Bell 407 Emergency/ Malfunction
Procedures
Export Classification C, ECCN EAR99
In event of helicopter control and Safe Flight Path
Emergency first
Priority is
Tripped CB can be Should not be reset unless deemed necessary for safe
reset how many times completion of the flight and then only once
Meaning - Land as land without delay at the nearest suitable area (i.e.
soon as possible open field) at which a safe approach and landing is
reasonably assured.
meaning Land as Landing site and duration of flight are at discretion of
soon as Practical pilot. Extended flight beyond nearest approved
landing area is not recommended.
Engine Failure - 1. Left Yaw
Hovering - Indications 2. ENGINE OUT and RPM warning lights Illuminated.
3. Engine Instruments indicate power loss
4. Engine Out audio activated when NG drops below
55%
5. Nr decreasing with RPM warning light and audio on
when Nr drops below 95%
Engine Failure - 1. maintain heading and attitude control
Hovering Procedure 2. Collective - Adjust to control Nr and rate of descent.
Increase prior to ground contact to cushion landing
3. Land
4. Shut down helicopter
Engine Failure - 1. Left Yaw
Inflight - Indications 2. ENGINE OUT and RPM warning lights Illuminated.
3. Engine Instruments indicate power loss
4. Engine Out audio activated when NG drops below
55%
5. Nr decreasing with RPM warning light and audio on
when Nr drops below 95%
Engine Failure - 1. maintain heading and attitude control
Inflight - Procedures 2. Collective - Adjust as required to maintain 85 to
107% Nr
3. Cyclic adjust to obtain desired autorotative
AIRSPEED
4. Attempt engine restart if ample altitude remains
(company policy is not when single pilot)
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. Collective
shal be reduced smoothly while maintaining Cyclic in
neutral or centered position.
8. Complete Helicopter Shutdown
Engine Underspeed 1. Decrease in Ng
(no Caution, 2. Subsequent Decrease in Np
Warning/Advisory 3. Possible Decrease in Nr
Lights illuminated) - 4. Decrease in TRQ
Indications
Engine Underspeed 1. Collective - Adjust as required to maintain 85 to
(no Caution, 107% Nr
Warning/Advisory 2. Throttle - Confirm in FLY detent position
Lights illuminated) - 3. Throttle - Position to the approximate bezel position
Procedures that coincides with the gage indicated Ng
4. FADEC MODE switch - MAN
5. Nr - Maintain 95 to 100% with throttle and collective
6. Land as soon as practical
Engine Overspeed 1. Increase in Nr
(no Caution, 2. Increase in Np
Warning/Advisory 3. Increase in Ng
Lights illuminated) - 4. Increase in TRQ
Indications
Engine Overspeed 1. Throttle Retard
(no Caution, 2. Ng or Np attempt to stabilize with Throttle and
Warning/Advisory collective
Lights illuminated) - 3. FADEC MODE switch - MAN
Procedures 4 Nr - Maintain 95 to 100% with Throttle and collective
Engine Compressor 1. Engine Pops
Stall - Indications 2. High or Erratic MGT
3. Decreasing or Erratic Ng or Np
4. TRQ oscillations
Engine Compressor 1. Collective - Reduce Power, Maintain slow Cruise
Stall - Procedure Part flight.
one 2. MGT and Ng - Check for Normal indications
3. ENG ANTI ICE Switch - ON
4. PART SEP Switch - ON
5. HEATER Switch - ON
If Pilots Elects to continue flight:
6. Collective - Increase slowly to achieve desired
power level
7 MGT and Ng - Monitor for normal response
8. Land and soon as Practical
Engine Compressor If Pilot Elects to shut down the engine:
Stall - Procedure Part 9. Enter Autorotation
two 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.
Engine Hot 1. Excessive MGT
Start/Shutdown - 2. Visible Fire/Smoke
Indications
Engine Hot 1. Throttle Closed
Start/Shutdown - 2. FUEL VALVE switch - OFF
Procedures 3. STARTER Switch - Ensure starter is motoring engine
until MGT stabilizes at Normal temperature
4. Shut Down Helicopter
Engine Oil Pressure 1. Engine oil pressure and temperature - Monitor
Low or Fluctuating 2. Land ASA Practical
Engine Oil Land ASA Practical
Temperature High
Driveshaft Failure - 1. Left Yaw
Indications 2. Rapid Decrease in Nr
3. Rapid increase in Np
4. Low RPM Audio Horn
5. Illumination of RPM Light
6. Possible increase in noise level due to overspeeding
engine and driveshaft breakage
Driveshaft Failure - 1. Maintain Heading and Attitude
Driveshaft Failure - 1. Maintain Heading and Attitude
Procedures 2. Collective - Adjust as required to maintain 85 to
107% Nr
3. Cyclic - Adjust to obtain desired Autorotative
airspeed
Note - Do not shut down engine
4. Landing - Complete autorotative landing
5. Complete helicopter Shutdown
FADEC Failure - 1. FADEC Fail Audio Activate
Indications 2. FADEC FAIL warning light illuminated
3. FADEC MANUAL caution light illuminated
4. AUTO RELIGHT advisory light illuminated
5. FADEC MODE switch MAN light illuminated
FADEC Failure - 1. Throttle - If time permits, match throttle bezel
Procedure position to Ng indication
2. Nr/Np - Maintain 95-100% with collective and
throttle
3. FADEC MODE Switch - Depress one time, Muting
FADEC fail audio.
4. Land as soon as Practical
5. Normal Shutdown if possible
Engine Fire on 1. Throttle - Closed
Ground 2. FUEL VALVE switch - OFF
3. GEN switch - OFF
4. BATT switch - OFF
5. Rotor brake - Engage
Exit Helicopter
Engine Fire In flight 1. Inflight - 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
Cabin Smoke or 1. Inflight - Start Descent
2. AIR COND BLO Switch -OFF
Fumes
3. HEATER Switch - 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/fumes still persist -
Land ASA Possible
8. If Source is Identified and smoke and/or fumes are
cleared - Land ASA Practical
Complete Loss of Tail 1. Uncontrollable Yawing to Right ( Left Side Slip)
Rotor Thrust - 2. Nose down tucking
Indications 3. Possible roll of fuselage
Complete Loss of Tail Hovering - Close Throttle and perform a hovering
Rotor Thrust - Auto landing. A slight rotation can be expected on
Procedures touchdown
In-Flight - Reduce Throttle to idle, immediately enter
autorotation, and maintain a minimum AIRSPEED of 55
KIAS during Descent
Fixed Pitch Failures Do not close throttle unless a severe right Yaw occurs.
Hover Land with power
Fixed Pitch Failures Will Yaw to left when power reduced
In-flight, Left Pedal 1. adjust power and airspeed to maintain a comfortable
Applied Yaw angle.
2. Power-on approach with sufficient low airspeed to
attain a rate of descent with a comfortable side slip
3. As collective is increased just before touchdown left
yaw will be reduced
Fixed Pitch Failures Will Yaw to right when power is increased
In-flight, Right Pedal 1. Low power run-on type landing will be necessary by
Applied gradually reducing throttle to maintain heading while
2. increasing collective to cushion landing
3. If right yaw becomes excessive, close throttle
completely
Loss of Hydraulic 1. HYDRAULIC SYSTEM caution light illuminated.
Pressure - Indications 2. Grinding or howling noise from pump
3. increase in force required to move flight controls
4. Feedback forces may be evident during flight
control movement
Loss of Hydraulic 1. Reduce airspeed to 70 to 100 KIAS
Pressure - Procedure 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 ASA Practical
6. Run-on landing at ETL speed (~15 knots) is
recommended
Flight Control 1. Uncommanded flight control movements
Actuator hardover - 2. High flight control forces to oppose movement in
indications one axis
3. feedback forces only in affected flight control axis
4. flight control forces normal in unaffected axis
Flight Control 1. Attitude - Maintain
Actuator hardover - 2. HYD SYS switch - Off
Procedure 3. AIRSPEED - set to 70 to 100 KIAS
4. Land ASA Possible using Loss of HYD Pressure
procedure
Cyclic Cam Jam Indications -
1. High fore and aft cyclic control forces
2. Normal pedal, collective and lateral cyclic control
forces
Procedure -
1. Helicopter Pitch Attitude - Maintain normal pitch
attitudes with forward or aft cyclic force
2. Land ASA Practical
Generator Failure - 1. GEN FAIL caution light Illuminated
Indications 2. AMPS indicate 0
3. Voltmeter - Approx 24 Volts
Generator Failure - 1. GENERATOR FIELD and GENERATOR RESET circuit
Procedure breakers - check in
2. GEN switch - RESET then GEN
3. If power is not restored, place GEN switch to OFF;
Land ASA practical
Battery Hot Light Battery Overheating
1. Turn Battery Switch off and land ASA Practical
If BATTERY RLY light illuminates, turn GEN switch OFF if
conditions permit. Land ASA Possible
ENGINE OUT Light NG Less than 55 +- 1% and/or FADEC senses ENGINE
illuminated OUT
Verify Condition. Accomplish engine failure procedure
ENGINE OVSPD NG Greater than 110% or NP versus TORQUE is above
max continuous limit (102.1% NP at 100%TQ to 108.6%NP
at 0%TQ)
Adjust Throttle and collective as necessary. Determine
if engine is controllable:if not shut down
FADEC FAIL (During FADEC has detected a serious malfunction
Start)
Close throttle immediately, Engage Starter to reduce
MGT.
