limitations and boldface during instruments Flashcards
Land as soon as possible
Land without delay to the nearest suitable area (i.e. open field) in which a safe approach and landing is reasonably assured. (The primary consideration is to ensure the survival of the occupants.
Land as soon as practicable
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.)
“Autorotate”
- Collective - Adjust as required to maintain rotor RPM (90 - 107%)
- “Pedals - Adjust” Crab or slip as required
- “Throttle - Adjust as necessary” Close as required
- “Airspeed - Adjust” as required
“Emergency Shutdown”
- “Throttle - Closed”
- “Fuel Valve Switch - Off”
- “Batt Switch - OFF as desired” Before turning the battery switch off during an in-flight emergency, the pilot should consider a “MAYDAY” call, selecting emergency on the transponder and the possible effects of a total electrical failure.
“Engine Failure at a hover”
- “Autorotate”
- “Emer Shutdown” - Accomplish after landing.
“Engine Failure - Low Altitude/Airspeed or Cruise.”
- “Autorotate”
- “Emer Shutdown” - Accomplish during descent if time permits.
“Engine Restart”
- “Throttle - Close”
- “Fuel Valve Switch - On”
- “Attempt start”
- “Land as soon as possible”
Engine Restart - CAUTION
Do not attempt air start above 12,000 feet MSL (TURB OUT TEMP rises too fast to control).
“Engine Compressor Stall”
- “Collective - Reduce”
- “Engine Anti-ice and Heater switches - OFF”
- “Land as soon as possible”
“Engine Overspeed”
- “Collective - Increase” to load the rotor and sustain engine/rotor RPM below the maximum operating limit.
- “Throttle - Adjust” until normal operating RPM is attained.
- “Land as soon as possible” Perform a power-on approach and landing by controlling the RPM manually with the throttle.
If RPM cannot be controlled by throttle adjustment.
- “Autorotate” when over a safe landing area.
- “Emer Shutdown” - Accomplish during descent if time permits.
“Engine Underspeed”
If an engine underspeed occurs, the collective must be adjusted downward to maintain rotor RPM within limits. If powered flight with rotor in the green can be accomplished:
- “Land as soon as possible” in an area that will permit a run-on landing.
An engine underspeed below 90% results in rotor RPM decay below minimum safe limits. Should this occur:
2. Autorotate
- Emer Shutdown - Accomplish during the descent if time permits.
“Engine Surges”
a. GOV INCR switch - INCR for maximum RPM
b. Throttle - Adjust to 97% N2
c. Land as soon as possible
If engine surges are not controlled in steps a. and b. above proceed as follows:
a. Autorotate - When over a safe landing area.
b. Emer Shutdown - Accomplish during descent if time permits.
“LOW INLET PRESSURE caution light ON”
- “ENGINE ALTERNATE AIR SWITCH - OPEN”
- “If caution light remains ON, Land As Soon As Possible.”
- If caution light goes out, Land As Soon As Practicable. Related engine parameters should be monitored frequently until landing.
“Engine Icing”
NOTE
When anti-ice system is ON, TOT will rise for same power setting.
- “ENGINE ANTI-ICING switch - ON” (if conditions warrant).
- “TURB OUT TEMP - Maintain within limits”
“If the engine oil pressure is below 50 PSI or the temperature is above 107*C”
- “Land as soon as possible”
NOTE
If engine oil pressure is falling or low and the oil temperature is rising or high, a severe leak may be present.
“Loss of T/R Effectiveness”
This is a situation involving a loss of effective tail rotor thrust without a break in the drive system which cannot be stopped with full left pedal application. If LTE is experienced, simultaneously:
- “Pedal - Full Left”
- “Cyclic - Forward”
- As recovery is affected, adjust controls for normal flight.
WARNING
Collective reducion will aid in arresting the yaw rate: however, if a rate of descent has been established, collective reduction may increase the rate of descent to an excessive value. The resultant large and rapid increse in collectiveto prevent ground or obstacle contact may further increse the yaw rate, decreasing the rotor RPM and cause an over torque and/or over-temperature condition. Therefore, the decision to reduce collective must be based on the pilot assesment of the altitude available for recovery.
4. If spinning cannot be stopped and crash is imminent, an autorotaion may be the best course a of action. Maintain full left peddle until spin stops, then adjust to maintain heading.
“Main Drive Shaft Failure”
WARNING
The engine must remain in operation to provide power to the tail rotor. Failure to maintain engine power will result in loss of aircraft control. Adjust throttle as required to maintain engine RPM within normal limits.
- Autorotate - Establish a Power On autorotation.
- Emergency Shutdown - Accomplish after landing.
“Clutch failing to disengage”
- “Throttle - Open”
- “Land as soon as possible”
“Hot Start”
During starting and shutdown, if TOT limits are exceeded, or it becomes apparent that TOT limits may be exceeded, proceed as follows.
- “Starter button - Press and hold until TURB OUT TEMP is less than 200°C.”
- “Throttle - Closed.”
- “FUEL VALVE switch - OFF.”
- “Complete shutdown.”
ENGINE OIL TEMPERATURE AND PRESSURE GAUGE
ENGINE OIL TEMPERATURE
- 0º C - 107º C Continuous Operation
- 107º C Maximum
ENGINE OIL PRESSURE
- 50 PSI Minimum below 78% N1
- 90 PSI Minimum from 78% to 94% N1
- 115 PSI Minimum above 94% N1, double wide arc
- 50 PSI Minimum, 130 PSI Maximum
NOTE
During cold temperature operation the oil pressure may exceed the maximum of 130 PSI. Stabilize the engine idle speed of 60 to 64% until the engine oil temperature is above 0º C and the engine oil pressure is within normal limits.
TRANSMISSION OIL PRESSURE AND TEMP
TRANSMISSION OIL PRESSURE
▩ 30 to 50 PSI Continuous Operation
▩ 30 PSI Minimum, 70 PSI Maximum
TRANSMISSION OIL TEMPERATURE
▩ 15º C to 110º C Continuous Operation
▩ 110º C Maximum
LOADMETER AND FUEL PRESSURE GAUGE
LOADMETER
▩ 70% Maximum
FUEL PRESSURE
▩ 4.0 PSI Minimum
▩ 4.0 PSI to 30 PSI Continuous Operation
▩ 30 PSI Maximum
► 8 PSI Minimum using TYPE A, A-1, JP-5, JP-8 Fuels below -18 °C (0 °F) to -32 °C (-25 °F)
AIRSPEED INDICATOR
NOTE
Autorotation above 100 KIAS will result in high rates of descent and low rotor RPM.
▩ 0 to 130 Knots Continuous Operation
▩ 130 Knots Maximum
▩ 100 Knots Maximum for Autorotation
VNE for internal Gross Weight above 3,200 pounds is 78 KIAS, not to exceed placarded VNE.
TURBINE OUTLET TEMPERATURE GAUGE
TURBINE OUTLET TEMPERATURE GAUGE
NOTE
The Red Warning light illuminates when either of the following conditions are exceeded: 810°C to 927°C for 10 seconds or higher than 927°C
▩ 100° to 738° Continuous Operation
▩ 738° to 810° Take-off Power Range (5 minute limit)
▩ 810°C Maximum
810°C to 843°C, 6 second transient limit (Not to be used intentionally)
🔴 927°C Maximum during starting and shutdown, 10 seconds maximum
GAS PRODUCER (N1)
GAS PRODUCER
▩ 60 to 105% Continuous Operation
▩ 105% Maximum
105% to 106% transient (15 seconds maximum)
DUAL TACHOMETER
ROTOR INDICATOR
▩ 90% Minimum Operation
▩ 50 to 60% Accelerate through this range
▩ 90 to 107% Normal Operation
▩ 107% Maximum
Power on Transient Rotor Droop Limit is 95%, 5 seconds maximum
POWER TURBINE INDICATOR
▩ 97% Minimum Operation
▩ 97 to 100% Continuous Operation
▩ 100% Maximum
N2 75% to 88%
60 seconds maximum (time not cumulative)
N2 TRANSIENT OVERSPEED LIMITS
“Student needs to explain graph (figure 5-9, se nederst) verbally”
N2 Transient overspeed limit is 15 seconds maximum. Shaded area represents allowable overspeed.
Explanation:
- N2 transient overspeed is dependant upon engine torque.*
- 0 - 32% Engine torque: 107% Engine RPM.*
- 32% - 100% Engine torque: gradually decreases to decreases to 103% Engine RPM at 100% torque.*
TORQUE METER
▩ 0 to 85% Continuous Operation
▩ > 85 to 100% Take-off Power Range (5 minute limit)
▩ 100% Maximum
Transient Torque Limit is 100 to 110% (5 seconds maximum)
INTENSIONAL USE IS PROHIBITED
