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148 Cards in this Set
- Front
- Back
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Land as Soon as Possible
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Land without delay to the nearest suitable area (ie. open field) in which a safe approach and landing are reasonably assured. The primary consideration is to ensure the survival of the occupants.
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Land as Soon as Practicable
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The landing site and duration of the flight are at the discretion of the pilot. Extended flight beyond the nearest approved landing area is not recommended. The primary consideration is the urgency of the emergency.
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Auto Rotate - Define
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Autorotation is defined a adjusting the flight controls as necessary to establish a autorotational descent and landing
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Auto Rotate
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1. Collective - Adjust as required to maintain rotor rpm (90-107%)
2. Pedals - adjust. Crab or slip as required. 3. Throttle - Adjust as necessary. Close as required 4. Airspeed - Adjust as required |
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Emergency Shutdown - Define
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Emergency shutdown is defined as engine shutdown without delay
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Emergency Shutdown
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1. Throttle - Close
2. Fuel Valve Switch - OFF 3. BATT Switch - OFF as desired. (MAYDAY Call, Emergency on Transponder, & possible effects of total electrical failure. |
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Airspeed for minimum rate of descent
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52 KIAS
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Airspeed for maximum glide distance
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69 KIAS
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Engine Oil Temp Limits
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G: 0-107 C Continuous Operations
R: 107 C Maximum |
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Engine Oil Pressure Limits
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Y: 50 PSI Minimum below 78% N1
G: 90 PSI Minimum from 78% to 94% N1 G: 115 PSI Minimum above 94% N1 (double wide arc) R; 50 PSI Minimum, 130 PSI Maximum |
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Engine Oil Pressure Note
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During cold temperature operations the oil pressure may exceed the maximum of 130 PSI. Stabilize the engine at idle speed of 60-62% until engine oil temperature is above 0 C and the engine oil pressure is withing normal limits.
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Immediate Action Emergency Actions
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The urgency of the emergency require immediate and instinctive action by the pilot. The most important single consideration is helicopter control. All procedures are subordinate to this requirement. If time permits during a critical emergency, transmit MAYDAY call, set transponder to emergency, turn the ELT ON, and lock the shoulder harnesses.
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N1 Gas Producer
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G: 60-105% Continuous Operations
R: 105% Maximum 105-106% Transient (15 Seconds Maximum) |
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N2 Power Turbine
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R: 97% Minimum Operation
G; 97-100% Continuous Operation R: 100% Maximum N2 75-88%, 60 seconds maximum (time not cumulative) N2 Transient overspeed limit is 15 seconds maximum. |
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Caution
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procedure if not followed could result in damage or destruction of equipment
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Warning
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procedure if not followed could result in personal injury or loss of life
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Note
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procedure which is essential to highlight
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Rotor Limits
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G: 90% Minimum Operation
Y: 50-60% Accelerate through this range G: 90-107% Normal Operation R: 107% Maximum Power on transient Rotor Droop Limit is 95% ( 5 Seconds Maximum) |
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Transmission Oil Pressure
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G: 30-50 PSI continuous operations
R: 30 PSI minimum, 70 PSI maximum |
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Emergency Equipment
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1) Fire Extinguisher - located on center pedestal between pilot and co-pilot stations
2) First Aid Kit - located in one of the pouches by the passenger seat 3) Emergency Locator Transmitter (ELT) - located in baggage compartment. controls on left side of instrument panel |
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Emergency Exits/Entrance
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Through either cabin or crew door. If doors won't open the windows should pop out if pressure is applied to outer edges of the window. If windows will not pop out, kick out the plexiglass to exit.
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Engine Failure at Hover
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1)Autorotate
2)Emer Shutdown - Accomplish after landing |
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Engine Failure - Low ALT/ Low A/S or Cruise
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1) Autorotate
2) Emer Shutdown - Accomplish during descent if time permits. |
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Engine Restart - During Flight Caution
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Do not attempt restart above 12,000 feet MSL. TOT rises too fast to control
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Engine Restart - During Flight
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Choice to restart will depend on altitude, time availble, rate of descent, landing areas. 52-60 KIAS recommended during descent. 1 Min aprox needed to restart in ideal conditions.
1) Throttle - Close 2) Fuel Valve Switch - ON 3) Attempt Start 4) Land as soon as possible |
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Causes of Spike Knock
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When the round pin in the drag-pin fitting contacts the side of the square hole of the pylon stop
Causes of spike knock: low rotor RPM, extreme asymmetric loading, poor execution of an autorotational landing and low “G” maneuvers below +.5 Gs. |
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Engine Oil Temp Limits
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G: 0-107 C Continuous Operation
R: 107 C Maximum |
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Transmission Oil Temp Limits
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G: 15-110 C Continuous Operation
R: 110 C Continuous Operation |
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Engine Starting Limitations
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During starting if N1 does not reach in 58% in 45 seconds or 60 seconds below 10 C FAT, close throttle and press starter until TOT is below 200 C.
If engine fails to start on 3rd attempt make entry on DA From 2408-13-1. |
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Engine Starter Limits - No Rise in TOT in first 20 Sec
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External Power
25 Sec - On 30 Sec - Off 25 Sec - On 30 Sec - Off 25 Sec - On 30 Minutes - Off Battery 40 Sec - On 60 Sec - Off 40 Sec - On 60 Sec-Off 40 Sec - On 30 Min - Off |
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Engine Starter Limits - Rise in TOT in first 20 Sec
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External/Battery Power
1 Min - On 1 Min - Off 1 Min - On 1 Min - Off 1 Min - On 30 Min - Off |
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Engine Compressor Stall
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1) Collective - Reduce
2) Engine Anti-ice/Heater Switches-Off 3) Land as soon as possible |
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Engine Compressor Stall Characteristics
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Sharp rumble or a series of loud sharper reports, severe engine vibration and a rapid rise in TOT
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Engine Over-speed indications
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Right yaw, rapid increase in both rotor & engine RPM, and an increase in engine and rotor noise
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Engine Overspeed
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1) Collective - Increase
2) Throttle - adjust 3) Land as soon as possible If RPM cant be controlled by throttle: 4) Autorotate 5) Emer Shutdown - during descent |
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Engine Underspeed
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1) Land as soon as possible
If engine underspeed below 90% results in rotor rpm decay 2) Autorotate 3) Emer Shutdown - during descent |
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Engine Compressor Stall - Characteristics
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Sharp rumble or a series of loud sharp reports, severe engine vibration and rapid rise in TOT
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Engine Compressor Stall -
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1) Collective - Reduce
2) Engine anti-ice and heater switches - OFF 3) Land as soon as possible |
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Engine Overspeed Indication
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Right yaw, rapid increase in both rotor and engine RPM and an increase in engine and rotor noise
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Engine overspeed - EP
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1) Collective - Increase (to load rotor & sustain engine/rotor RPM below max ops limit)
2) Throttle - Adjust ( until normal ops RPM) 3) Land as soon as possible (power-on approach, land controlling rpm by throttle) If RPM cannot be controlled by throttle adjustment: 4) Autorotate 5) Emer Shutdown (during descent if time permits) |
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Engine Underspeed EP
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If rotor RPM in green:
1) Land as soon as possible ( run-on landing) Engine underspeed below 90% results in rotor RPM decay below min limits: 1) Autorotate 2) Emer Shutdown (during descent if time permits |
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Engine Oil Temp Limits
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G: 0-107 deg C cont ops
R: 107 deg c maximum |
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Trans Oil Temp Limits
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G: 15-110 deg C cont ops
R: 110 deg c Maximum |
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Starter Limits - No Rise in TOT within first 20 seconds External Power
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25 Sec - ON
30 Sec - OFF 25 Sec - ON 30 Sec - OFF 25 Sec - On 30 Min - OFF |
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Starter limits - No Rise in TOT within first 20 seconds Battery
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40 Sec - ON
60 Sec - OFF 40 Sec - ON 60Sec - OFF 40 Sec - On 30 Min - OFF |
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Starter Limits - Rise in TOT within first 20 Seconds - External/Batter Power
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1 Min - ON
1 Min - OFF 1 Min - ON 1 Min - OFF 1 Min - ON 30 Min - OFF |
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Engine Surges
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If surges in engine RPM occur:
1) GOV INCR switch - INCR for max RPM 2) Throttle - adjust to 97% N2 3) Land as soon as possible If engine surges are not controlled in above steps: 4) Autorotate - over safe landing area 5) Emer Shutdown - during descent |
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Fuel Pump Failure
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1) Descend below 6,000 feet pressure altitude in possible
2) Land as soon as practicable |
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Fuel Pump Failure Note
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Engine wiill operate without boost pump pressure under 6,000 feet. One boost pump will supply enough fuel for all normal engine operations. Both pumps shall be operating for all normal operations.
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Fuel Boost Pump Failure Warning
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Operation with both fuel boost pumps inoperative is not authorized. Due to fuel sloshing and out of trim conditions & one or both fuel boost pumps inoperative, unusable fuel is ten gallons
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Low Inlet Pressure
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Low Inlet Pressure Caution Light
1) Engine Alternate Air Switch - Open 2) If caution light remains on, Land as soon as possible 3) If caution light goes out, Land as soon as practicable. |
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Engine Icing Note
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With system on TOT will rise for same power setting
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Engine Icing EP
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1) Engine Anti-Icing switch - ON
2) TURB OUT Temp - Maintain within limits |
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Un-Commanded Flight Control Input Malfunction
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1) Land as soon as possible
2) Emer Shutdown - after landing |
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Hot Start
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During Starting/shutdown, if TOT limits are exceeded or it seems like TOT limits may be exceeded:
1) Starter button - press and hold until TOT is less than 200 deg C 2) Throttle - closed 3) Fuel Valve Switch - Off 4) Complete Shutdown |
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Fuel Pressure Limits
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R: 4 PSI Minimum
G: 4-30 PSI Continuous Operation R: 30 PSI Maximum R: 8 PSI Minimum - type A,A-1. JP-5, JP-8 fuel below -18 deg C to -32 deg C |
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Torque Limits
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G: 0-85% Continuous Operation
Y: > 85-100% Take off power Range (5 Min Limit) R: 100% Maximum Transient Torque Limit is 100-110% (5 Sec Max) Intentional Use is Prohibited |
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Airspeed Indicator Limits
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G: 0-130 Knots continuous operation
R: 130 knots maximum B: 100 knots maximum for autorotation VNE for internal gross weigh above 3200 lbs is 78 KIAS, not to exceed placarded VNE |
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Airspeed Indicator Note
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Autorotation above 100 KIAS will result in high rates of descent and low rotor RPM
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Engine Anti-Ice Limitations
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1) Engine Anti-ice shall not be used in ambient temp above 4 deg C
2) Engine anti-ice shall be ON for flight in visible moisture in temp 4 deg C or below |
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Distress Call - Force Landing
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1) MAYDAY, MAYDAY, MAYDAY
2) Tail Number 3) Location 4) Brief description of your distress |
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Distress Call - Precautionary Landing
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1) PAN, PAN, PAN
2) Tail Number 3) Location 4) Brief description of your distress |
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Main Driveshaft Failure EP
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1) Autorotate - Establish a Power On autorotation
2) Emer Shutdown - Accomplish after landing |
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Main Drive Shaft Failure Indications
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1) Sudden increase in Engine RPM
2) Decrease in rotor RPM 3) Left Yaw 4) Low RPM Audio 5) ROTOR RPM Light 6) Transient overspeed of N1 & N2 |
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Main Drive Shaft Warning
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Engine must remain in ops to provide power to tail rotor. Failure to will result in loss of aircraft control during autorotation. Adjust throttle as required to maintain engine RPM within limits
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Mast Bumping EP
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Land as soon as possible
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Mast Bumping Define
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Main yoke contacting the mast
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Causes of Mast Bumping
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1) Slope Landing
2) Rotor Startup/coastdown 3) Flight envelope is exceeded |
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Loss of Tail Rotor Effectiveness
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1) Pedal - Full Left
2) Cyclic - Forward 3) Adjust controls for normal flight 4) If spins cannot be stopped & crash is imminent, autorotation may be the best COA. Maintain full left pedal until spin stops, then adjust to maintain heading. |
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Loss of Tail Rotor Effectiveness - Define
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- Uncommanded and rapid right raw rate
- Yaw is usually correctable if immediate additional left pedal is applied, if slow or incorrect yaw rate may increase to where recovery may not be possible. |
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Fire Note
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Although the agent contained in the fire extinguisher is non toxic, it may cause skin irritation. In case of contact, flush affected area with clean cool water.
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Fire Caution
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If aircraft fire occurs on ground with GPU connected, GPU should be shutdown immediately.
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Fire
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The safety of helicopter occupants in the primary consideration when a fire occurs. Flight crew should make every effort to put the fire out. On the ground shutdown engine and crew evacuated and fire fighting begun if time permits a MAYDAY. In flight the most important action is by the pilot to land.
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ENG/Fuselage/Electrical Fire - Ground
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1) Emer Shutdown
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ENG/Fuselage Fire - Flight
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If power-on landing:
1) Land as soon as possible 2) Emer Shutdown - After Landing If power-off landing: 1) Autorotate 2) Emer Shutdown - During Descent |
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ENG/Fuselage Fire - Flight Consideration
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If fire is observed during flight IMC, VMC,night, altitude, & landing area must be considered in order to determine whether to execute a power-on or power-off landing.
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Electrical Fire - Flight
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1) BATT & MAIN GEN switches - off
2) IFR STBDY GEN switch - off 3) Land as soon as possible 4) Emer Shutdown - after landing |
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Electrical Fire - Flight Considerations
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Consider the equipment that is essential to a particular flight environment that will be encountered,
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Smoke & Fume Elimination
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Positive ventilation of cabin to protect occupants from effects of toxic fumes, smokes.
1) VENTS - Open 2) Cockpit and Cabin Windows - open for max ventilation |
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Longitudinal CG Limits
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VMC- 106-114.2; but variable upon gross weight and aircraft config
IMC - 106-110 <3200lbs; 106.9-110 >3200lbs Doors Off - No change with only aft cabin doors off. WIth 1 or both forward doors off, long CG are same as doors on. |
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Longitudinal Center of Gravity Limits - Note
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Station 0 (datum) is located 55.16 inches forward of forward jack point centerline
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VFR Generator Failure - No Output Indication
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Zero indication on the DC Load meter and an illumination of the Main GEN FAIL caution light.
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VFR Generator Failure - No Output EP
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1) GEN FIELD, & GEN RESET Circuit Breakers - Check In
2) MAIN GEN switch - reset then MAIN GEN. ( Do not hold in reset position) If the generator is not restored or it goes off line again: 1) MAIN GEN switch - off 2) Turn OFF all unnecessary electrical equipment 3) Land as soon as practicable |
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Hydraulic Power Failure Indications
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Increase in the force required for control movement; feedback forces will be noticed as well as rate limiting.
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Hydraulic Power Failure EP
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1) Airspeed - adjust as necessary to attain the most comfortable level of control movements
2) HYD BOOST circuit breaker - out. Check for restoration of hydraulic power If hydraulic power is not restored: 1) HYD BOOST circuit breaker - IN 2) HYDR SYSTEM switch - off 3) Land as soon as practicable at an area that will permit a run-on landing |
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Hydraulic Power Failure Warning
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Do not return the HYDR SYSTEM switch to the on position for remainder of flight. This prevent any possibility of a sure in hydraulic pressure and the resulting loss of control.
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Landing in Trees
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Landing should be made when no other landing area is available. In addition, select a landing area with the least number of trees of minimum height.
Autorotate with throttle closed using following: 1) Airspeed - Minimum at treetop level 2) Descend - Vertically into trees 3) Collective - Apply remaining collective prior to blades entering trees |
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Lateral CG Limits
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Lateral CG Limits vary depending on longitudinal CG location. Refer to Chpt 6 for chart.
3in left - 4in right of helicopter centerline |
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Before Landing Check
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Crew, passengers, mission equipment - check
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Before Takeoff Check
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1) RPM - 100%, Throttle Full
2) Systems - Check 3) Avionic - As Required 4) Crew, passengers, mission equipment - check |
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Before Starting Engine: Overhead Switches and Circuit Breakers
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Start aft and come forward check switches are off, circuit breakers are in.
1) State hydraulic & GEN (field & reset) circuit breakers are identified 2) Anti-collision light switch ON |
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Before Starting Engine: Instrument panel instruments & switches
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1) ICS/Foot switch controls-as desired
2) ICS(white) - 2/3 Up, 1/4/5 Down 3) Nav(blue) - middles 4) RX/ICS Volume - as desired 5) VOX switch - VOX 6) Selector switch-2 7) ISO/Normal - normal 8) Foot switch - ICS |
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Ditching - Power On
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Accomplish an approach to a hover above the water:
1) Doors - Open 2) Crew(except pilot) and passengers - exit 3) Have a safe distance away from personnel 4) Autorotate. Apply all remaining collective as helicopter enters the water. Maintain attitude at helicopter enters and begins to sink until it rolls, then apply cyclic in direction for roll. 4) Pilot - exit when main rotor stops |
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Ditching - Power Off
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If engine fails over water, accomplish engine failure EP:
1) Autorotate - decelerate to min forward speed. Apply remaining collective as helicopter enters water. Maintain attitude as helicopter sinks and begins to roll, apply cyclic in direction of roll. 2) Doors -Open 3) Crew and Passengers - Exit when main rotor stops |
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Flight Control Malfunction Indications
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Varying degrees of feedback, binding, resistance, or sloppiness
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Flight Control Malfunction EP
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1) Land as soon as possible
2) Emer Shutdown - After Landing |
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Lighting Strike
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1) Land as soon as possible
2) Emer Shutdown - after landing |
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Weight Limits
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Max Allowable ramp weight - 3350lbs
Max Allowable gross weight for hover/flight - 3350lbs Min front seat weight - 170lbs |
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Aerobatic Maneuvers
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Aerobatic maneuvers are prohibited. Defined as:
1) abrupt change in aircraft attitude 2) abnormal attitude 3) pitch angle > 30 deg 4) roll ange > 60 deg 5) abnormal acceleration |
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5. 10. 15. Rule
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Less than 5 - Shallow & Normal approaches to large, improved landing areas & normal take-offs
5 But Less than 10 - Normal take-off & approaches 10 but less than 15 - steep approaches, confined area ops, pinnacles & ridgeline ops 15 or more - no restrictions |
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Starting Engines- Main Gen Switch - Reset, then on
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Observe and state main gen fail light out, increase in load on loadmeter, increase voltage on voltmeter
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Preliminary Hydr System Check
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1)Co-pilot identify HYDR system switch
2) Verify HYDR system switch 3) Instruct co-pilot to turn switch off 4) State no unusual feedback 5) Instruct co-pilot to turn switch on |
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Engine Start - Complete Call outs
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1) ENG,TRANS,TOT are stabilized
2) N1 - between 60-62% 3) N2 & Rotor stabilized 4) ENG, TRANS lights out |
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HYD System - Check as Follows
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1) Co-pilot identify HYDR SYSTEM switch
2)Verify Switch 3) Instruct co-pilot to turn of switch 4) Check for ops as published 5) State controls are neutralized and pressure is relaxed 6) Co-pilot identify HYDR SYSTEM switch 7) Verify the switch, instruct to turn switch on 8) Check and state hydraulics are restored |
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Engine Out Warning System
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Intermittent audio signal produced and ENG OUT light is illuminated - GAS PRODUCER 55% +/-3
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Rotor Low RPM Warning System
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ROTOR LOW RPM light illuminated and steady audio signal is produced. Activated when rotor rpm is less than 90%
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Battery Temp
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Land as soon as possible
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Engine Chip
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Metallic Particles in engine oil. Land as soon as possible
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Trans Chip
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Metallic particles in transmission oil. Land as soon as possible
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T/R Chip
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Metallic particles in tail rotor gearbox. Land as soon as possible
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A/F Fuel Filter
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A/F fuel filter impending bypass. Land as soon as practicable. Clean before next flight
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Fuel Pump
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Perform Fuel Pump EP
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Main GEN Fail
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EP
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Heater Overtemp
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Indicated excessive heater (220 deg F) in heater. Switch-Off. If light does not extinguish, land as soon as practicable
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Fuel Low
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Plan landing. Aprox 12 gallons of fuel remain
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Low Inlet Pressure
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EP
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Spare
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Unknown malfunction. Land as soon as possible
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Rotor Low RPM
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Rotor RPM is below normal - aprox 90%. Reduce collective pitch and ensure throttle is full open
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Trans Oil Press
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Main transmission pressure is below minimum. Check Gauge. Land as soon as possible
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Trans Oil Temp
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Main transmission oil temp is above 110 deg C. Reducing power may help alleviate the condition. Check transmission oil pressure. Land as soon as possible.
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Control Movements
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Abrupt control movements, including rapid and repetitive anti-torque pedals reversals are prohibited to avoid excessive stresses in the structure. This restriction in no way limits normal control application
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Control Movements Warning
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For gross weight > 3000lbs and DA greater than sea level, the directional control margin may be significantly reduced while hovering in the winds for the right greater than 20 knt or for right sidewards flight at speed > 20 knts.
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Wind Limitations
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1)Helicopter can be started in max wind velocity of 45 knots and max gust spread of 15 knots
2) Max wind for hovering is 35 knot crosswind, 30 knot tailwind 3) For over at gross weight about 3200lbs: - IGE maneuvers-refer to chpt 8 - OGE maneuvers - calm wind only |
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Wind Limitations Note
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Gust spreads are not normally reported. To obtain spread, compare minimum and maximum velocities.
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Slope Landing
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Slope operations shall be limited to slopes of 8 degrees or less.
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Slope Landing Caution
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Caution is to be exercised for slopes > 5 degrees since rigging, loading, terrain and wind conditions may alter the slop landing capability
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RPM Warning system - Warning
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Do not respond to RPM warning system by entering autorotation and reducing the throttle without first confirming engine malfunction by one or more other indications. Normal indication signify the engine is operating properly and there is a failure in tachometer generator or open circuit rather than an actual malfunction.
Indications of engine malfunction- left yaw, drop in rpm, drop engine rpm, caution lights and audio signals |
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Complete Loss of Tail Rotor Thrust -Description & Indications
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Break in drive system, such as severed driveshaft.
1)Pedal input has no effect on trim 2) Nose turn to right 3) Left roll of fuselage along longitudinal axis |
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Complete Loss of Tail Rotor Thrust EP
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1) If safe landing area is no immediately available, continue powered flight to suitable landing area at or above minimum rate of descent autor airspeed.
2) When landing area is reached, make auto landing - throttle closed 3) Use airspeed above min rate of descent 4) If run landing is possible, complete auto with touchdown airspeed as required for directional control. 5) If run on landing is no possible, start decel at 75ft so forward groundspeed is at minimum at 10-25ft. Execute touchdown with collective pull prior to touchdown in level attitude w/min ground run |
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Complete Loss of Tail Rotor Thrust Warning
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Degree of roll/side-slip may be varied by varying throttle and/or collective. At airspeeds below approx 50 knots, side slip may become uncontrollable, and helicopter will begin to spin on the vertical axis
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Complete Loss of Tail Rotor Thrust Note
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Airflow around vertical fin may permit controlled flight at low power levels & sufficient airspeed when a suitable landing is is not available. Touchdown shall be accomplished with the throttle in the full closed position
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Loss of Tail Rotor Components - Indications
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Varying degrees of right yaw depending on power applied and airspeed at the time of failure.
Forward CG Shift |
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Loss of Tail Rotor Components EP
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1) Enter autorotative descent(throttle closed)
2) Maintain airspeed above min rate of descent airspeed 3) If run on landing is possible, complete auto with touchdown speed as require for direction control 4) If run on landing not possible, start to decel at 75 feet so forward groundspeed is at min when helicopter reachers 10-20 feet. Execute touchdown with rapid collective pull just prior to touchdown in level attitude with min ground run. |
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Fixed Pitch Setting - Low Torque
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Indications - nose turn right when power applied
1) If helicopter control can be maintained in powered flight, best coa to maintain control with power and accomplish run-on landing as soon as practicable. Use airspeed/throttle/collective to reduce sideslip angle at touchdown. 2) If helicopter control can't be maintained, close throttle immediately and accomplish autorotational landing |
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Fixed Pitch Setting- High Torque
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Indications - helicopter turns left when power is reduced
1) Maintain control with power & airspeed-between 40-70knt 2) Continue powered flight to suitable landing area where run-on landing can be accomplished 3) execute run on landing w/ power and a touchdown speed which will minimize sideslip. use throttle and collective, as necessary to control sideslip and heading at touchdown |
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Fixed Pitch Setting- Hover
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Indication - Helicopter heading cannot be controlled w/ pedals
1) Fixed Pedal-Land |
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Flight Restriction in Falling or Blowing Snow
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1) Flight in fall &/or blowing snow is prohibited unless the particle separator kit & deflector kit are installed to reduce possibility of engine flameout
2) If particle separator kit is installed, the following limitations apploy to flight: - Hover is limited to 20min after which the helicopter must be landed and check for snow & ice accumulation - Flight operations are prohibited when visibility is less than 1/2 statue mile |
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Flight Over Salt Water and Near Volcanic Activity
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Salt spray ingestion in turbine engines my result in deterioration in performance as well as loss in compressor stall margin. When aircraft has been operated within 10 miles of salt water & 200 miles of volcanic activity, entries shall be made on DA form 2408-13-1 to alert maintenance
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Flight Over Salt Water and Near Volcanic Activity Caution
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Prolonged hovering over salt water which results in spray ingestion, indicated by spray on the windshield should be avoided
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Flight in Sand & Dust Conditions
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1) Ops in heavy sand or dusty conditions without the improved nozzles will result in lower inlet particle separator efficiency which shortens the engine life.
2) If inlet air barrier filter is installed and AIR INLET PRESSURE caution light illuminates or Engine Air Alternate Switch is turned on, entries shall be made on DA Form 2408-13-1, to alert maintenance. |
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Flight in Rain, Snow, or Icing Conditions
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If flown in rain, snow or icing conditions, appropriate entries shall be made on DA Form 2408-13-1 to alert maintenance
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Mast Bumping - Define & Causes
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Main yoke contacting the mast.
1) Slope Landing 2) Starting/Coastdown 3) exceeded flight envelope |
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Mast Bumping
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Slope Landing - reposition cyclic to stop bumping, reestablish hover and long on less sloping ground
Startup/coastdown - move cyclic to minimize/eliminate bumping. Exceeded flight envelope - move cyclic aft to return rotor to a positive thrust condition, roll level, continuing flight if mast bumping has not occured |
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N2 Droop
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The decrease in N2 RPM that exists between the time a demand for power is made and the time the power is delivered.
It may occur during normal flight maneuver requiring rapid increase in power. If N2 droop occur, but lower rotor RPM warning light and audio is not activated & n2 recovers to 100% within 5 seconds and further droop is not experienced, this is considered normal flight. |
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LTE - Define
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The occurrence of a uncommanded and rapid right yaw which does not subside on its own accord and which if not quickly reacted to, can result in loss of aircraft control.
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LTE - EP
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1) Pedal - Full Left
2) Cyclie - Forward 3) As recovery is affected, adjust flight controls for normal flight 4) If spin cannot be stopped and crash is imminent, a autorotation might be the best COA. Maintain full left pedal until spin stops, then adjust to maintain heading |
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Pylon Whirl
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A condition which occurs after blade flapping and mast bumping. The resultant motion of the pylon is elliptical, and spike knock is apt to occur. If the frequency of motion coincides with a particular natural frequency of the helicopter and the amplitude and direction of the force is large enough, damaging vibrations can occur in the aft section of the fuselage and tail boom. Could occur during touchdown autorotations, if operational limits are exceeded.
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Restrictions for practice autorotations
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1) Reported surface winds must not exceed 20 knots.
2) Surface crosswind component must not exceed 10 knot. 3) Wind gust spreads must not exceed 10 knots. 4) Touchdown auto's downwind are prohibited. 5) Airspeed shall not be less than minimum rate of descent 6) Ground speed at touchdown should be approx 5 knots. 7) Auto Landings at gross weight about 3200lb is prohibited. |
