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MSFS 2024 · Rotary
Airbus H125 Startup Checklist
Airbus H125 Startup Notes
The H125's Arriel 2D is FADEC governed, so the start is simpler than the AS350 family's reputation suggests. Battery on, fuel prime pump running, and the collective twist grip checked at its idle detent before anything else. Move the starting selector to the start position and the FADEC handles fuel introduction and light-off while you monitor NG and T4. There is no throttle modulation during a normal start; the governor owns the engine. Once idle is stable, advance the twist grip to the flight detent and watch NR rise.
Sim pilots most often blow this start by skipping the prime pump or leaving the twist grip out of position, either of which gets you a failed or aborted start. The other habit to break is grabbing collective too early: wait until NR is in the green and the engine is at flight RPM. Keep an eye on T4 during light-off even though the FADEC protects against hot starts, and give the hydraulics a moment before you lift.
Common mistakes
- Starting without the fuel prime pump on
- Twist grip out of the idle detent before starting
- Pulling collective before NR reaches flight RPM
Related Aircraft
Pilot Tools for This Flight
FLIGHT2.17.1Checklist
Airbus H125MSFS 2024 · Startup Checklist · 128 steps · 12 phases
PHS 1 - Pre-Flight Planning11 steps
| 01 | Types of OperationCONFIRMEDCAUTION: The helicopter is approved in the NORMAL category of FAR Part 27.NOTE: Section 2.1 para 2: operation is approved out of icing conditions for day VFR, and night VFR when the required equipment is installed and serviceable and such operation is permitted by the flight regulations of the country concerned. | |
| 02 | Weather BriefingREVIEWEDNOTE: Section 2.1 para 7.2: minimum temperature -40 degC, maximum ISA +35 degC limited to +50 degC. For cold weather operation refer to Supplement 4. | |
| 03 | Falling SnowCHECKEDWARNING: Section 2.1 para 7.4: with visibility greater than 1500 m flight in falling snow is authorized. With visibility 800 to 1500 m total flying time in falling snow is limited to 10 minutes, including the time required to leave all snowy conditions. With visibility less than 800 m flight in falling snow is prohibited. | |
| 04 | NOTAMs / AirspaceREVIEWED | |
| 05 | Performance LimitsDETERMINEDNOTE: Section 4.1 para 3: determine aircraft performance limits for the expected flying conditions, referring to the PERFORMANCE section. | |
| 06 | Weight and BalanceWITHIN LIMITSCAUTION: Section 2.1 para 4: maximum permissible weight is 2,250 kg (4,961 lb). Weights beyond 2,250 kg must only be used with jettisonable loads. Lateral CG limits are 0.18 m (7.08 in) left and 0.14 m (5.51 in) right of the aircraft symmetry plane. | |
| 07 | Cross-Hatched CG ZoneCHECKEDWARNING: Section 4.1 para 3: in the cross-hatched zone of the C of G graph in Section 2, comply with the particular VNE limitation of 133 kt. For a standard aircraft this zone corresponds to a single pilot alone, or one pilot with a passenger in the rear. | |
| 08 | Altitude PlanningCHECKEDNOTE: Section 2.1 para 7.1: maximum substantiated pressure altitude is 23,000 ft (7,010 m). | |
| 09 | Height / Velocity DiagramREVIEWEDNOTE: Section 4.1 para 7 directs the pilot to climb while avoiding entering the height/airspeed diagram. | |
| 10 | Fuel PlanningCALCULATEDNOTE: Section 2.1 para 12.4: normal fuels include JP8/F34, Jet A1/F35, Jet A, JP5/F43 and F44. An anti-icing additive is compulsory if OAT is below -20 degC when the fuel does not already contain a fuel system icing inhibitor, at 0.10 to 0.15 percent by volume. | |
| 11 | Radio FrequenciesSET |
PHS 2 - External Checks26 steps
| 01 | Daily InspectionCONFIRMED PERFORMEDNOTE: Section 4.1 para 1: ensure the inspection associated with the day's flights has been performed, either by the pilot in accordance with Flight Manual Section 8, or by the aircraft mechanic in accordance with the Master Servicing Recommendations. | |
| 02 | Ground Around AircraftCLEAN AND UNOBSTRUCTED | |
| 03 | Blade SocksREMOVED (IF APPLICABLE) | |
| 04 | Station 1 - Transparent PanelsCLEANLINESS - Condition | |
| 05 | Station 1 - Total Pressure Head (Pitot)COVER REMOVED - Check clean | |
| 06 | Station 1 - Landing GearSECURITY - Visual checkNOTE: Cross-members, skids and wear-resistant plates. | |
| 07 | Station 1 - Sideslip IndicatorCONDITION | |
| 08 | Station 2 - Engine Air IntakeCLEARNOTE: Free of water, snow and foreign matter. | |
| 09 | Station 2 - MGB CowlingCHECK MGB OIL LEVELNOTE: Use the steps. Close the cowling and check it is closed. | |
| 10 | Station 2 - Main Rotor HeadINSPECTNOTE: Inspect star, sleeves for peeling, spherical thrust bearing and adapters for separation. | |
| 11 | Station 2 - Main Rotor BladesSECURITYNOTE: Check attachment and inspect from the ground for signs of impact. | |
| 12 | Station 2 - Tail Pipe Cover (If Fitted)REMOVED | |
| 13 | Station 2 - Transmission Deck and EngineCONDITION AND CLEANLINESSNOTE: Open the engine cowling to check, then close it. | |
| 14 | Station 2 - Lower Fairing PanelsCLOSED - Check | |
| 15 | Station 2 - Port HoldCHECKNOTE: Door opening action, no loose objects, closing and latching. | |
| 16 | Station 2 - Fuel Tank and SystemFILLER PLUG CLOSED - Check for leaks | |
| 17 | Station 3 - Heat Shield on Tail Drive Shaft FairingCONDITION AND ATTACHMENTS | |
| 18 | Station 3 - Oil LeaksNO OIL UNDER SCUPPERS | |
| 19 | Station 3 - Tail Boom and TGB FairingsSECURITYNOTE: Dzus fasteners locked. | |
| 20 | Station 3 - Tail Rotor Gear BoxCHECK OIL LEVEL | |
| 21 | Station 4 - Tail Rotor BladesCONDITIONNOTE: Condition of skin, no impact damage such as dents, and laminated stops checked for separation. | |
| 22 | Station 4 - Tail Rotor Guard (If Fitted)SECURITY AND CONDITION | |
| 23 | Station 5 - Starboard HoldCHECK IF NECESSARYNOTE: Open the door, check no loose objects, check the battery connection, close the door and check. | |
| 24 | Station 5 - External Power Receptacle DoorCLOSED - Check | |
| 25 | Station 5 - MGB CowlingCHECK ENGINE OIL LEVELNOTE: Use the steps. Check for foreign objects on the transmission deck. Close the cowling and check. | |
| 26 | Station 5 - Hydraulic Unit / SystemCHECK RESERVOIR FLUID LEVEL |
PHS 3 - Internal Checks8 steps
| 01 | CabinCLEAN | |
| 02 | Fire ExtinguisherFITTED | |
| 03 | FusesFITTED | |
| 04 | Objects CarriedSTOWED | |
| 05 | Door JettisonCHECKED | |
| 06 | Collective Pitch Control and Yaw PedalsFREE TRAVEL | |
| 07 | Rotor Brake ControlFREE MOVEMENT | |
| 08 | Fuel Shut-Off ControlFORWARD POSITIONCAUTION: The fuel flow control on the collective grip must not be operated when the aircraft electrical system is switched off.NOTE: Snap wire fitted, or plastic guard or snap wire fitted per the later revision. |
PHS 4 - Checks Before Starting The Engine22 steps
| 01 | Seats and Control PedalsADJUSTED | |
| 02 | Seat BeltsFASTENEDNOTE: Check particularly that the copilot seat belt is fastened when that seat is not occupied. | |
| 03 | Battery and GeneratorSWITCHES ONNOTE: On aircraft battery power the HYDR, GENE, MGBP, PITOT, ENG.P, FUEL.P and HORN lights come on. On external power the same lights come on plus BATT. | |
| 04 | Battery VoltageCHECKED | |
| 05 | HYD TEST Push-ButtonPRESS FOR APPROXIMATELY 2 SECONDSNOTE: Depressurizes the yaw hydraulic accumulator in order to centre the yaw pedals. | |
| 06 | Collective Pitch Lever and Yaw PedalsFREEDOM OF TRAVEL | |
| 07 | Cyclic Pitch Control StickNEUTRAL | |
| 08 | Collective Pitch Control LeverLOCKED IN LOW PITCH | |
| 09 | Cyclic Stick Friction LockADJUSTED | |
| 10 | Collective Lever Friction LockADJUSTED | |
| 11 | Rotor BrakeRELEASED - Forward safety guard removed | |
| 12 | Fuel Shut-Off LeverFORWARDNOTE: Lockwired, or with the safety device in place per the later revision. | |
| 13 | Emergency Rotary Throttle ControlIN FLIGHT NOTCHNOTE: With the flight stop in position. | |
| 14 | AUTO/MAN SelectorAUTO | |
| 15 | Starting SelectorOFF - Switch guard down | |
| 16 | TEST LIGHT Push-ButtonENGAGEDNOTE: On the interseat console. Warning lights on the Caution Advisory Panel and instrument panel light, and the target and software identification number is displayed on both screens. | |
| 17 | TEST FIRE Push-ButtonENGAGEDNOTE: On the interseat console. The ENG FIRE warning light illuminates. | |
| 18 | VEMD - Engine Oil Temperature and PressureDISPLAYED | |
| 19 | VEMD - Fuel GaugeQUANTITY CHECKED | |
| 20 | Hydraulic PressureON | |
| 21 | Heating System, Demister, Air ConditionerOFF | |
| 22 | Gyroscopic InstrumentsON |
PHS 5 - Starting21 steps
| 01 | Warning Lights (Red and Amber)OUT | |
| 02 | Booster PumpONNOTE: On the console. Check that the blue indicator light on the instrument panel is on. | |
| 03 | Starting SelectorONCAUTION: Section 4.1 para 4 Note 1: in strong wind, apply a little forward cyclic. Note 2: if the starting cycle has to be aborted, return the start switch to the closed position and switch off the fuel pump and the generator.NOTE: For outside air temperatures below -20 degC refer to Supplement 4. | |
| 04 | NgCHECK INCREASING | |
| 05 | t4CHECK BELOW LIMITWARNING: Section 2.1 para 12.2 (Arriel 2B): maximum t4 for engine starting is 750 degC. Maximum transient during starting is 865 degC for 10 seconds maximum. | |
| 06 | RotorCHECK TURNING | |
| 07 | Engine Oil PressureCHECK INCREASING | |
| 08 | Caution Advisory Panel LightsCHECK OUTNOTE: P MOT (ENG.P) should be out at 70 percent Ng. P BTP (MGB.P) and HYDR should also go out. | |
| 09 | HornENGAGE - HORN light extinguishesNOTE: Check the aural warning operates at approximately 360 rpm. Check that NR is in the green zone of the indicator, near the lower limit. | |
| 10 | Starter Switch GuardLOWERED | |
| 11 | Rotor Brake Safety DevicePOSITIONED | |
| 12 | External PowerDISCONNECT IF USEDNOTE: Check the Caution Advisory Panel GEN and BAT lights are off. | |
| 13 | PITOT HeatingONNOTE: On the pedestal panel. Check that the PITOT light goes out. | |
| 14 | Booster PumpOFFNOTE: PUMP and FUEL P captions extinguished. | |
| 15 | Warning and Caution LightsALL OFF | |
| 16 | Electrical SystemCHECK VOLTAGE AND CURRENT | |
| 17 | Engine Oil PressureCHECK | |
| 18 | SystemsSWITCH ON AS NECESSARYNOTE: VHF, lights, windshield wiper and so on. Do not use the wiper on a dry windshield or in light rain. | |
| 19 | Hydraulic Accumulator TestCARRY OUTNOTE: Check collective pitch locked. Cut off hydraulic pressure with the test push-button on the console; check the HYDR light illuminates and the gong sounds. Move the cyclic stick 2 or 3 times along both axes separately over about 10 percent of total travel and check for hydraulic assistance by absence of control load. Press the test push-button to restore hydraulic pressure and check the HYDR light goes out. | |
| 20 | Hydraulic Pressure Isolation CheckCARRY OUTNOTE: Isolate hydraulic pressure with the switch on the collective pitch lever: the HYDR light illuminates and control load is felt immediately, except on the yaw pedals where control load should remain low because of the load-compensating servo. Restore hydraulic pressure with the switch: the HYD light goes out after 2 to 3 seconds. | |
| 21 | Tail Rotor Pedal NoteNOTEDNOTE: Section 4.1 para 4: on the ground, to obtain zero thrust at the tail rotor it is necessary to push the left hand pedal over approximately 2 cm (0.8 in). |
PHS 6 - Checks Before Take-Off6 steps
| 01 | DoorsCLOSEDWARNING: Section 2.1 para 6.2: with all four standard doors removed, or two right hand doors removed, or two left hand doors removed, VNE is limited to 70 kt (130 km/h). Any other configuration is prohibited. Sliding door installations have their own VNE table. | |
| 02 | NavigationCHECKED | |
| 03 | Radio Navigation and Radio CommunicationTESTS - Correct operation | |
| 04 | Collective and Cyclic Friction ClampsADJUST AS REQUIREDNOTE: Sufficient friction must be applied to the collective and cyclic so that the controls do not move without specific pilot action. | |
| 05 | Pressures and TemperaturesCORRECT | |
| 06 | Warning and Caution LightsALL OUTCAUTION: Section 4.1 para 5: P2 bleed is prohibited beyond the maximum continuous power rating (Ng/t4). |
PHS 7 - Take-Off5 steps
| 01 | Collective PitchINCREASE GRADUALLYNOTE: Section 4.1 para 6: take off by gradually increasing the collective pitch. | |
| 02 | HoverMAINTAIN AT ABOUT 5 FT (1.5 M)NOTE: Head into wind. | |
| 03 | Engine and Transmission InstrumentsWITHIN NORMAL OPERATING RANGESNOTE: Section 2.1 para 10: First Limitation Instrument maximum continuous is 9.6, take-off zone (5 min) is 9.6 to 10, maximum take-off is 10 which activates the power alarm, and maximum transient is 10.4. | |
| 04 | Transition From HoverINCREASE SPEED TO 40 KT IASCAUTION: Section 2.1 para 11: below 40 kt, maximum continuous torque is 100 percent and maximum transient torque is 104 percent for 10 seconds. At or above 40 kt, maximum continuous torque is 92.7 percent.NOTE: Increase speed without increasing the power demand (the power required for hover in ground effect) and without climbing, until IAS is 40 kt (74 km/h). | |
| 05 | Bleed Valve FlagMONITORNOTE: The bleed valve flag disappears when the valve closes. The bleed valve is normally open when the engine is shut down, during starting and at low power. |
PHS 8 - Climbing4 steps
| 01 | PowerMAINTAIN AND CLIMBWARNING: Section 4.1 para 7: keep the same power and climb while avoiding entering the height/airspeed diagram. | |
| 02 | Above 100 FT (30 M) - PowerSELECT MAX CONTINUOUS | |
| 03 | Climb Speed (Vy)IAS 65 KT (120 KM/H)NOTE: Optimum climbing speed, reducing by 1 kt per 1000 ft. | |
| 04 | Engine LimitsMONITORNOTE: Section 2.1 para 12 (Arriel 2B): maximum takeoff t4 is 915 degC and maximum continuous t4 is 849 degC. Maximum take-off Ng rating (5 min) is 101.1 percent with P2 air bleed off; maximum continuous Ng is 97.1 percent; maximum transient Ng is 102.3 percent for less than 5 seconds. Values are at Zp 0 m and 15 degC. |
PHS 9 - Cruising Flight and Manoeuvres8 steps
| 01 | PowerMAX CONTINUOUS FOR FAST CRUISENOTE: Section 4.1 para 8.1. | |
| 02 | AirspeedWITHIN VNEWARNING: Section 2.1 para 6.1.1: power-on absolute VNE is 155 kt (287 km/h) at zero pressure altitude, reduced by 3 kt per 1000 ft. Subtract a further 10 kt when OAT is below -30 degC. In the cross-hatched zone of the C of G graph, VNE is limited to 133 kt or the value determined above, whichever is lower. | |
| 03 | Power-Off AirspeedWITHIN VNEWARNING: Section 2.1 para 6.1.2: power-off absolute VNE is 125 kt (231 km/h) at zero pressure altitude, reduced by 3 kt per 1000 ft without dropping below 65 kt. Subtract a further 20 kt when OAT is below -20 degC, without dropping below 65 kt. | |
| 04 | Main Rotor SpeedMONITORNOTE: Section 2.1 para 8: power on in stabilized flight is 390 +4/-5 rpm; on the ground at low pitch it is 380 +/- 5 rpm. Power off maximum is 430 rpm and minimum is 320 rpm. The horn sounds continuously below 360 rpm and intermittently above 410 rpm. | |
| 05 | TurnsAS REQUIREDNOTE: Section 4.1 para 8.2: in turns the maximum load factor is indicated by transparency of the servo-controls and is therefore not dangerous. In maximum power configuration it is advisable to decrease collective pitch slightly before initiating a turn, since power requirement increases in this manoeuvre. | |
| 06 | Hover Rotation RateLIMITCAUTION: Section 4.1 para 8.2: in the hover, avoid rotation faster than 6 seconds for one full rotation. | |
| 07 | Flight With Doors OpenCABIN SECUREDNOTE: Section 4.1 para 8.3: check that objects, cushions and documents in the cabin are correctly secured before opening one or both of the sliding doors in flight. | |
| 08 | Heating / Demisting SystemAS REQUIREDCAUTION: Section 4.1 para 12: the heating/demisting system may be used without restriction up to the Maximum Continuous Power rating. Beyond that its use is prohibited. |
PHS 10 - Approach and Landing5 steps
| 01 | Final ApproachINTO WIND AT LOW SINK RATENOTE: Section 4.1 para 9.1: recommended airspeed 65 kt (120 km/h). | |
| 02 | P2 BleedCHECKCAUTION: Section 4.1 para 9.2: P2 bleed is prohibited beyond the maximum continuous power rating (Ng/t4). | |
| 03 | Collective PitchREDUCE VERY GRADUALLY FROM HOVERNOTE: Until initial touch-down is made. | |
| 04 | Collective PitchCANCEL COMPLETELY AFTER TOUCHDOWN | |
| 05 | Slope LandingCYCLIC TO NEUTRALWARNING: Section 4.1 para 9.2: when landing on a slope, return the cyclic control stick to neutral before final cancellation of collective pitch. |
PHS 11 - After Landing - Engine and Rotor Shutdown6 steps
| 01 | Unnecessary Power-Consuming SystemsSWITCH OFF | |
| 02 | Generator and All SwitchesSWITCH OFF | |
| 03 | Start SelectorOFF AFTER 30 SECONDSNOTE: Section 4.1 para 10: wait 30 seconds, then position the start selector to OFF. | |
| 04 | Rotor BrakeAPPLY FULLY AT 140 RPM NRWARNING: Section 2.1 para 9: maximum rotor speed for rotor brake application is 170 rpm. Minimum time between two consecutive brakings is 5 minutes.NOTE: 170 rpm maximum NR in high wind conditions. | |
| 05 | HYD Test Push-ButtonPRESS 1 TO 2 SECONDS WHEN ROTORS STOPPEDNOTE: Discharges the hydraulic accumulator and re-centres the yaw pedals if necessary. | |
| 06 | VEMD Flight ReportRECORDNOTE: On engine shutdown the lower VEMD screen displays the flight report: engine start number, operating time counted from Ng above 60 percent until Ng below 50 percent, number of gas generator cycles performed during the flight and in total, and number of free turbine cycles performed during the flight and in total. Check that the partial cycles figure is not zero and that it is displayed in white. |
PHS 12 - Turnaround Check6 steps
| 01 | MGB, TGB and Engine Fluid LevelsCHECK | |
| 02 | General Drain for the Engine PlatformCHECK NO FLOW | |
| 03 | Main and Tail Rotor Blade SkinsRAPID CHECK | |
| 04 | Loads, Baggage Doors and CowlingsSECURELY TIED DOWN AND LOCKED | |
| 05 | Engine Reduction Gear Magnetic PlugsCHECK EVERY 15 FLIGHT HOURS MAXIMUMNOTE: Forward and aft plugs, without electrical indication. | |
| 06 | Short-Term PicketingAS REQUIREDWARNING: Section 4.1 para 11: in this case all picketing and handling tooling must be removed before the next flight.NOTE: Should the turnaround time be prolonged, short-term picketing is recommended: blanking plugs and covers fitted, and blade socks and poles in winds greater than 40 kt. |