Kapitelauswahl

Normal Procedures

Refer also to our video tutorial for engine start-up

Pre-Start Check

  Overhead Panel:  
  All switches OFF or NORM
  Instrument Panel:   
  All switches OFF or NORM
  BAT MSTR sw ON; CPDS internal test starts
NOTE Do not switch off CPDS during or after flight
  CAD Check no INP FAIL message
NOTE If INP FAIL appears in conjunction with the appropriate caution(s), this caution(s) will not be provided during flight. Abort pre-start check.
  Overhead Panel:   
  FIRE EW 1 test sw EXT/WARN
  CAD FIRE EXT and FIRE E TST must come on (system I)
  Warning Panel FIRE I must come on
  FIRE EW 1 test sw OFF
  FIRE EW 2 test sw EXT/WARN
  CAD FIRE EXT and FIRE E TST must come on (system II)
  Warning Panel FIRE II must come on
  FIRE EW 2 test sw OFF
  CDS/WARN UNIT TEST sw WARN UNIT (all warning lights and gong must come on)
  CDS/WARN UNIT TEST sw CPDS: Check display self test
  Fuel XFER pumps (AFT and FWD) ON; Check caution (F PUMP AFT/FWD) off
  Fuel XFER pumps (AFT and FWD) OFF
  Both fuel PRIME pumps ON and check cautions coming on
  A-COLL light sw ON
  Instrument Panel:  
  CAD & VEMD brightness Adjust as required
  VEMD DC voltage: minimum 24 V
  CAD fuel quantity indication Check quantity
  FADEC sw I then II ON
    Check following cautions: 
-TRAINING
-ENG MANUAL
-DEGRADE
-REDUND
  Cyclic Stick:  
  TRIM REL sw Press

Starting Engines

  Before starting engines  
  Rotor area Clear
  Abort start procedure  
 

IMMEDIATELY ABORT START FOR ANY OF THE FOLLOWING:

IF IGNITION DOES NOT TAKE PLACE AFTER REACHING OF N1 = 20% BUT LAT-EST AFTER 15 SECONDS. WAIT FOR 30 SECONDS BEFORE TRYING STARTING AGAIN.

TOT RISES ABNORMALLY RAPIDLY ABOVE 650°C AND IS QUICKLY APPROACH-ING 760°C.

IF ENGINE HANGS. (Stagnation in N1 below 54%)

NO POSITIVE ENGINE OR TRANSMISSION OIL PRESSURE INDICATIONS UPON REACHING GROUND IDLE CONDITION.

IF N1 OR N2 INCREASE BEYOND ENGINE LIMITS.

  ENG MAIN sw(s) OFF
  Starting first engine  
NOTE Either engine may be started first  
  First Limit Indicator Check needle shows TOT
  ENG MAIN sw first engine IDLE, simultaneously start clock
Monitor:
- N1 increase
- TOT rise (≈ 570 °C); note that FLI needle moves not until ≈ 350 °C.
- Engine oil pressure
- N2 and NRO increase
  Ground IDLE Check N2 ≈ 74%
  HYDRAULIC Check:  
  TRIM REL sw (on cyclic stick) Press
  Cyclic stick Unlock
  HYD test sw SYS 1
Check caution indication HYD PRESS (System 2)
    SYS 2
Check caution indication HYD PRESS (System 1)
    NORM
  Starting second engine  
  First Limit Indicator Check needle shows TOT
  ENG MAIN sw second engine IDLE, simultaneously start clock
Monitor:
- N1 increase
- TOT rise (≈ 570 °C); note that FLI needle moves not until ≈ 350 °C.
- Engine oil pressure
- N2 and NRO increase
  When IDLE speed of N2 ≈ 74% is reached:
  Both Fuel XFER pumps ON
  Both Fuel PRIME pumps OFF
  INVERTER sw ON
  AVIONIC MASTER switches ON
  Instruments Set and check
  Both ENG MAIN switches FLIGHT
  After rotor RPM has stbilized:
  Both ENG MAIN switch guards Close
  Engine quick start procedure
  INVERTER sw ON
  TRIM REL sw Press
  Cyclic stick Unlock and hold in neutral pos.
NOTE Only one engine will begin starting cycle. After reaching N1 ≈ 50%, the second engine will begin its starting cycle automatically.
  First Limit Indicator Check needle shows TOT
  Both ENG MAIN sw’s FLIGHT, simultaneously start clock
Monitor:
- N1 increase
- TOT rise (≈ 570 °C); note that FLI needle moves not until ≈ 350 °C.
- Engine oil pressure
- N2 and NRO increase
  When N2 > 74% at both engines:
  Both Fuel XFER pumps ON
  Both Fuel PRIME pumps OFF
  AVIONIC MASTER switches ON
  When both engines in Flight idle:
  Instruments Set and check
  HYDRAULIC Check  
  HYD test sw SYS 1
Check caution indication HYD PRESS (System 2)
    SYS 2
Check caution indication HYD PRESS (System 1)
    NORM

System Checks

  Miscellaneous Checks  
  Optional equipment checks As required
  SAS Check  
  SAS / AP CUT push-button Press
Check CAUTION indication:
-YAW SAS
-P/R SAS
  SAS Y RST switch Reset YAW
  SAS PR RST switch Reset P/R
  AFCS Test (when AFCS intended to be operated in A.TRIM mode)
  TEST button Press to initiate system test
  Warning panel AP/A.TRIM appears
  CAD During test the following cautions appear:
-AUTOPILOT
-TRIM
-ACTUATION
-P/R SAS
-GYRO
-DECOUPLE
-YAW SAS
-P DAMPER
  PFD / YR / P / flashing
  Cyclic stick Check motion during trim test
  If system test was successful (lamp of the test button out):
  CAD All autopilot relevant cautions disappear
  AP button Press to engage the autopilot (OFF lamp of the AP button goes off)

Pre-Takeoff Check

  NRO / N2 Check ≈ 98 %
  FLI needles Check matched at same parameter
  All WARNING, CAD & VEMD indications Check
  All doors Closed
  Collective pitch Unlock

Takeoff 

NOTE If AFCS is engaged, it is required to override the autopilot temporarily during takeoff procedure by using the Force Trim Release button. Alternatively A.TRIM mode can be deactivated while lifting off. Autopilot then operates in SAS mode.
  Cyclic stick Perform small input; check start-ing triangles disappeared
  Hover flight Perform
  NRO / N2 Check ≈ 100 %
  FLI needles Check matched at same parameter
  All WARNING, CAD & VEMD indications Check
  Recommended takeoff procedure:
  Acceleration and climb Start nose down pitch rotation and simultaneously increase power smoothly so that the helicopter gains speed and height.
  When reaching 50 KIAS Maintain airspeed until reaching 50ft AGL, then accelerate to VY (65 kt) and climb through 100ft AGL

Pre-Landing Check

NOTE If AFCS is engaged, it is required to override the autopilot temporarily during takeoff procedure by using the Force Trim Release button. Alternatively A.TRIM mode can be deactivated while lifting off. Autopilot then operates in SAS mode.
  All instruments Check
  All WARNING, CAD & VEMD indications Check

Landing

  Recommended landing procedure
  After reaching 50 ft AGL Descent with ≤ 500 ft/min at 40 KIAS
  Before touchdown Establish flare attitude to reduce ground speed and raise collec-tive lever to cushion landing
  Touchdown Establish with zero groundspeed
  Cyclic stick Neutral
  Collective pitch Lock

Engine Shutdown

  ENG I/II main switches IDLE
  Inverter sw OFF
  Avionic Master switches OFF
  STBY/HOR sw OFF
  Fuel XFER F + A pumps OFF
  All electrical consumers OFF; except anti-collision light and FADEC sw
  Cyclic stick Lock
  ENG I/II main switches OFF
  Engine parameters Monitor
  When rotor has stopped:  
  Anti-collision light OFF
  VEMD Check FLIGHT REPORT page for counter cycles and exceeded mast moment indications
  FADEC switches (2) OFF
  BAT MSTR switch OFF

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