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Emergency Procedures Flashcards

(63 cards)

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1
Q

Land as soon as possible

A

Land without delay at
nearest suitable area
(i.e., open field) at which
a safe approach and
landing is reasonably
assured.

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2
Q

Land as soon as practice

A

Landing site and
duration of flight are at
discretion of pilot.
Extended flight beyond
nearest approved
landing area is not
recommended.

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3
Q

Engine failure in a hover

A
  1. Maintain heading and attitude
    control.
  2. Collective — Adjust to control NR
    and rate of descent. Increase prior to
    ground contact to cushion landing.

NOTE

Amplitude of collective movement is
a function of height above ground.
Any forward airspeed will aid in
ability to cushion landing.
3. Complete helicopter shutdown.

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4
Q

Engine failure in flight

A
  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.

  1. 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.

  1. Attempt engine restart if ample
    altitude remains. (Refer to ENGINE
    RESTART, paragraph 3-3-B.)
  2. FUEL VALVE switch — OFF.
  3. At low altitude:
    - Throttle — OFF.
    - Flare to lose airspeed.
  4. 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.
  5. Complete helicopter shutdown.
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5
Q

Engine restart in auto mode

A
  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.

  1. FUEL VALVE switch — ON.
  2. Throttle — OFF.
  3. START switch — Hold to start
    position (start will latch after throttle
    is placed to idle).
  4. NG — Between 12 and 50%.
  5. Throttle — IDLE.
  6. MGT — Monitor.
  7. Engine oil pressure — Check.
  8. Throttle — Advance smoothly to FLY
    detent position.

If restart is unsuccessful, abort start and
secure engine as follows:
11. Throttle — OFF.
12. FUEL VALVE switch — OFF.
13. Accomplish autorotative descent
and landing.

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6
Q

Engine restart in manual made

A
  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.

  1. Throttle — OFF.
  2. FADEC MODE switch — MAN.
  3. FUEL VALVE switch — ON.
  4. START switch — Hold to start
    position (starter will not latch).
  5. NG — 12%.
  6. Throttle — Slowly advance out of
    cutoff and stop advancing throttle at
    light off.
  7. MGT — Allow to peak.
  8. Throttle — Increase fuel flow by
    modulating throttle to maintain MGT
    within limits.
  9. START switch — Release at 50% NG.
  10. Engine oil pressure — Check.
  11. Throttle — Advance smoothly and
    modulate to 100% NP.

If restart is unsuccessful, abort start and
secure engine as follows:14. Throttle — OFF.
15. FUEL VALVE switch — OFF.
16. Accomplish autorotative descent
and landing.

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7
Q

Engine underspeed

A
  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 gauge indicated
    NG.
  4. FADEC MODE switch — MAN.
  5. NR — Maintain 95 to 100% with
    throttle and collective.
  6. Land as soon as practical.
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8
Q

Engine overspeed

A
  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.
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9
Q

Engine compresor stall/surge

A
  1. Collective — Reduce power,
    maintain slow cruise flight.
  2. MGT and NG — 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. MGT and NG — Monitor for normal
response.
8. Land as soon as practical.

If pilot elects to shut down engine:
9. Enter autorotation.
10. Throttle — OFF.
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.

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10
Q

Engine hot start/shutdown

A
  1. Throttle — OFF.
  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.

  1. STARTER switch — Ensure starter is
    motoring engine until MGT stabilizes
    at normal temperature.
  2. Shut down helicopter.
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11
Q

Engine oil pressure high, low or fluctuating

A
  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.
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12
Q

Driveshaft failure

A
  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.

  1. Cyclic — Adjust to obtain desired
    autorotative airspeed.

NOTE
To maintain tail rotor effectiveness
do not shutdown engine.

  1. Landing — Complete autorotative
    landing.
  2. Complete helicopter shutdown.
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13
Q

FADEC Failure

A
  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 advisory light 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.

  1. Land as soon as practical.
  2. Normal shutdown if possible.
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14
Q

Engine fire on the ground

A
  1. Throttle — OFF.
  2. FUEL VALVE switch — OFF.
  3. GEN switch — OFF.
  4. BATT switch — OFF.
  5. Rotor brake (if installed) — Engage.
  6. Exit helicopter.
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15
Q

Engine fire in flight

A
  1. In-flight — Immediately enter
    autorotation.
  2. Throttle — OFF.
  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.

NOTE
Do not restart engine until corrective
maintenance has been performed.

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16
Q

Cabin smoke or fumes

A
  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.
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17
Q

Electrical fire

A
  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 KIAS 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, 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.

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18
Q

Complete loss of tail rotor thrust in a hover

A

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

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19
Q

Complete loss of tail rotor in flight

A

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.

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20
Q

Loss of hydraulic pressure

A
  1. Reduce AIRSPEED to 70 to 100 KIAS.
  2. HYD SYSTEM circuit breaker — Out.
    If hydraulic power is not restored,
    push breaker in.
  3. HYD SYS switch — HYD SYS; OFF if
    hydraulic power is not restored.
  4. For extended flight set comfortable
    AIRSPEED, up to 120 KIAS, to
    minimize control forces.
  5. Land as soon as practical.
  6. A run-on landing at effective
    translational lift speed
    (approximately 15 knots) is
    recommended.
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21
Q

Flight control actuator malfunction

A
  1. Attitude — Maintain.
  2. HYD SYS switch — OFF.
  3. AIRSPEED — Set to 70 to 100 KIAS.
  4. Land as soon as possible using
    procedure from paragraph 3-6-A.
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22
Q

Generator failure

A
  1. GENERATOR FIELD and
    GENERATOR RESET circuit
    breakers — Check in.
  2. GEN switch — RESET; then GEN.
  3. If power is not restored, place GEN
    switch to OFF; land as soon as
    practical.

NOTE
With generator OFF, a fully charged
battery will provide approximately 21
minutes of power for basic helicopter
and one VHF COMM radio (35
minutes with optional 28 ampere/
hour battery).

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23
Q

Excessive electrical load

A
  1. GEN switch — OFF.
  2. BATT switch — OFF.
  3. FUEL BOOST/XFR LEFT circuit
    breaker switch — LEFT (on).
    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, 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 ampere/
hour battery).
4. Airspeed — 60 KIAS or less.

NOTE
Pedal stop disengages with loss of
electrical power.
5. Land as soon as practical.

NOTE
When throttle is repositioned to the
idle stop (during engine shutdown)
the PMA will go offline and the
engine may flame out.

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24
Q

Dual fuel transfer failure

A
  1. LEFT and RIGHT FUEL BOOST/XFR
    circuit breaker switches — Check
    ON.
  2. Determine FUEL QTY in forward cell.
  3. Subtract quantity of fuel trapped in
    forward cell from total to determine
    usable fuel remaining.
  4. Plan landing accordingly.
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25
Cyclic cam jam
1. Helicopter pitch attitude — Maintain normal pitch attitudes with forward or aft cyclic force. CAUTION DO NOT TURN HYDRAULIC BOOST OFF 2. Land as soon as practical.
26
Battery hot
Fault Condition Battery overheating. Turn BATT switch OFF and land as soon as practical. If BATTERY RLY light illuminates, turn GEN switch OFF if conditions permit. Land as soon as possible.
27
Engine out
Fault Condition NG less than 55 ± 1% and/or FADEC senses ENGINE OUT. Verify engine condition. Accomplish engine failure procedure.
28
Engine overspeed
Fault Condition NG greater than 110% or NP versus TORQUE is above maximum continuous limit (102.1% NP at 100% TORQUE to 108.6% NP at 0% TORQUE). Adjust throttle and collective as necessary. Determine if engine is controllable; if not, shut down. Maintenance action required before next flight.
29
FADEC fail during start
Fault Condition FADEC has detected a serious malfunction. Close throttle immediately. Engage starter to reduce MGT. Applicable maintenance action required prior to next flight.
30
FADEC fail in flight
Fault Condition FADEC has detected a serious malfunction. Dependent on flight profile (takeoff, climb, cruise, or descent) and power setting at time of failure, the transition to manual mode may result in an NR/NP overspeed or underspeed within 2 to 7 seconds following activation of FADEC fail horn and illumination of FADEC FAIL warning light. Any other FADEC related lights may be illuminated. Accomplish FADEC FAILURE procedure (paragraph 3-3-K). Applicable maintenance action required prior to next flight.
31
RPM (with low RPM audio)
Fault Condition NR below 95%. Reduce collective and ensure throttle is in FLY detent position. Light will extinguish and audio will cease when NR increases above 95%.
32
RPM (without audio)
Fault Condition NR above 107%. Increase collective and/or reduce severity of maneuver. Light will extinguish when NR decreases below 107%.
33
XMSN Oil Pressure
Fault Condition Transmission oil pressure is below minimum. Reduce power; verify fault with gauge. Land as soon as possible.
34
XMSN Oil Temp
Fault Condition Transmission oil temperature is at or above red line. Reduce power; verify fault with gauge. Land as soon as practical.
35
AUTO RELIGHT (white)
Fault Condition Engine igniter is operating. None NOTE AUTO RELIGHT light will be illuminated when ignition system is activated.Ignition system is activated: 1 - during start sequence 2 - in MANUAL mode with NG above 55% 3 - with FADEC detection of engine out condition with NG above 50%.
36
Bagage door
Fault Condition Baggage compartment door not securely latched. Close door securely before flight. If light illuminates during flight, land as soon as practical.
37
Battery RLY
Fault Condition Battery relay has malfunctioned to closed (ON) position with BATT switch OFF. Battery is still connected to DC BUSS. If BATTERY HOT light is illuminated, turn GEN switch OFF if conditions permit. Land as soon as possible.
38
Check INSTR
Fault Condition TRQ, MGT, or NG is about to or has detected an exceedance. Flashing LCD trend arc and digital display indicates impending exceedance. Letter E in digital display indicates an exceedance has occurred. Reduce engine power if possible. Press INSTR CHK button to display magnitude of exceedance. Refer to BHT-407-MD-1.
39
Cyclic Centering
Fault Condition Cyclic stick is not centered. Reposition cyclic stick to center position to extinguish CYCLIC CENTERING light.
40
Engaged
Fault Condition Information system status. None
41
Engine Anti-ice
Fault Condition ANTI-ICE switch ON. Engine receiving anti-icing air. If light (if installed) remains illuminated with ENGINE ANTI-ICE switch OFF, avoid operations requiring maximum power.
42
Engine Chip
Fault Condition Ferrous particles in engine oil. Land as soon as possible.
43
FADEC DEGRADED (In-flight)
Fault Condition FADEC ECU operation is degraded which may result in NR droop, NR lag, or reduced maximum power capability. Remain in AUTO mode. Fly helicopter smoothly and nonaggressively. Land as soon as practical. NOTE It may be necessary to use FUEL VALVE switch to shut down engine after landing. Applicable maintenance action required prior to next flight.
44
FADEC DEGRADED (With engine shutdown)
Fault Condition FADEC ECU has recorded a fault during previous flight or a current fault has been detected. Position throttle to idle; if light extinguishes, fault is from previous flight. Applicable maintenance action required prior to next flight.
45
FADEC Fault
Fault Condition PMA and or MGT, NP or NG automatic limiting circuit(s) not functional. Remain in AUTO mode. Land as soon as practical. Applicable maintenance action required prior to next flight.
46
FEDEC Manual
Fault Condition FADEC is operating in MANUAL mode. No automatic governing is available. AUTO RELIGHT light will be illuminated when FADEC MODE switch is depressed. Fly helicopter smoothly and nonaggressively. Maintain NR with coordinated throttle and collective movements. Land as soon as practical.
47
Float Arm
Fault Condition FLOAT ARM switch is ON. Float inflation solenoid is armed. Normal operation for takeoff and landing over water. FLOAT ARM switch — OFF. If light remains illuminated, FLOATS circuit breaker — Out. Land as soon as practical. NOTE With float inflation solenoid armed, flight should not exceed 60 KIAS and 500 feet AGL.
48
FLOAT TEST (green)
Fault Condition Float system in test mode. No corrective action
49
Fuel Filter
Fault Condition Airframe fuel filter in impending bypass. Land as soon as practical. Clean before next flight.
50
Fuel Low
Fault Condition 100 ±10 pounds of fuel remain in aft tank. NOTE Aft fuel tank quantity is the total fuel quantity less the forward fuel tank quantity. Verify FUEL QTY of aft fuel tank. Land as soon as practical.
51
R/Fuel Boost
Fault Condition Right fuel boost pump has failed. If practical, descend below 8000 feet HP if fuel is Jet A or 4000 feet HP if fuel is Jet B to prevent fuel starvation if other fuel boost pump fails or has low output pressure. Land as soon as practical. WARNING IF BOTH FUEL BOOST PUMPS FAIL, ALTITUDE MUST BE REDUCED TO BELOW 8000 FEET HP (JET A) OR 4000 FEET Hp (JET B). LAND AS SOON AS POSSIBLE.
52
L/Fuel Boost
Fault Condition Left fuel boost pump has failed If practical, descend below 8000 feet HP if fuel is Jet A or 4000 feet HP if fuel is Jet B to prevent fuel starvation if other fuel boost pump fails or has low output pressure. Land as soon as practical. WARNING IF BOTH FUEL BOOST PUMPS FAIL, ALTITUDE MUST BE REDUCED TO BELOW 8000 FEET HP (JET A) OR 4000 FEET Hp (JET B). LAND AS SOON AS POSSIBLE.
53
Fuel Valve
Fault Condition Fuel valve position differs from FUEL VALVE switch indication or FUEL VALVE circuit breaker out. Check FUEL VALVE circuit breaker in. Land as soon as practical. If on ground, cycle FUEL VALVE switch.
54
L/Fuel XFR
Fault Condition Left fuel transfer pump has failed. Land as soon as practical. NOTE Under normal fuel transfer conditions, helicopters S/N 53000 through 53174 L/FUEL XFR and R/FUEL XFR lights will illuminate for 2.5 minutes and then extinguish. This indicates transfer is complete and transfer pumps have been automatically turned off. Helicopters S/N 53175 and subsequent inhibit illumination of the lights. CAUTION IF BOTH FUEL TRANSFER PUMPS FAIL, UNUSABLE FUEL MAY BE AS HIGH AS 151.0 POUNDS DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELL. LAND AS SOON AS PRACTICAL.
55
R/Fuel XFR
Fault Condition Right fuel transfer pump has failed. Land as soon as practical.
56
GEN Fail
Fault Condition Generator not connected to DC BUSS. Verify fault with AMPS gauge. GEN switch — RESET, then ON. If GEN FAIL light remains illuminated, GEN switch — OFF. Land as soon as practical.
57
Heater Overtemp
Fault Condition An overtemp condition has been detected by a temperature probe either under pilot seat, copilot seat, or in vertical tunnel. Turn HEATER switch OFF immediately.
58
Hydraulic System
Fault Condition Hydraulic pressure below limit. Verify HYD SYS switch position. Accomplish hydraulic system failure procedure (refer to paragraph 3-6).
59
Litter Door
Fault Condition Litter door not securely latched. Close door securely before flight. If light illuminates during flight, land as soon as practical.
60
Petal Stop
Fault Condition Pedal Restrictor Control Unit has detected a failure of part of system. VNE — 60 KIAS. PEDAL STOP emergency release — Pull. Land as soon as practical.
61
Restart Fault (white)
Fault Condition FADEC ECU has detected a fault which will not allow engine to be restarted in AUTO mode. Remain in AUTO mode. Plan landing site accordingly. Applicable maintenance action required prior to next flight. NOTE When throttle is repositioned to idle stop (during engine shutdown) the PMA will go offline and engine may flameout.
62
Start (white)
Fault Condition Start relay is in START mode. If START switch has not been engaged and there is zero indication on AMPS gage; START relay has malfunctioned and helicopter is on battery power. START circuit breaker — Out. Land as soon as practical.
63
T/R Chip
Fault Condition Ferrous particles in tail rotor gearbox oil. Land as soon as possible.

Bell 407 (2 decks)

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