible.

2.Engine oil pressure above maximum or fluctuating abnormally.
a.Monitor engine oil pressure and temperature.
b.Land as soon as practical
1. Engine oil pressure below minimum.
2.Engine oil pressure above maximum or fluctuating abnormally.
3-3-H ENGINE OIL TEMPERATURE HIGH
INDICATION

1. Engine oil temperature Increasing
above normal.
2.Engine oil temperature above maximum.

• PROCEDURE:

1.Land as soon as practical.
3-3-I. DRIVESHAFT FAILURE

WARNING:
FAILURE OF MAIN DRIVESHAFT TO TRANSMISSION WILL RESULT IN COMPLETE LOSS OF POWER TO MAIN ROTOR. ALTHOUGH COCKPIT INDICATIONS FOR A DRIVESHAFT FAILURE ARE SIMILAR TO AN ENGINE OVERSPEED, IT IS IMPERATIVE THAT AUTOROTATIVE FLI GHT PROCEDURES BE ESTABLISHED IMMEDIATELY. FAILURE TO REACT IMMEDIATELY TO LOW RPM AUDIO, RPM LIGHT AND NP/NR TACHOMETER CAN RESULT IN LOSS OF CONTROL.

• INDICATIONS:
1. Left yaw.
2.Rapid decrease in NR. 3.Rapid increase in NP.
4. Low RPM audio.
5. Illumination of RPM light. 6.MFD switches to ENGINE page.
7.Possible increase in noise level due to overspeeding engine and driveshaft breakage.

NOTE:
Engine overspeed trip system will activate at 118.5% NP causing fuel flow to go to minimum. After initial overspeed, FADEC will adjust fuel flow to maintain engine at 100% NP.
• PROCEDURE:
1. Maintain heading and attitude control.

2.Collective — Adjust as required to maintain 85 to 107% NR.

NOTE:
Minimum rate of descent airspeed is 55 KIAS. Maximum glide distance airspeed is 80 KIAS.

3.Cyclic — Adjust to obtain desired autorotative airspeed.

NOTE:
To maintain tail rotor effectiveness do not shut down engine.

4. Landing — Complete autorotative landing.

5. Complete helicopter shutdown
• INDICATIONS:
1. Left yaw.
2.Rapid decrease in NR.
3.Rapid increase in NP.
4. Low RPM audio.
5. Illumination of RPM light.
6.MFD switches to ENGINE page.
7.Possible increase in noise level due to overspeeding engine and driveshaft breakage.
3-3-J. FADEC FAILURE
NOTE
Takeoff power may not be available in the MAN mode. Maximum continuous power will be available for all ambient conditions.
• INDICATIONS:(Hint)
1.Throttle — If time permits, match throttle bezel position to NG indication.

2. NR/NP — Maintain 95 to 100% with collective and throttle.

3.FADEC MODE switch — Depress one time, muting FADEC fail audio. AUTO RELIGHT message illuminates.
NOTE:
Depressing FADEC MODE switch one time, will only mute FADEC fail audio and activate ignition. This step should not be accomplished until pilot is firmly established in MAN control.

4.Land as soon as practical.

5.Normal shut down if possible.
1. FADEC fail audio activated.
2.FADEC FAIL warning message illuminated.
3.FADEC MANUAL caution message illuminated.
4. RESTART FAULT advisory message illuminated.
5.FADEC MODE switch MAN light illuminated.
FIRE
3-4-A. ENGINE FIRE ON GROUND
• INDICATIONS:(Hint)
• PROCEDURE:
1. Throttle — Closed.
2.FUEL VALVE switch — OFF.
3.GEN switch — OFF.
4.BATT switch — OFF.
5.Rotor brake (if installed) — Engage.
6. Exit helicopter.
1. Smoke.
2. Fumes.
3. Fire.
FIRE
3-4-B. ENGINE FIRE DURING FLIGHT
• INDICATIONS:(Hint)
• PROCEDURE:
1.In flight — Immediately enter autorotation.
2. Throttle — Closed.
3.FUEL VALVE switch — OFF.
4.If time permits, FUEL BOOST/XFR circuit breaker switches — OFF.
5. Execute autorotative descent and landing.
6.BATT switch — OFF.
1. Smoke.
2. Fumes.
3. Fire.
3-4-C. CABIN SMOKE OR FUMES
• INDICATIONS:
• PROCEDURE:
1.In flight — Start descent.

2.AIR COND BLO switch (if installed) — OFF.

3.HEATER switch (if installed) — OFF.

4.All vents — Open.

5.Side windows — Open.

If time and altitude permits:

6.Source — Attempt to identify and secure.
7.If source is identified and smoke and/ or fumes still persist — Land as soon as possible.

8.If source is identified and smoke and/ or fumes are cleared — Land as soon as practical
1. Smoke.
2. Fumes.
3-4-D. ELECTRICAL FIRE
• INDICATIONS:(Hint)
• PROCEDURE:
1.Vents/side windows — Open, as required; ventilate cabin.

2. Begin descent.

NOTE
Maintain safe flight condition and land as soon as possible.

If source of smoke or fire can be positively identified, remove electrical power from the affected equipment by switching it off via switch or circuit breaker.

If source of the smoke or fire cannot be positively identified:

3.GEN switch — OFF.

4.Land as soon as practical.

If smoke/fumes do not decrease:
5.Airspeed — 60 knots or less.

6.BATT switch — OFF.

7.FUEL BOOST/XFR LEFT circuit breaker switch — LEFT (on).

If smoke/fumes do not decrease:

8.Land as soon as possible.

WARNING:

PRIOR TO BATTERY DEPLETION, ALTITUDE MUST BE REDUCED BELOW 8000 FEET HP (JET A) OR 4000 FEET HP (JET B). UNUSABLE FUEL MAY BE AS HIGH AS 151.0 POUNDS AFTER THE BATTERY IS DEPLETED DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELLS.

NOTE:
With battery and generator OFF, only standby airspeed and altimeter will be available.

NOTE:
With battery and generator OFF, an 80% charged battery will operate left fuel boost pump and left fuel transfer pump for approximately 1.7 hours (2.8 hours with optional 28 amp-hour battery).

NOTE:
Pedal stop disengages with loss of electrical power.
When throttle is repositioned to the idle stop (during engine shutdown), the PMA will go offline and the engine may flame out.

1.Smoke fumes or fire.
2. Possible indication of abnormal amps.
3-5-A.COMPLETE LOSS OF TAIL ROTOR THRUST
This is a situation involving a break in drive system (e.g., severed driveshaft), wherein tail rotor stops turning and delivers no thrust.
• INDICATIONS:(Hint)
• PROCEDURE:
3-5-A-1. HOVERING

Close throttle and perform a hovering autorotation landing. A slight rotation can be expected on touchdown.

3-5-A-2. IN FLIGHT

Reduce throttle to idle, immediately enter autorotation, and maintain a minimum airspeed of 55 KIAS during descent.

NOTE:
When a suitable landing site is not available, vertical fin may permit controlled flight at low power levels and sufficient airspeed.
During final stages of approach, a mild flare should be executed, making sure all power to rotor is off. Maintain helicopter in a slight flare and smoothly use collective to execute a soft, slightly nose-high landing. Landing on aft portion of skids will tend to correct side drift. This technique will, in most cases, result in a run-on type landing.

CAUTION

IN A RUN-ON TYPE LANDING AFTER TOUCHING DOWN, DO NOT USE CYCLIC TO REDUCE FORWARD SPEED.
1.Uncontrollable yawing to right (left side slip).
2. Nose down tucking.
3. Possible roll of fuselage.

NOTE
Severity of initial reaction of helicopter will be affected by AIRSPEED, CG, power being used, and HD.