AIRBUS H125 / AS350B3e (2D Engine) Limitations Flashcards
AIRBUS H125 / AS350B3e (2D Engine) Check Ride Study Info
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THE FOLLOWING ARE FORBIDDEN
- Aerobatic maneuvers.
- Engine starting when snow or ice accumulations are in or around the engine air intake.
- Flight in falling snow without optional sand filter installed.
- Flight in freezing rain or icing conditions. (Visible moisture and temperature conducive to producing ice).
- In-flight engine power reduction using twist grip control except for engine failure training, emergency procedures referring to it, or maintenance check procedures.
- In-flight intentional VEMD complete cut-off (lane 1 + 2)
OCCUPANTS
- Minimum flight crew : One pilot in right seat
(Pilot must have collective with Hyd Cut Off switch on collective)
- Maximum number of occupants (including flight crew) : Six
(Note: This indicates the pilot should not leave the controls while rotor is turning)
INSTRUMENT MARKINGS
Limitations are marked on instruments with the following color code:
On the VEMD, related numerical values of parameters are underlined:
- In yellow, when the parameter is in caution or takeoff power range,
- In red, when at or above a safety limit or maximum takeoff power. Moreover, to
attract attention, red underlining flashes.
WEIGHT LIMITATIONS
- Maximum internal weight for flight, 5225 lbs. (With Dual Hydraulics and High Skids)
- IF CARRYING EXTERNAL LOAD Maximum internal weight for flight, 4961 lbs. (Even With Dual Hydraulics and High Skids)
- Minimum internal weight for flight, 2888 lbs.
With External Load 6173
Sling Limit 1660
Swing Limit 3086
AIRSPEEDS
POWER ON VNE 155 Knots
POWER OFF VNE 125 Knots
-3 Knots per 1000 Density Altitude
ALTITUDE LIMITATION
23,000 feet
TEMPERATURE
LIMITS
Minimum Temperature -40ºc
Maximum Temperature ISA +35ºc, limited to 50ºc
(every increase of 1000 ft Hp subtract 2ºc from maximum)
RECOMMENDATION:
- When the aircraft has been subject to very low temperatures, it is recommended:
• either to perform regular ground runs every two hours for temperatures of around - 20°C or every hour for lower temperatures.
• or to preheat the engine, transmission assemblies and cabin before engine starting (even if it is possible to start the engine at temperatures down to - 40°C).
SLOPE LIMITATIONS
Nose up 10º
Nose down 6º
Side to Side 8º
RUNNING LANDING LIMITS
Excluding emergencies and failures, maximum speed for performing running landings
40 kt (74 km/h).
MANEUVER LIMITATIONS
Continued Operation in Servo Transparency (Where Force Feedback is Felt In The Controls) Is PROHIBITED
Maximum load factor is a combination of TAS, Hσ and gross weight. Avoid such combinations at high values associated with high collective. Transparency may be reached during maneuvers, steep turns, hard pull-up or when maneuvering near VNE. Self- correcting, the phenomenon will induce an uncommanded right cyclic load and an associated collective down reaction. However, even if the transparency feedback loads are fully controllable, immediate action is required to relieve the feed back loads: reduce the severity of the maneuver, follow the aircraft’s natural reaction, let the collective decrease naturally (avoid low pitch) and smoothly counteract the right cyclic motion. Transparency will disappear as soon as excessive loads are relieved.
- In maximum power configuration, decrease collective slightly before initiating a turn, as for this maneuver the power requirement is increased.
- In hover, avoid rotation faster than 6 sec. per full rotation.
MAIN ROTOR LIMITATION
It is prohibited to use the rotor brake prior to engine shutdown.
Minimum time between two consecutive brake applications: 5 min.
ROTOR BRAKE LIMITATIONS
Max 170 RPM (High Winds)
Recommended 140 RPM
Minimum time between consecutive braking 5 Minutes
TAKEOFF POWER
Takeoff power is limited to:
- Maximum airspeed 40 KIAS.
- If N1 and/or TOT is in Takeoff power range (numerical value of related parameter underlined in yellow):
- 5 min. continuous use (Pre-MOD OP-4309)*
- 30 min. continuous use (Post-MOD OP-4309)*
- If only the Torque (TRQ) is in Takeoff power range, there is no time limit.
- Use of heating and demisting is authorized up to max. TOP.
- (*) MOD OP-4309: Tail rotor drive shaft reinforced thermal protection
FIRST LIMIT INDICATOR
NOTE The values (N1 = 100 %, TOT = 680 °C, TRQ = 90%) are given as example.
MAIN TRANSMISSION LIMITATIONS
(MAXIMUM TORQUE)
N2 LIMITS
NOTE
A rotor speed of NR 386 rpm corresponds to an N2 speed of 39158 rpm
N1 LIMITS
NOTE
100 % N1 corresponds to 52110 rpm
TOT LIMITS STARTING
TOT LIMITS FLIGHT
ENGINE OIL TEMPERATURE
MAX °117c
Minimum oil temperature before power application:
- 0°C (Oil 5 cSt).
-10°C (Oil 3 to 3.9 cSt).
During the oil warm up period, the engine must be run with the collective in its full low
pitch position. The twist grip can be in “IDLE” or “FLIGHT” position.
ENGINE OIL PRESSURE
Oil pressure has variable limits that depend on N1
Safran Arriel 2D Modules
(Reference only)
