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MSFS 2024 · Rotary
Eurocopter EC135 T1 Startup Checklist
Eurocopter EC135 T1 Startup Notes
The EC135 T1 is a twin, so cold-and-dark means two complete start cycles. Battery and avionics come first, then the fuel prime pumps, and you monitor the CPDS screens rather than steam gauges. Move the number 1 engine main switch to IDLE and the automated sequence handles ignition and fuel while you watch N1 and TOT on the VEMD. Once it stabilizes at idle, repeat for engine 2, then bring both to FLIGHT and let NR settle at 100 percent.
Most sim pilots rush the second engine. Let engine 1 stabilize at idle and confirm clean indications before touching engine 2; work one side at a time. Other classics: leaving the rotor brake set, skipping the prime pumps so the start hangs or flames out during light-off, and shoving both switches to FLIGHT at once. Check the caution panel is clean after each start, and only then advance the switches to FLIGHT and watch NR come up together.
Common mistakes
- Skipping the fuel prime pumps before engine start
- Advancing both engines to FLIGHT before idle stabilizes
- Starting with the rotor brake still engaged
Related Aircraft
Pilot Tools for This Flight
FLIGHT2.17.1Checklist
Eurocopter EC135 T1MSFS 2024 · Startup Checklist · 131 steps · 13 phases
PHS 1 - Pre-Flight Planning11 steps
| 01 | Flight PlanningCOMPLETEDNOTE: EC135 P2+ FM 4.2.1. | |
| 02 | Types of OperationCONFIRMEDNOTE: EASA TCDS EASA.R.009 para III.11: VFR day and night, non-icing conditions. For IFR and Category A operation see the additional equipment requirements and limitations in the relevant EASA-approved RFMS. | |
| 03 | Weather BriefingREVIEWEDWARNING: TCDS para III.11: operation in icing conditions is not approved. | |
| 04 | Mass and BalanceWITHIN LIMITSCAUTION: TCDS para III.12: maximum mass is 2,720 kg. Operation between 2,720 kg and 2,835 kg is only permitted in accordance with RFMS 9.1-3 and when SB EC135-11-003 is incorporated.NOTE: EC135 P2+ FM 4.2.2. | |
| 05 | Centre of GravityCHECKEDNOTE: TCDS para III.13: maximum forward limit 4,180 mm aft of datum at 1,840 kg and 4,219 mm at 2,720 kg. Maximum rearward limit 4,570 mm at 1,500 kg and 4,387 mm at 2,720 kg. Lateral CG maximum deviation is 100 mm right or left. | |
| 06 | Cargo LoadingWITHIN LIMITSNOTE: TCDS para III.19: cargo floor maximum load is 1,130 kg and maximum unit load is 600 kg per square metre. | |
| 07 | Seating and CrewCONFIRMEDNOTE: TCDS para III.16 and III.17: minimum flight crew is 1 pilot in the right seat. Maximum passenger seating is 1 cockpit and six cabin, or seven cabin if the kit described in RFMS 9.2-31 is installed and operated. | |
| 08 | Fuel PlanningCALCULATEDNOTE: TCDS para III.7.1: standard fuel tank capacity is 680.0 litres with 670.5 litres usable up to s/n 0249, and 710.0 litres with 700.5 litres usable from s/n 0250 or with SB EC135-28-007. Self-sealing tanks hold slightly less. | |
| 09 | Altitude PlanningCHECKEDNOTE: TCDS para III.10.1: maximum operating altitude is 20,000 ft (6,096 m) pressure altitude. Refer to the approved RFM for variation according to MTOW. | |
| 10 | Height-Velocity DiagramREVIEWEDNOTE: EC135 P2+ FM 4.6 directs the pilot to observe the Height-Velocity diagram described in Section 5 during the acceleration and climb. | |
| 11 | Radio FrequenciesSET |
PHS 2 - Exterior Check14 steps
| 01 | Helicopter Forms and DocumentsCHECK - Complete | |
| 02 | Weight and CGCHECK | |
| 03 | Covers and Tie-DownsREMOVED | |
| 04 | Ice and Snow (If Any)REMOVED | |
| 05 | Ground Handling WheelsREMOVED | |
| 06 | Fuel TanksDRAIN | |
| 07 | Equipment and CargoSECURED | |
| 08 | Helicopter HeadingINTO WINDNOTE: EC135 P2+ FM 4.3.2: the area around the helicopter should be clear of all foreign objects. | |
| 09 | Walk-Around - Fuselage RHCHECKNOTE: The exterior check is laid out as a walk-around starting forward right at the pilot's door and proceeding clockwise. | |
| 10 | Walk-Around - Rear StructureCHECKNOTE: Tail boom, Fenestron and rear structure. | |
| 11 | Walk-Around - Fuselage LHCHECK | |
| 12 | Walk-Around - Cabin TopCHECKNOTE: Main rotor head, blades and transmission area. TCDS para III.2: the main rotor is bearingless with 4 blades and 10.20 m diameter; the tail rotor is a Fenestron with 10 blades and 1.00 m diameter. | |
| 13 | Walk-Around - Nose AreaCHECKNOTE: The walk-around is completed at the helicopter nose area. | |
| 14 | External Power UnitAS REQUIREDNOTE: To avoid excessive drain on the helicopter battery, particularly in cold weather, all ground operations should be conducted using an external power unit. Prior to EPU connection make sure the battery is connected. When the battery is used, the operation of electrical equipment should be kept to a minimum. |
PHS 3 - Interior Check14 steps
| 01 | Seats and PedalsADJUSTED AND LOCKED | |
| 02 | Safety BeltFASTENED | |
| 03 | Pilot / Copilot DoorCHECK LATCHES ENGAGEDNOTE: Check all latches properly engaged by pushing the doors outwards. If the optional pre-catch device is installed, the door must be in the fully closed position prior to the next opening. | |
| 04 | Overhead Panel - Circuit BreakersALL IN | |
| 05 | Overhead Panel - SwitchesOFF OR NORM | |
| 06 | Rotor Brake Lever (If Installed)OFF (UPWARD) POSITION | |
| 07 | Instrument Panel - InstrumentsCHECK | |
| 08 | ClockCHECK AND SET | |
| 09 | Instrument Panel - SwitchesOFF OR NORM | |
| 10 | Static Pressure SwitchSTATIC TUBE STATIC PRESSURE | |
| 11 | COM/NAV EquipmentCHECK CONDITION | |
| 12 | Collective Pitch SwitchesOFF, NORM, GUARDED IF POSSIBLE | |
| 13 | Twist GripsNEUTRAL | |
| 14 | Collective LeverCHECK LOCKED |
PHS 4 - Pre-Start Check19 steps
| 01 | BAT MSTR SwitchON - CPDS internal test startsCAUTION: EC135 P2+ FM 4.4.1.1: after the BAT MSTR switch is switched on the low rotor RPM audio tone appears. Do not press the RESET pushbutton on the cyclic stick until the end of the CPDS test, otherwise the INPUT FAIL caution logic may be corrupted. | |
| 02 | NR/N2 InstrumentCHECK FULL DEFLECTION | |
| 03 | GND PWR Switches (If Installed)OFF | |
| 04 | CADCHECK NO INP FAIL CAUTIONWARNING: If INP FAIL appears in conjunction with the appropriate cautions, those cautions will not be provided during flight. Abort the pre-start check; maintenance action is required. | |
| 05 | Low NR RPM Audio ToneRESET | |
| 06 | FIRE EW 1 Test SwitchEXT THEN EXT/WARN THEN OFFNOTE: At EXT the CAD FIRE EXT must come on for system I. At EXT/WARN the CAD FIRE EXT and FIRE E TST must come on, the warning panel FIRE I must come on, and the aural warning signal must come on in the headset. | |
| 07 | FIRE EW 2 Test SwitchEXT THEN EXT/WARN THEN OFFNOTE: Same checks for system II, with the warning panel showing FIRE II. | |
| 08 | CDS/WARN UNIT TEST SwitchWARN UNITNOTE: All warning lights and the double gong must come on. The low NR RPM audio tone comes on and must be reset. | |
| 09 | CDS/WARN UNIT TEST SwitchCDSNOTE: Check the CPDS display self test. | |
| 10 | Fuel PRIME Pumps (1 and 2)ONNOTE: Check the PRIME PUMP 1 / 2 cautions come on. The FUEL PRESS 1 / 2 caution may remain on when engine 1 or 2 is not running. | |
| 11 | A-COLL Light SwitchON | |
| 12 | Instrument Panel CoolingCHECK OPERATIVE | |
| 13 | CAD and VEMD BrightnessADJUST AS REQUIRED | |
| 14 | VEMD - DC VoltageMINIMUM 24 V DC | |
| 15 | CAD Fuel Quantity IndicationCHECK QUANTITY | |
| 16 | NAV/COMAS REQUIRED | |
| 17 | TRIM REL Switch (On Cyclic Stick)PRESS | |
| 18 | Cyclic StickCENTERED | |
| 19 | FADEC Switch I Then IIONWARNING: If one of these cautions remains on, abort the pre-start check. Maintenance action is required.NOTE: Check the TRAINING, TRAIN IDLE and FADEC MINR cautions come up on the CAD for a few seconds for systems 1 and 2. |
PHS 5 - Starting First Engine12 steps
| 01 | Fire GuardPOSTED (IF AVAILABLE) | |
| 02 | Rotor AreaCLEAR | |
| 03 | Abort CriteriaBRIEFEDWARNING: EC135 P2+ FM 4.4.1.2: immediately abort the start if ignition does not take place after reaching N1 = 20 percent but at the latest after 15 seconds, if abnormal noises are heard, if the engine hangs below ground idle limits, if the start is not completed within 45 seconds, if there is no positive engine or transmission oil pressure on reaching ground idle, if N2 RPM and rotor RPM needles are not matched after stabilized ground idle, if N1 or N2 increase beyond engine limits, or if abnormal vibrations occur during rotor RPM increase.CAUTION: The P2+ manual's TOT abort thresholds (rising abnormally rapidly above 650 degC and quickly approaching 760 degC) are Pratt and Whitney PW206B2 values and do NOT apply to the Arrius 2B1. Use the T1 certified TOT limits from the EASA TCDS: 895 degC AEO take-off and 855 degC maximum continuous. | |
| 04 | First Limit IndicatorCHECK NEEDLE SHOWS TOT | |
| 05 | ENG MAIN Switch First EngineIDLE - Start clock simultaneouslyNOTE: Either engine may be started first. In case of operation under low OAT, observe oil limits, fuel limits and the warm up procedure. | |
| 06 | N1MONITOR INCREASE | |
| 07 | TOTMONITOR RISECAUTION: Certified T1 TOT limits from the EASA TCDS are 895 degC for AEO take-off (5 min) and 855 degC maximum continuous. Consult the approved EC135 T1 RFM for the Arrius 2B1 starting TOT limit, which is not published in the TCDS.NOTE: The FLI needle does not move until about 350 degC. | |
| 08 | Engine Oil PressureMONITOR INCREASE | |
| 09 | N2 and Rotor RPMMONITOR INCREASENOTE: A GEN PARAM OVERLIMIT message on the FLI is normal during start. | |
| 10 | Ground IdleCHECK N2 STABILIZEDCAUTION: The P2+ manual specifies ground idle at N2 of at least 74 percent. That figure is a PW206B2 value; confirm the Arrius 2B1 ground idle N2 against the approved EC135 T1 RFM. | |
| 11 | HYD Test SwitchSYS 1 AND HOLDWARNING: HYD TEST must not be operated during flight.NOTE: Check the HYD PRESS caution for system 2, then make small movements with the cyclic stick (TRIM REL pressed) checking mast moment indication if installed, with collective pitch, and with pedals checking higher forces. | |
| 12 | HYD Test SwitchSYS 2 AND HOLDNOTE: Check the HYD PRESS caution for system 1, then check correct operation with small cyclic stick, collective pitch and pedal movements. |
PHS 6 - Starting Second Engine13 steps
| 01 | First Limit IndicatorCHECK NEEDLE SHOWS TOT | |
| 02 | ENG MAIN Switch Second EngineIDLE - Start clock simultaneously | |
| 03 | N1, TOT, Oil Pressure, N2 and Rotor RPMMONITORNOTE: Same monitoring as for the first engine. A GEN PARAM OVERLIMIT message on the FLI is normal during start. | |
| 04 | Avionic Master SwitchesONNOTE: Once idle speed is reached. | |
| 05 | Inverter Switch (If Installed)ON | |
| 06 | Pitot Heater 1 and 2ON | |
| 07 | Both Fuel XFER PumpsON | |
| 08 | Both Fuel PRIME PumpsOFF | |
| 09 | Position LightsONNOTE: Mandatory for night flight. | |
| 10 | AvionicsCHECK ON AND SET | |
| 11 | InstrumentsSET AND CHECK | |
| 12 | Both ENG MAIN SwitchesFLIGHT | |
| 13 | Both ENG MAIN Switch GuardsCLOSENOTE: After rotor RPM has stabilized. |
PHS 7 - System Checks8 steps
| 01 | Optional Equipment ChecksAS REQUIRED | |
| 02 | Power CheckPERFORM AS REQUIREDNOTE: TCDS engine limits for the Arrius 2B1: AEO take-off (5 min) 2 x 75 percent torque, Ng 57,706 rpm (101.1 percent), power turbine 104 percent, TOT 895 degC. AEO maximum continuous 2 x 69 percent torque, Ng 53,406 rpm (98.7 percent), power turbine 104 percent, TOT 855 degC. | |
| 03 | SAS DCPL Push-ButtonPRESS - Check YAW SAS caution | |
| 04 | P&R // Y RST SwitchREENGAGE YAW SAS | |
| 05 | Cyclic Trim SystemCHECK FUNCTION IN ALL FOUR MAIN DIRECTIONSNOTE: Monitor the mast moment indication, if installed, while performing small cyclic inputs. | |
| 06 | TRIM-REL SwitchPRESS WHILE MAKING SMALL CYCLIC INPUTSNOTE: In all four directions. Check that no spring forces are present. | |
| 07 | Standby Horizon (If Installed)CHECKNOTE: Required for IFR. Pull and rotate the cage button, set STBY/HOR to TEST for 5 seconds and check HOR BAT remains on in the CAD MISC group, then set STBY/HOR ON and check HOR BAT goes off. | |
| 08 | Bleed Air Heating CheckAS REQUIREDWARNING: Moisture accumulated in the heater system ducting will cause the windshields to fog on initial activation of the heater. Before takeoff, make certain any moisture in the heater system is eliminated by operating the heater in defogging mode until indications of moisture on the windows are no longer present.NOTE: Before the first flight if use of the heating system is intended. Pull the HEATING/DEFOG knob, set BLD HTG to NORM and the rheostat to MAX, check the BLEED AIR indication comes on, then set the rheostat OFF and check the indication disappears. |
PHS 8 - Pre-Takeoff Check6 steps
| 01 | Rotor RPM / N2CHECK AT OR ABOVE 97 PERCENTNOTE: TCDS para III.9: certified power-on rotor speed limits for the T1 are 104 percent maximum and 95 percent minimum. | |
| 02 | All WARNING, CAD and VEMD IndicationsCHECK | |
| 03 | All DoorsCLOSED | |
| 04 | Cyclic StickCHECK CENTERING DEVICE SECURED | |
| 05 | Collective PitchUNLOCKNOTE: When pushing the collective down to release the collective lock, the FADEC MINR caution may appear. It disappears when pressure is released from the collective. | |
| 06 | Intercom VolumeCHECKCAUTION: EC135 P2+ FM 4.5: check that the adjustment of the intercom volume regulator guarantees audible signals. |
PHS 9 - Takeoff8 steps
| 01 | CollectiveCHECK STARTING TRIANGLES DISAPPEAREDNOTE: If not, perform a small input of about 30 percent torque. | |
| 02 | Hover FlightPERFORM | |
| 03 | NR/N2 InstrumentCHECK AT OR ABOVE 100 PERCENTCAUTION: TCDS para III.9: maximum power-on rotor speed is 104 percent. | |
| 04 | FLI NeedlesCHECK MATCHED AT SAME PARAMETER | |
| 05 | All WARNING, CAD and VEMD IndicationsCHECK | |
| 06 | Acceleration and ClimbSTART NOSE DOWN PITCH ROTATIONWARNING: EC135 P2+ FM 4.6: an oscillation which could be unintentionally induced or assisted by the pilot (PIO/PAO) may be experienced in flight in turbulent weather conditions. In case of PIO/PAO, release the collective lever momentarily and increase collective lever brake friction.NOTE: Simultaneously increase power smoothly so that the helicopter gains speed and height. Observe the Height-Velocity diagram. | |
| 07 | At 50 KIASMAINTAIN UNTIL 50 FT AGLNOTE: Then accelerate to Vy (65 kt) and climb through 100 ft AGL. | |
| 08 | TorqueMONITORCAUTION: TCDS: AEO take-off torque limit for the T1 is 2 x 75 percent for 5 minutes; AEO maximum continuous is 2 x 69 percent. |
PHS 10 - Cruise5 steps
| 01 | AirspeedWITHIN VNEWARNING: TCDS para III.8: VNE is 155 KIAS at MSL. Refer to the approved RFM for the reduction in VNE with altitude and for other speed limitations. | |
| 02 | AltitudeWITHIN LIMITSNOTE: TCDS para III.10.1: maximum operating altitude is 20,000 ft (6,096 m) pressure altitude, with variation according to MTOW per the approved RFM. | |
| 03 | Rotor RPMMONITORNOTE: TCDS para III.9: power on maximum 104 percent, minimum 95 percent. Power off maximum 106 percent, minimum 80 percent up to 1,900 kg and 85 percent above 1,900 kg. | |
| 04 | Engine ParametersMONITORNOTE: TCDS: AEO maximum continuous is 2 x 69 percent torque, Ng 53,406 rpm (98.7 percent), power turbine 104 percent, TOT 855 degC. | |
| 05 | Fuel StateMONITOR |
PHS 11 - Pre-Landing Check2 steps
| 01 | All InstrumentsCHECK | |
| 02 | All WARNING, CAD and VEMD IndicationsCHECK |
PHS 12 - Landing5 steps
| 01 | Descent300 TO 500 FT/MIN AT 40 KIASWARNING: An oscillation which could be unintentionally induced or assisted by the pilot (PIO/PAO) may be experienced during a running landing or harder vertical landings. In case of PIO/PAO, rapidly increase or decrease the collective lever, whichever the situation allows, until the oscillation has stopped.NOTE: EC135 P2+ FM 4.8: after reaching 50 ft AGL. | |
| 02 | Before TouchdownESTABLISH FLARE ATTITUDENOTE: Reduce ground speed and raise the collective lever to cushion the landing. | |
| 03 | TouchdownESTABLISH WITH ZERO GROUNDSPEED | |
| 04 | Cyclic StickNEUTRAL | |
| 05 | Collective PitchLOCK |
PHS 13 - Engine Shutdown14 steps
| 01 | ENG I / II Main SwitchesIDLE | |
| 02 | ClockSTART | |
| 03 | Inverter SwitchesOFF | |
| 04 | Avionic Master SwitchesOFF | |
| 05 | STBY/HOR Switch (If Installed)OFF | |
| 06 | Fuel XFER Forward and Aft PumpsOFF | |
| 07 | All Electrical ConsumersOFFNOTE: Except the anti-collision light and the FADEC switches. | |
| 08 | Cyclic StickCENTERED | |
| 09 | ENG I / II Main SwitchesOFF | |
| 10 | Engine ParametersMONITOR | |
| 11 | Anti-Collision LightOFFNOTE: When the rotor has stopped. | |
| 12 | VEMDCHECK FLIGHT REPORT PAGENOTE: Check counter cycles and perform the appropriate logbook entry. | |
| 13 | FADEC Switches (2)OFFNOTE: Allow approximately 10 seconds between the rotor stopping and placing the FADEC switches to OFF, to ensure that the LCF data is stored in the DCU. | |
| 14 | BAT MSTR SwitchOFF |