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Bell UH-1H Huey Startup Checklist
FLIGHT2.23.0Checklist
Bell UH-1H HueyMSFS 2024 · Startup Checklist · 149 steps · 16 phases
PHS 1 - Pre-Flight Planning12 steps
| 01 | Mission BriefREVIEWEDNOTE: TM 8-1: mission planning covers the flight plan, operating limits, weight and balance, and performance. | |
| 02 | Weather BriefingREVIEWEDCAUTION: TM 5-10: intentional flight into severe or extreme turbulence is prohibited, and intentional flight into thunderstorms is prohibited.NOTE: Check METAR/TAF at departure and destination. Wind direction is critical for approach planning. | |
| 03 | NOTAMs / AirspaceREVIEWEDNOTE: Check for TFRs, heliport closures, restricted areas and airspace restrictions along the route. | |
| 04 | Icing ConditionsCHECKEDWARNING: TM 5-13b: intentional flight into known icing is prohibited with the rotor blade erosion protection coating and polyurethane tape installed. Only light or trace icing is permitted when they are not installed. | |
| 05 | Fuel PlanningCALCULATEDNOTE: Refer to TM Chapter 7 for recommended airspeeds, power settings and fuel flow. An auxiliary fuel kit adds up to 300 US gallons (TM 2-27). | |
| 06 | Weight and Balance / PayloadWITHIN LIMITSCAUTION: TM 5-9: maximum gross weight is 9,500 pounds. Cargo hook maximum is 4,000 pounds. Cargo floor loading must not exceed 100 pounds per square foot. | |
| 07 | Center of GravityCHECKEDCAUTION: TM 5-8: do not carry external loads with the CG aft of station 142. At an aft CG (station 140 to 144) terminate the approach at a minimum five-foot hover to prevent striking the tail. | |
| 08 | Performance PlanningCHECKEDNOTE: Refer to TM Chapter 7 or 7.1. Density altitude determines hover capability and maximum payload. | |
| 09 | Height Velocity DiagramREVIEWEDWARNING: Flight within the avoid area of the height velocity chart exposes the helicopter to a high probability of damage after a power loss despite the best efforts of the pilot (TM 9-9d).NOTE: TM Figure 9-3 at 324 rotor RPM. The chart is applicable for all gross weights up to and including 9,500 pounds. | |
| 10 | Wind LimitsCHECKEDCAUTION: TM 5-13: maximum crosswind for hover is 30 knots and maximum tailwind for hover is 30 knots. The helicopter may be started in a maximum wind of 30 knots or a maximum gust spread of 15 knots. | |
| 11 | Landing Zone SurveyREVIEWEDCAUTION: TM 5-17: maximum slope landing capability is 10 degrees cross slope or nose up, 7 degrees nose down. Exercise caution above 5 degrees since rigging, loading and wind may result in contacting the control stops.NOTE: Review landing zone size, obstacles, approach and departure paths, and alternates. | |
| 12 | Radio FrequenciesSETNOTE: Note tower, approach, CTAF and enroute frequencies. |
PHS 2 - Exterior Check15 steps
| 01 | BAT SwitchOFFNOTE: TM 8-12: set before walking around. | |
| 02 | Flight ControlsCHECK - Freedom of movementNOTE: Center cyclic, collective down. | |
| 03 | Area 1 - Main Rotor BladeCHECK CONDITION | |
| 04 | Area 2 - Engine CompartmentCHECK - Fluid lines and connectionsNOTE: Check condition and security. Cowling secure. | |
| 05 | Area 3 - TailboomCHECKNOTE: Skin condition, driveshaft cover secure, synchronized elevator, antennas, tail skid. | |
| 06 | Area 4 - Tail Rotor Gearboxes (90 and 42 Degree)CHECK - Condition, oil levels, filler caps secure | |
| 07 | Area 4 - Tail RotorCHECK - Condition and free movement on flapping axisNOTE: The tail rotor blades should be checked as the main rotor blade is rotated. | |
| 08 | Area 5 - Hydraulic Fluid Sight GageCHECK | |
| 09 | Area 5 - Landing GearCHECK - Condition and securityNOTE: Ground handling wheels removed. | |
| 10 | Area 5 - Static PortCHECK UNOBSTRUCTED | |
| 11 | Area 6 - Main Rotor SystemCHECK - Condition and securityNOTE: Check level of fluid in dampers, blade grips and pillow blocks. | |
| 12 | Area 6 - Transmission and Hydraulic Filler CapsSECURE | |
| 13 | Area 6 - Main DriveshaftCHECK - Condition and security | |
| 14 | Area 6 - Engine Air IntakeCHECK UNOBSTRUCTED | |
| 15 | Area 6 - Pitot Static TubeCHECK - Security and unobstructed |
PHS 3 - Interior Check - Cabin6 steps
| 01 | Transmission Oil LevelCHECK | |
| 02 | CargoCHECK - Proper loading and security | |
| 03 | Loose EquipmentSTOWEDNOTE: Stow rotor blade tiedown, pitot tube cover, tailpipe cover and other equipment. | |
| 04 | Passenger Seats and BeltsCHECK - Condition and security | |
| 05 | First Aid Kits and Fire ExtinguisherCHECK SECURE | |
| 06 | Crew and Passenger BriefingCOMPLETE AS REQUIRED |
PHS 4 - Before Starting Engine31 steps
| 01 | DC Circuit BreakersINNOTE: Except for armament and special equipment. | |
| 02 | PITOT HTR SwitchOFF | |
| 03 | ANTI COLL SwitchON | |
| 04 | POSITION Lights SwitchesAS REQUIREDNOTE: STEADY or FLASH for night, OFF for day. | |
| 05 | CARGO REL and WIPERS SwitchesOFF | |
| 06 | CABIN HEATING SwitchesOFF | |
| 07 | INST LTG SwitchesAS REQUIRED | |
| 08 | PHASE SwitchAC | |
| 09 | INVTR SwitchOFFNOTE: AC power stays off until after the engine is started. | |
| 10 | MAIN GEN SwitchON - Cover down | |
| 11 | VM SelectorESS BUS | |
| 12 | NON-ESS BUS SwitchAS REQUIRED | |
| 13 | STARTER GEN SwitchSTART | |
| 14 | BAT SwitchON | |
| 15 | Ground Power UnitCONNECT FOR GPU STARTNOTE: Only if a GPU start is being made. | |
| 16 | FIRE Warning Indicator LightTEST | |
| 17 | Press to Test Caution / Warning LightsCHECK AS REQUIRED | |
| 18 | Systems InstrumentsCHECKNOTE: Check engine and transmission systems for static indications, slippage marks and ranges. | |
| 19 | Avionics EquipmentOFF - Set as desired | |
| 20 | External Stores Jettison HandleCHECK SAFETIED | |
| 21 | GOV SwitchAUTO | |
| 22 | DE-ICE SwitchOFF | |
| 23 | MAIN FUEL SwitchON | |
| 24 | START FUEL SwitchON | |
| 25 | All Other Fuel SwitchesOFF | |
| 26 | CAUTION Panel LightsTEST AND RESET | |
| 27 | HYD CONT SwitchON | |
| 28 | FORCE TRIM SwitchON | |
| 29 | CHIP DET SwitchBOTH | |
| 30 | Flight ControlsCHECK - Full travelNOTE: Center cyclic and pedals; collective pitch full down. | |
| 31 | AltimetersSET TO FIELD ELEVATION |
PHS 5 - Starting Engine14 steps
| 01 | FireguardPOSTED IF AVAILABLE | |
| 02 | Rotor BladesCHECK CLEAR AND UNTIEDWARNING: Visually confirm the rotor disc area is clear of persons and obstacles before engaging the starter. | |
| 03 | Ignition Key Lock SwitchON | |
| 04 | ThrottleSET FOR STARTNOTE: Position the throttle as near as possible, on the decrease side, to the engine idle stop. | |
| 05 | Start SwitchPRESS AND HOLD - Note start timeCAUTION: TM 5-7b: maximum starter energize time is 40 seconds, with a three-minute cooling time between attempts and three attempts in any one hour.NOTE: Note the DC voltmeter indication. Battery starts can be made below 24 volts provided the voltage is not below 14 volts when cranking through 10 percent N1. | |
| 06 | Main RotorCHECK TURNING AT 15 PERCENT N1WARNING: If the rotor is not turning as N1 reaches 15 percent, abort the start. | |
| 07 | Exhaust TemperatureMONITORWARNING: Figure 5-1: starting and acceleration limits are 625 to 675 degC for 10 seconds and 675 to 760 degC for 5 seconds. 760 degC is the absolute maximum. If EGT limits are exceeded or will be exceeded, carry out the Fire-Engine Start procedure (TM 9-30).NOTE: Flames emitting from the tailpipe are acceptable if the EGT limits are not exceeded. | |
| 08 | START FUEL SwitchOFF AT 40 PERCENT N1 | |
| 09 | Start SwitchRELEASE AT 40 PERCENT N1NOTE: Or after 40 seconds, whichever occurs first. | |
| 10 | ThrottleADVANCE SLOWLY TO ENGINE IDLENOTE: Advance slowly past the engine idle stop to the engine idle position, then manually check the engine idle stop by attempting to close the throttle. | |
| 11 | N168 TO 72 PERCENTNOTE: Hold very slight pressure against the engine idle stop during the check. A slight rise in N1 may be anticipated after releasing pressure on the throttle. | |
| 12 | INVTR SwitchMAIN ONCAUTION: The copilot attitude indicator should be caged and held momentarily as inverter power is applied. | |
| 13 | Engine and Transmission Oil PressuresCHECKNOTE: Figure 5-1: engine oil pressure minimum at engine idle is 25 PSI; 80 to 100 PSI is the continuous range and 100 PSI is the maximum. Transmission oil pressure minimum is 30 PSI, continuous 40 to 60 PSI, maximum 70 PSI. | |
| 14 | GPUDISCONNECT |
PHS 6 - Engine Runup10 steps
| 01 | AvionicsON | |
| 02 | STARTER GEN SwitchSTBY GEN | |
| 03 | Fuel SystemCHECKNOTE: Figure 5-1: fuel pressure continuous range is 5 to 35 PSI. | |
| 04 | Engine SystemCHECKNOTE: Figure 5-1: N1 maximum is 101.5 percent. Exhaust temperature continuous range is 400 to 610 degC; 610 to 625 degC is limited to 30 minutes. | |
| 05 | Transmission SystemCHECKNOTE: Figure 5-1: transmission oil temperature maximum is 110 degC. | |
| 06 | Electrical System - AC112 TO 118 VOLTS | |
| 07 | Electrical System - DCCHECKNOTE: 27 volts at 26 degC and above, 28 volts from 0 degC to 26 degC, 28.5 volts below 0 degC. | |
| 08 | RPM6600NOTE: As the throttle is increased, the low rpm audio and warning light should go off at 6100 to 6300 rpm. | |
| 09 | Avionics and Flight InstrumentsCHECK AND SET AS REQUIRED | |
| 10 | Health Indicator Test (HIT) CheckPERFORM AS REQUIREDNOTE: Refer to the HIT/EGT log in the helicopter logbook. A difference of plus or minus 20 degC or greater from baseline EGT requires an entry on DA Form 2408-13-1; plus or minus 30 degC or greater and the aircraft shall not be flown. |
PHS 7 - Hover / Taxi Check7 steps
| 01 | Engine and Transmission InstrumentsCHECK | |
| 02 | VSI and AltimeterCHECK - Indication of climb and descent | |
| 03 | Slip IndicatorCHECK - Ball free in race | |
| 04 | Turn Needle, Heading Indicator and Magnetic CompassCHECK - Turn indication left and right | |
| 05 | Attitude IndicatorCHECK - Nose high and low, banks left and right | |
| 06 | Airspeed IndicatorCHECK AIRSPEED | |
| 07 | Power CheckAS REQUIREDCAUTION: The torque gauge is marked with the maximum torque limit for the individual engine as reflected by its engine Data Plate Torque. Refer to the Torque Available chart in TM Chapter 7.NOTE: Compare the indicated torque required to hover with the predicted values from the performance charts. |
PHS 8 - Before Take-off4 steps
| 01 | RPM6600 | |
| 02 | SystemsCHECKNOTE: Check engine, transmission, electrical and fuel systems indications. | |
| 03 | AvionicsAS REQUIRED | |
| 04 | Crew, Passengers and Mission EquipmentCHECK |
PHS 9 - Take-off6 steps
| 01 | HoverSTABILIZE AT APPROXIMATELY 3 FEET SKID HEIGHTNOTE: Align the helicopter with the desired take-off course. | |
| 02 | CyclicAPPLY FORWARD SMOOTHLY AND GRADUALLYWARNING: TM 8-31: during take-off and any time the skids are close to the ground, negative pitch attitudes (nose low) of 10 degrees or more can result in ground contact of the WSPS lower cutter. Forward CG, high gross weight, high density altitude, transitional lift setting and a tail wind all increase the probability of ground contact. | |
| 03 | CollectiveINCREASE SIMULTANEOUSLYNOTE: Coordinated climb, or level acceleration at approximately 3 to 5 feet skid height (TM 8-33). | |
| 04 | PedalsADJUST TO MAINTAIN HEADING | |
| 05 | TorqueAPPLY MAXIMUM AVAILABLECAUTION: Maximum torque available should be applied without exceeding helicopter limits, prior to accelerating through effective translational lift. | |
| 06 | Climb AirspeedESTABLISHCAUTION: Care must be taken not to decrease airspeed during the climb out since this may result in the helicopter descending.NOTE: Approximately five knots prior to reaching the desired climb airspeed, gradually release forward cyclic pressure and allow the helicopter to begin a constant airspeed climb. |
PHS 10 - Climb4 steps
| 01 | AirspeedSELECT TO CLEAR OBSTACLESNOTE: TM 8-35: after take-off select the speed necessary to clear obstacles. When obstacles are cleared, adjust airspeed as desired at or above the maximum rate of climb airspeed. Refer to TM Chapter 7 for recommended airspeeds. | |
| 02 | RPM6600 | |
| 03 | Engine InstrumentsMONITORCAUTION: Figure 5-1: exhaust temperature above 610 degC is limited to 30 minutes and 625 degC is the maximum for that period. | |
| 04 | AltimeterSET |
PHS 11 - Cruise6 steps
| 01 | PowerADJUST FOR REQUIRED AIRSPEEDNOTE: TM 8-36: refer to Chapter 7 for recommended airspeeds, power settings and fuel flow. | |
| 02 | Rotor RPMCHECKCAUTION: TM 5-6b: with metal main rotor blades installed, restrict rotor speed to 319 to 324 RPM (6500 to 6600 engine RPM) during cruise flight. This restriction does not apply with composite blades.NOTE: Figure 5-1: 294 to 324 rotor RPM continuous (6400 to 6600 engine RPM). 339 rotor RPM is the maximum. | |
| 03 | AirspeedWITHIN LIMITSWARNING: Figure 5-1: 112 knots maximum with the nose mounted pitot tube, 124 knots maximum with the roof mounted pitot tube. VNE varies with gross weight, pressure altitude and free air temperature. Refer to the Airspeed Operating Limits chart, Figure 5-2 or 5-2.1. | |
| 04 | Fuel StateMONITOR | |
| 05 | NavigationCHECK - Heading and position | |
| 06 | Engine and Transmission InstrumentsSCAN |
PHS 12 - Descent4 steps
| 01 | Power and AttitudeADJUSTNOTE: TM 8-37: adjust power and attitude as necessary to attain and maintain the desired speed and rate during descent. Refer to Chapter 7 for power requirements at selected airspeeds and rates of descent. | |
| 02 | Mission Equipment ChecksACCOMPLISHNOTE: All checks of mission equipment that must be made in preparation for landing should be accomplished during descent. | |
| 03 | AltimeterSET - Local QNH | |
| 04 | Landing ZoneIDENTIFYNOTE: Note wind direction, obstacles and surface condition. |
PHS 13 - Before Landing2 steps
| 01 | RPM6600 | |
| 02 | Crew, Passengers and Mission EquipmentCHECK |
PHS 14 - Landing5 steps
| 01 | ApproachESTABLISHWARNING: TM 8-39a: refer to the Height Velocity Diagram, Figure 9-3, for the avoid area during the approach. | |
| 02 | Aft CG ConsiderationCHECKCAUTION: TM 5-8c: when flying at an aft CG (station 140 to 144) terminate the approach at a minimum of a five-foot hover prior to landing to prevent striking the tail on the ground. | |
| 03 | TouchdownSKIDS ON GROUND - LEVEL ATTITUDE | |
| 04 | CollectiveFULL DOWN AFTER TOUCHDOWN | |
| 05 | Run-On Landing (If Required)TOUCHDOWN ABOVE ETLNOTE: TM 8-39b: a run-on landing may be used during hydraulic power failure, some flight control malfunctions, and certain environmental conditions. The approach is shallow and flown at an airspeed that provides safe helicopter control, with touchdown above effective translational lift. After ground contact slowly decrease collective pitch to minimize forward speed. |
PHS 15 - Engine Shutdown19 steps
| 01 | ThrottleENGINE IDLE FOR TWO MINUTESWARNING: TM 8-40: if the throttle is inadvertently rolled to the OFF position, do not attempt to roll it back on. | |
| 02 | FORCE TRIM SwitchON | |
| 03 | PITOT HTRCHECKNOTE: Steps 117 through 122 are to be completed after the last flight of the day if system operation was not verified during the mission. Place the PITOT HTR switch ON, note the loadmeter increase, then OFF. | |
| 04 | INVTR SwitchOFFNOTE: Check for INST INVERTER caution light illumination, then switch to SPARE and check the caution light goes off. | |
| 05 | AC VoltmeterCHECK 112 TO 118 VOLTS | |
| 06 | MAIN GEN SwitchOFFNOTE: The DC GENERATOR caution light should illuminate and the standby generator loadmeter should indicate a load. | |
| 07 | MAIN GEN SwitchON - Guard closedNOTE: The DC GENERATOR caution light should be out and the main generator loadmeter should indicate a load. | |
| 08 | STARTER GEN SwitchSTART | |
| 09 | ThrottleOFF | |
| 10 | Center Pedestal FUEL SwitchesOFF | |
| 11 | Center Pedestal AvionicsOFF | |
| 12 | Overhead INVTR SwitchOFF | |
| 13 | Overhead PITOT HTR SwitchOFF | |
| 14 | Overhead LTS SwitchesOFF | |
| 15 | Overhead MISC SwitchesOFF | |
| 16 | Overhead CABIN HEATING SwitchesOFF | |
| 17 | Overhead INST LTG SwitchesOFF | |
| 18 | BAT SwitchOFFCAUTION: TM 5-16: the helicopter should not be towed for 25 minutes after the battery and inverter switches have been turned off, to prevent damage to the attitude and directional gyros. | |
| 19 | Ignition Keylock SwitchREMOVE KEY AS REQUIRED |
PHS 16 - Before Leaving The Helicopter4 steps
| 01 | Walk-AroundCOMPLETENOTE: Check for damage, fluid leaks and levels. | |
| 02 | Mission EquipmentSECURE | |
| 03 | DA Forms 2408-12 and 2408-13COMPLETENOTE: An entry on DA Form 2408-13 is required if the helicopter was flown in a loose grass environment, operated in a salt-laden environment, exposed to radioactivity, operated in rain, ice or snow, or operated in a volcanic ash environment. An entry is also required any time an operating limit was exceeded. | |
| 04 | HelicopterSECURENOTE: Install rotor blade tiedown, pitot tube cover and tailpipe cover. |