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AIRBUS H125 /AS350B3 / B3e > AIRBUS H125 / AS350B3 (2B1 Engine) Limitations > Flashcards

AIRBUS H125 / AS350B3 (2B1 Engine) Limitations Flashcards

AIRBUS H125 / AS350B3 (2B1 Engine) Check Ride Study Info

1
Q

DISCLAIMER

A

This flash card study aide is provided to ease and assist in studying much more comprehensive material provided by Eurocopter / Airbus. The creator of this study aide accepts no responsibility for inaccuracies or abbreviation of procedures. This is intended to introduce the associated material and all persons using these cards should study and reference the officially distributed material from the manufacturer. It is recommended that after referencing each card, the student should independently verify the information on that card by looking it up and learning the comprehensive information from the direct source. If any inaccuracies, misleading or typo errors are found, please notify the administrator of the study deck.

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2
Q

THE FOLLOWING ARE FORBIDDEN

A
  • 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)
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3
Q

OCCUPANTS

A
    • 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)

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4
Q

INSTRUMENT MARKINGS

A

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.

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5
Q

WEIGHT LIMITATIONS

A
  • Maximum internal weight for flight, 5225 (With High skid and Dual Hydraulics)
  • IF CARRYING EXTERNAL LOAD Maximum internal weight for flight, 4961 lbs. (Even With Dual Hydraulics and High Skids)

With External Load 6173

Sling Limit 1660

Swing Limit 3086

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6
Q

AIRSPEEDS

A

POWER ON VNE 155 Knots

POWER OFF VNE 125 Knots

-3 Knots per 1000 Density Altitude

Absolute maximum permissible IAS with external load 80 kt

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7
Q

ALTITUDE LIMITATION

A

23,000 feet

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8
Q

TEMPERATURE LIMITS

A

Minimum Temperature -40ºc

Maximum Temperature ISA +35ºc, limited to 50ºc

(every increase of 1000 ft Hp subtract 2ºc from maximum)

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9
Q

SLOPE LIMITATIONS

A

Nose up 10º

Nose down 6º

Side to Side 8º

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10
Q

RUNNING LANDING LIMITS

A

Excluding emergencies and failures, maximum speed for performing running landings

40 kt.

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11
Q

MANEUVER LIMITATIONS

A

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 reaction 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.

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12
Q

MAIN ROTOR LIMITATION

A

It is prohibited to use the rotor brake prior to engine shutdown.
Minimum time between two consecutive brake applications: 5 min.

Low NR aural warning below 360 rpm
High NR aural warning above 410 rpm

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13
Q

ROTOR BRAKE LIMITATIONS

A

Max 170 RPM (High Winds)

Recommended 140 RPM

Minimum time between consecutive braking 5 Minutes

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14
Q

MAIN TRANSMISSION LIMITATIONS

(MAXIMUM TORQUE)

A
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15
Q

FIRST LIMIT INDICATOR

A

Use of heating and demisting is forbidden above the engine maximum continuous rating (Ng or t4)

**NOTE**
The values (Ng = 100 %, t4 = 680 °C, Tq = 90%) are given as examples.
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16
Q

N2 (NF) LIMITS

A

Use of heating and demisting is forbidden above the engine maximum continuous rating (Ng or t4). Use of engine takeoff rating range, is limited to 5 continuous minutes.

NOTE
A rotor speed of NR 386 rpm corresponds to an N2 speed of 39158 rpm

17
Q

N1 (NG) LIMITS

A

NOTE
100 % N1 corresponds to 52110 rpm

18
Q

TOT (T4) LIMITS STARTING

A
19
Q

TOT (T4) LIMITS FLIGHT

A
20
Q

ENGINE OIL TEMPERATURE

A

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.

21
Q

ENGINE OIL PRESSURE

A

Oil pressure has variable limits that depend on N1

22
Q

ELECTRICAL SYSTEM

A

Minimum Voltage 25v

Maximum Voltage 31.5v

Rated Voltage 26-29v

Max Current 150Amps

For 200 A Starter Generator
(if installed), refer to SUP.29

23
Q

FUELS

A

NO RESTRICTIONS

  • JET A / A1
  • JP5 (HIGH FLASH POINT)
  • JP8 (KEROSENE 50)
  • REPLACEMENT FUELS
    (Fuels allowing operations in a restricted flight envelope.)
    • Fuels with restricted flight envelope of:
    OAT ≤ 25 °C and Hp ≤ 5000 ft (1524 m)
  • JP4 (WIDECUT)
  • JET BWIDECUT

REFUELING

Fuel temperature must be within the above OAT limitations specified for the fuel actually used for refueling. The engine can operate with mixtures of normal and replacement fuels. The limitations associated with the mixture correspond to the most restrictive of all the fuels used for the mixture. In order to overcome the limitation of the most restrictive fuel, the helicopter fuel system shall be drained.

24
Q

ANTI ICE ADDITIVE

A

If temp is below 0c, and fuel does not already contain an system icing inhibitor, the use of anti-icing additive is compulsory. (Prist)The concentration shall be from 0.10% to 0.15% by volume.

25
Q

OIL

A

Mobile Jet 254

or

Royco 586M

(Don’t mix oils!)

26
Q

MGB AND TGB LUBRICANT

A

MINERAL OIL

27
Q

HYDRAULIC SYSTEM FLUID

A

SYNTHETIC MIL-H-83282

28
Q

LOAD LIMITS

A
  • Rear Cabin Floor 682 lbs.
  • Forward Cabin Floor 330 lbs.
  • Rear Hold 176 lbs.
  • Left Hand Hold 264 lbs.
  • Right Hand Hold 220 lbs.
  • (62.5 lb/ft2)
  • (check placards on each ship)
29
Q

STARTER GENERATOR

A

When starting the engine, the starter time is the time between selecting the engine starting selector to ON and the engine igniting. When performing an engine ventilation, the starter time is the duration that the
[CRANK] is pressed.

To prevent starter overheat damage, limit starter time to the following:
- 30 seconds ON
- 60 seconds OFF
- 30 seconds ON
- 60 seconds OFF
- 30 seconds ON
- 30 minutes OFF
The 30 minute cooling period is required before beginning another starting cycle.

30
Q

MANDATORY EQUIPMENT

A

A minimum of two adequate radio/audio headsets shall be on-board the helicopter,
one worn by the pilot at the controls to monitor the audio warnings delivered through
the ICS system, and a spare one.

31
Q

TAIL ROTOR RPM

(information only, not limitation)

A

TR BLADE - 2086 RPM

DRIVE SHAFT - 6125 RPM

32
Q

ENGINE RATING

(5 minute, information only, not limitation)

A

847 Shaft Horse Power (SHP)

(Arriel 2B1)

33
Q

MGB RATING

(information only, not limitation)

A

747 SHP

34
Q

Vy Speed

(Info Only. Not limitation)

A

65 KIAS

35
Q

Safran Arriel 2B1 Modules

(Reference only)

A

AIRBUS H125 /AS350B3 / B3e (6 decks)

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