Emergency Procedures Flashcards
Land as Soon as Possible.
Land without delay at nearest suitable areas (open field) at which a safe approach and landing is reasonably assured.
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.
Engine failure- Hover
• INDICATIONS:
- Left yaw.
- ENG OUT light illuminated.
- Engine instruments indicate power loss.
- Engine out audio (if installed, 206L1+ and 206L3+ IGW Upgrade) activated when N1 drops below 55%
- Nr decreasing with Low Rotor RPM light and audio on when NR drops below 90%
Collective Maintain
Pedals - Control yaw.
Collective - Increase as needed to cushion landing.
Engine failure In flight
Indications and actions?
- Left yaw.
- ENG OUT light illuminated.
- Engine instruments indicate power loss.
- Engine out audio (if installed, 206L1+ and 206L3+ IGW Upgrade) activated when N1 drops below 55%.
- NR decreasing with ROTOR LOW RPM light and audio on when NR drops below 90%.
Procedure: Enter autoroation attempt restart if able. Not able to restart
Throttle - Closed
Fuel Valve switch - Off
Accomplish automative descent and landing. Complete helicopter shutdown.
Autorotation speeds
Minimum ROD airspeed is 52 Kias
Max Glide 69 Kias.
Nominal authoritative airspeed is 61 Kias.
Engine Restart In flight
Collective - Adjust to maintain 90 to 107% NR
Airspeed adjust as desired. 52 knots and minimum NR will allow more time.
Throttle Closed
Fuel valve switch On
Starter button Press and hold.
Throttle Idle
TOT - Modulate throttle to maintain 716 to 826C
Throttle advance smoothly to full open position.
If restart is unsuccessful, abort start and secure engine as follows:
Throttle - Closed
Fuel valve switch - off
Finish auto.
Engine underspeed indications and procedures:
• INDICATIONS: 1. Decrease in N1. 2. Subsequent decrease in N2. 3. Possible decrease in NR. 4. Decrease in TORQUE• PROCEDURE: 1. Collective — Adjust as required to maintain 90 to 107% NR. 2. Throttle — Confirm full open. 3. If unable to maintain NR, establish autorotative glide. (Refer to AUTOROTATIVE DESCENT PROCEDURE, paragraph 3-3-A-3.) 4. Prepare for power-off landing.
Engine Overspeed Indications
Procedure:
INDICATIONS: 1. Increase in NR. 2. Increase in N2. 3. Increase in N1. 4. Increase in TORQUE PROCEDURE: 1. Throttle — Retard. 2. N1 or N2/NR — Attempt to stabilize with throttle and collective. 3. TOT — Monitor for normal operation. 4. NR — Maintain 90 to 107% with throttle and collective. IF UNABLE TO MAINTAIN NR, N2, N1, OR TOT, PREPARE FOR A POWER OFF LANDING BY LOWERING COLLECTIVE AND SHUTTING DOWN ENGINE.
Engine Compressor Stall/Surge
Indications:
Procedure:
INDICATIONS:
- Engine pops.
- High or erratic TOT.
- Decreasing or erratic N1 or N2.
- TORQUE oscillations. PROCEDURE:
- Collective — Reduce power, maintain slow cruise flight.
- TOT AND N1 — Check for normal indications.
- ENGINE ANTI-ICING switch — ON.
- PARTICLE SEP PRG switch (if installed) — ON.
- HEATER switch (if installed) — ON.
- Collective - Increase slowly to achieve desired power level.
- Toto and N1 Monitor for normal response.
- Land as soon as practical.
If pilot elects to shut down engine: 9. Enter auto 10. Throttle closed. 11. Fuel valve switch Off accomplish authoritative descent and landing.
Engine Hot Start/ Shutdown
Indications: Excessive TOT. Visible smoke or fire.
Throttle - Closed
Fuel Valve switch - Off.
Starter button -press to motor engine until TOT stabilizes at normal temp.
Completehelicopter shutdown.
Engine oil Pressure Low, High or Fluctuating.
Engine oil pressure below minimum — Monitor engine oil pressure and temperature. Land as soon as possible
Engine oil pressure above maximum or fluctuating abnormally — Monitor engine oil pressure and temperature. Land as soon as practical.
Engine Oil Temperature High
Land as soon as practical.
Drive shaft failure indications:
Indications:
- Left yaw.
- Rapid decrease in NR.
- Rapid increase in N2.
- ROTOR LOW RPM audio horn.
- Illumination of ROTOR LOW RPM light.
- Possible increase in noise level due to overspending engine and driveshaft breakage.
Procedure: enter auto.
To maintain tail rotor effectiveness do not shut down engine.
Engine Fire on Ground
Procedure. Throttle — Closed.
- FUEL VALVE switch — OFF.
- BAT switch — OFF.
- Rotor brake (if installed) — Engage. 5. Exit helicopter.
Engine fire during flight.
PROCEDURE:
1. In-flight — Immediately enter autorotation.
2. Throttle — Closed.
3. FUEL VALVE switch — OFF.
4. If time permits, LEFT/RIGHT FUEL BOOST circuit breakers —Pull out.
5. Accomplish autorotative descent and landing. (Refer to AUTOROTATIVE DESCENT PROCEDURE, paragraph 3-3-A-3.)
6. BAT switch — OFF.
NOTE
Do not restart engine until corrective maintenance has been performed.
Cabin smoke or Fumes
In-flight — Start descent.
HEATER switch (if installed) — OFF. All vents — Open.
Side windows — Open.
and altitude permits:
Source — Attempt to identify and secure.
If source is identified and smoke and/ or fumes still persist — Land as soon as possible.
If source is identified and smoke and/ or fumes are cleared — Land as soon as practical
Complete loss of tail rotor thrust in flight
Reduce throttle to idle, immediately enter autorotation, and maintain a minimum AIRSPEED of 52 KIAS (60 MPH) during descentNOTE
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.
Fixed pitch failures Note
NOTE
If pedals cannot be moved with a moderate amount of force, do not attempt to apply a maximum effort, since a more serious malfunction could result. If helicopter is in a trimmed condition when malfunction occurs, TORQUE and AIRSPEED should be noted and helicopter flown to a suitable landing area. Certain combinations of TORQUE, NR, and AIRSPEED will correct a yaw attitude, and these combinations should be used to land helicopter.
TR Fixed Pitch Failure Hovering
NOTE
If pedals cannot be moved with a moderate amount of force, do not attempt to apply a maximum effort, since a more serious malfunction could result. If helicopter is in a trimmed condition when malfunction occurs, TORQUE and AIRSPEED should be noted and helicopter flown to a suitable landing area. Certain combinations of TORQUE, NR, and AIRSPEED will correct a yaw attitude, and these combinations should be used to land helicopter.
In Flight Left pedal applied TR fixed pitch
In a high power condition, helicopter will yaw to left when power is reduced. Power and AIRSPEED should be adjusted to a value where a comfortable yaw angle can be maintained. If AIRSPEED is increased, vertical fin will become more effective and an increased left yaw attitude will develop. To accomplish landing, establish a power-on approach with sufficiently low AIRSPEED(zero if necessary) to attain a rate of descent with a comfortable sideslip angle. A decrease in N2 decreases tail rotor thrust. As collective is increased just before touchdown, left yaw will be reduced.
In flight Right pedal applied fixed pitch TR
n cruise flight or reduced power situation, helicopter will yaw to right when power is increased. A low power, run-on type landing will be necessary by gradually reducing throttle to maintain heading while adding collective to cushion landing. If right yaw becomes excessive, close throttle completely.
Loss of hydraulic Pressure
PROCEDURE:
- AIRSPEED — Reduce to 60 to 80 KIAS (69 to 92 MPH).
- HYDR SYSTEM circuit breaker — Out. If hydraulic power is not restored, push breaker in.
- HYDRAULIC SYSTEM switch — ON; OFF if hydraulic power is not restored.
- Land as soon as practical.
- A run-on landing at approximately 9 KIAS (10 MPH) is recommended.
FLIGHT CONTROL ACTUATOR MALFUNCTION
Explanation
Note:Uncommanded movement of an actuator can occur in any flight control axis through one or two flight controls. If two controls move, the pilot will find one of these controls will require a higher than normal control force to oppose the movement. This force cannot be removed without turning the HYDRAULIC SYSTEM switch OFF. Once the hydraulic boost is OFF, the forces on the affected flight control should be similar to the “normal” hydraulic off forces.
Flight control actuator malfunction indications and procedures
Uncommanded flight control movements.
2. High flight control forces to oppose movement in one axis.
3. Feedback forces only in affected flight control axis.
4. Flight control forces normal in unaffected axis
Procedure: Attitude — Maintain.
2. HYDRAULIC SYSTEM switch — OFF.
3. AIRSPEED — Set to 60 to 80 KIAS (69 to 92 MPH).
4. Land as soon as possible using LOSS OF HYDRAULIC PRESSURE procedure.
Generator Failure
Indications: GEN FAIL light illuminated.DC loadmeter indicates 0% LOAD.
Procedure:
1. GEN FIELD and GEN RESET circuit breakers — Check in.
2. GEN switch — RESET; then GEN.
3. If power is not restored, place GEN switch to OFF.
4. Land as soon as practical.
Note on Generator Failure
NOTE
With all electrical equipment OFF, battery, when 80% charged, will operate left fuel boost pump approximately 3 hours to transfer fuel from forward fuel cells and maintain helicopter within CG limits.
Excessive Electrical Load
Gen Switches off
Bat switch Off
Left fuel Boost Circuit breaker check in.
Warning about battery depletion.
206L4: PRIOR TO BATTERY DEPLETION, ALTITUDE SHALL BE REDUCED BELOW 6000 FEET HP. UNUSABLE FUEL MAY BE AS HIGH AS 86.3 POUNDS AFTER BATTERY IS DEPLETED DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELLS.206L3+ IGW UPGRADE: PRIOR TO BATTERY DEPLETION, ALTITUDE SHALL BE REDUCED BELOW 6000 FEET Hp. HELICOPTERS NOT EQUIPPED WITH FUEL QTY SWITCH, UNUSABLE FUEL MAY BE AS HIGH AS 156.9 POUNDS (86.3 POUNDS IF EQUIPPED WITH FUEL QTY SWITCH) AFTER BATTERY IS DEPLETED DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELLS.206L1+ IGW UPGRADE: PRIOR TO BATTERY DEPLETION, ALTITUDE SHALL BE REDUCED BELOW 6000 FEET HP. UNUSABLE FUEL MAY BE AS HIGH AS 154.4 POUNDS AFTER THE BATTERY IS DEPLETED DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELLS.
Fuel Transfer Failure
FUEL TRANSFER FAILURE
A fuel transfer failure will result in trapped fuel in forward cells and reduce usable fuel by amount remaining in forward cells.
• INDICATIONS:
At total FUEL QTY of approximately 195.8 pounds and below, FUEL QTY in forward cells remains constant.
• PROCEDURE:
1. Determine FUEL QTY in forward cells.
2. Subtract quantity of fuel trapped in forward cells from total to determine usable fuel remaining.
3. Plan landing accordingly.
Red warning light Battery HOT (battery overheating Temp 140F or higher.
Turn Bat switch off and land as soon as practical. If battery Rly Caution light illuminates land as son as possible.
Red warning light.
Litter Door Open
Close door securely before flight. If light illuminates during flight land as soon as practical.
amber lights
Rotor Low RPM
Reduce collective and ensure throttle is full open. Light and audio should cease when ROTOR increases above approximately 90% NR.
Amber trans oil press light (transmission pressure is below minimum)
Reduce power; verify fault with gauge. Land as soon as possible.
Trans oil temp amber light. XMSN Oil temperature is at or above red line.
Reduce power: verify fault with gauge. land as soon as possible.
Yellow Battery RLY light.
Battery relay has malfunctioned to closed position with BAT switch OFF. Battery will not drop offline.
If Battery Hot Light illuminated, land as soon as possible.
ENG CHIP yellow light.
Land as soon as possible.
Trans Chip Yellow Light
Land as soon as possible.
Fuel Filter yellow Light (A/F) fuel filter in impending bypass
Land as soon as practical.
T/R Chip yellow light
Land as soon as possible.
R/ Fuel Pump yellow light. (Right pump of dual boost pump assembly failed.)
Descend below 6000 feet HP if flight permits. Land as soon as practical.
206L4: IF BOTH FUEL BOOST PUMPS FAIL, ALTITUDE MUST BE REDUCED BELOW 6000 FEET HP. UNUSABLE FUEL MAY BE AS HIGH AS 86.3 POUNDS DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELLS. LAND AS SOON AS POSSIBLE.
L/Fuel PUMP yellow light
Left pump dual boost pump assembly failed
Descend below 6000 feet HP if flight permits. Land as soon as practical.
GEN Fail amber caution Light. Generator not connected to DC Buss.
Verify fault with loadmeter. GEN switch — RESET, then GEN (on). If GEN FAIL light remains illuminated, GEN switch — OFF. Land as soon as practical.
Baggage Door Yellow Light ( door not latched)
Land as soon as practical.
Fuel Low yellow light (Approximately 50 to 75 pounds of fuel remain.
Verify FUEL QTY. Land as soon as practical.AVOID UNCOORDINATED FLIGHT AS FUEL STARVATION MAY OCCUR.
