MSFS 2024 · Rotary

Airbus H125 Quick Reference

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V-SPEEDS

SpeedValueDescription
Vne power-on155 kt at zero HpSection 2.1 para 6.1.1. Reduce 3 kt per 1000 ft; subtract 10 kt when OAT is below -30 degC
Vne power-off125 kt at zero HpSection 2.1 para 6.1.2. Reduce 3 kt per 1000 ft, never below 65 kt; subtract 20 kt when OAT is below -20 degC
Vne cross-hatched CG zone133 ktOr the altitude/temperature corrected VNE, whichever is lower
Vne all four doors removed70 ktSection 2.1 para 6.2.1. Also applies with two RH or two LH doors removed; any other configuration is prohibited
Vy (best climb)65 kt IASSection 4.1 para 7, above 100 ft, reducing 1 kt per 1000 ft
Vauto65 ktSection 3.1 para 2.1. Rate of descent at 65 kt is 1,800 ft/min
Approach speed65 ktSection 4.1 para 9.1, final approach into wind at low sink rate
Transition from hover40 kt IASSection 4.1 para 6. Accelerate to 40 kt without increasing power demand or climbing

POWER SETTINGS

PhaseSetting
Hover / takeoffHover at about 5 ft (1.5 m) head into wind; FLI within limits
ClimbMax continuous power above 100 ft, 65 kt IAS
CruiseMax continuous power for fast cruise; NR 390 +4/-5 rpm
Approach65 kt into wind at low sink rate
AutorotationLow collective pitch, NR in the upper part of the green band, 65 kt
Autorotation trainingTwist grip out of the flight notch to idle without disabling the flight stop; engine regulates at idle Ng approximately 68 percent

ENGINE LIMITS

ParameterValue
EngineTurbomeca ARRIEL 2B (AS 350 B3). The H125 / AS 350 B3e uses the ARRIEL 2D - these figures are 2B values
t4 max for engine starting750 degC
t4 max transient during starting865 degC for 10 seconds maximum
t4 max on takeoff915 degC
t4 max continuous849 degC
Ng max transient102.3 percent, less than 5 seconds (delta Ng +1)
Ng max take-off (5 min)101.1 percent with P2 air bleed off (delta Ng 0)
Ng max continuous97.1 percent (delta Ng -4)
Free turbine max continuous418 rpm
Free turbine transient450 rpm, 5 seconds maximum
Free turbine minimum349 rpm
Main rotor, power on (flight)390 +4/-5 rpm stabilized flight
Main rotor, power on (ground)380 +/- 5 rpm at low pitch
Main rotor, power off430 rpm maximum, 320 rpm minimum
Rotor hornContinuous below 360 rpm, intermittent above 410 rpm
Torque below 40 kt100 percent max continuous, 104 percent max transient (10 s)
Torque at or above 40 kt92.7 percent max continuous
First Limitation Instrument9.6 max continuous; 9.6 to 10 take-off zone (5 min); 10 max take-off; 10.4 max transient
Rotor brakeMaximum 170 rpm for application; 5 minutes minimum between consecutive brakings

KEY NUMBERS

ParameterValue
Maximum permissible weight2,250 kg (4,961 lb). Beyond this only with jettisonable loads
Max pressure altitude23,000 ft (7,010 m)
Temperature limits-40 degC minimum; ISA +35 degC limited to +50 degC maximum
Lateral CG limits0.18 m (7.08 in) left, 0.14 m (5.51 in) right of the symmetry plane
CG datum3.40 m (133.8 in) forward of the main rotor head centre line
Types of operationDay VFR and night VFR (with required equipment), out of icing conditions. FAR Part 27 Normal category
Flight in falling snowAuthorized above 1,500 m visibility; 10 min limit at 800 to 1,500 m; prohibited below 800 m
Autorotation rate of descent1,800 ft/min at 65 kt
Autorotation flare heightFlare at about 65 ft (20 m); apply collective at 20 to 25 ft (6 to 8 m)
Hover rotation rateAvoid faster than 6 seconds for one full rotation
Zero tail rotor thrust on groundPush LH pedal over approximately 2 cm (0.8 in)
Engine relight ceiling20,000 ft normal; relight may be attempted throughout the altitude envelope
ENG.P lightOut at 70 percent Ng
Anti-ice fuel additiveCompulsory below -20 degC OAT if the fuel has no icing inhibitor; 0.10 to 0.15 percent by volume