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Bell 407 > Emergency Procedures > Flashcards

Emergency Procedures Flashcards

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
Q

Cyclic cam jam

A
  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.

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26
Q

Battery hot

A

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
Q

Engine out

A

Fault Condition
NG less than 55 ± 1% and/or
FADEC senses ENGINE OUT.

Verify engine condition. Accomplish
engine failure procedure.

28
Q

Engine overspeed

A

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
Q

FADEC fail during start

A

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
Q

FADEC fail in flight

A

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
Q

RPM (with low RPM
audio)

A

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
Q

RPM (without audio)

A

Fault Condition
NR above 107%.

Increase collective and/or reduce
severity of maneuver. Light will
extinguish when NR decreases
below 107%.

33
Q

XMSN Oil Pressure

A

Fault Condition
Transmission oil pressure is below minimum.

Reduce power; verify fault with
gauge. Land as soon as possible.

34
Q

XMSN Oil Temp

A

Fault Condition
Transmission oil temperature is at or above red line.

Reduce power; verify fault with
gauge. Land as soon as practical.

35
Q

AUTO RELIGHT (white)

A

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
Q

Bagage door

A

Fault Condition
Baggage compartment door not securely latched.

Close door securely before flight. If
light illuminates during flight, land
as soon as practical.

37
Q

Battery RLY

A

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
Q

Check INSTR

A

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
Q

Cyclic Centering

A

Fault Condition
Cyclic stick is not centered.

Reposition cyclic stick to center
position to extinguish CYCLIC
CENTERING light.

40
Q

Engaged

A

Fault Condition
Information system status.

None

41
Q

Engine Anti-ice

A

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
Q

Engine Chip

A

Fault Condition
Ferrous particles in engine oil.

Land as soon as possible.

43
Q

FADEC DEGRADED
(In-flight)

A

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
Q

FADEC DEGRADED
(With engine shutdown)

A

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
Q

FADEC Fault

A

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
Q

FEDEC Manual

A

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
Q

Float Arm

A

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
Q

FLOAT TEST (green)

A

Fault Condition
Float system in test mode.

No corrective action

49
Q

Fuel Filter

A

Fault Condition
Airframe fuel filter in impending bypass.

Land as soon as practical. Clean
before next flight.

50
Q

Fuel Low

A

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
Q

R/Fuel Boost

A

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
Q

L/Fuel Boost

A

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
Q

Fuel Valve

A

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
Q

L/Fuel XFR

A

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
Q

R/Fuel XFR

A

Fault Condition
Right fuel transfer pump has failed.

Land as soon as practical.

56
Q

GEN Fail

A

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
Q

Heater Overtemp

A

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
Q

Hydraulic System

A

Fault Condition
Hydraulic pressure below limit.

Verify HYD SYS switch position.
Accomplish hydraulic system
failure procedure (refer to paragraph
3-6).

59
Q

Litter Door

A

Fault Condition
Litter door not securely latched.

Close door securely before flight. If
light illuminates during flight, land
as soon as practical.

60
Q

Petal Stop

A

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
Q

Restart Fault (white)

A

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
Q

Start (white)

A

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
Q

T/R Chip

A

Fault Condition
Ferrous particles in tail rotor gearbox oil.

Land as soon as possible.

Bell 407 (2 decks)

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