Deutsch (Deutschland) 
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 |
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| Cyclic Stick: | ||
| TRIM REL sw | Press | |
Starting Engines
| Before starting engines | ||
| Rotor area | Clear | |
| Abort start procedure | ||
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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 810°C AND IS QUICKLY APPROACH-ING 895°C. IF ENGINE HANGS. (Stagnation below GROUND IDLE limits) NO POSITIVE ENGINE OR TRANSMISSION OIL PRESSURE INDICATIONS UPON REACHING GROUND IDLE CONDITION. IF N1 OR N2 INCREASE BEYOND ENGINE LIMITS. |
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| 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 (≈ 720 °C); note that FLI needle moves not until ≈ 350 °C. - Engine oil pressure - N2 and NRO increase |
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| Ground IDLE | Check N2 ≈ 70% | |
| HYDRAULIC Check: | ||
| TRIM REL sw (on cyclic stick) | Press | |
| Cyclic stick | Unlock | |
| HYD test sw | SYS 1 Check caution indication HYD PRESS (System 2) |
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| SYS 2 Check caution indication HYD PRESS (System 1) |
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| 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 (≈ 720 °C); note that FLI needle moves not until ≈ 350 °C. - Engine oil pressure - N2 and NRO increase |
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| When IDLE speed of N2 ≈ 70% 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 (≈ 720 °C); note that FLI needle moves not until ≈ 350 °C. - Engine oil pressure - N2 and NRO increase |
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| When N2 ≈ 70% 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) |
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| SYS 2 Check caution indication HYD PRESS (System 1) |
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| 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 |
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| 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 |