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AIRBUS H125 /AS350B3 / B3e > AIRBUS H125 / AS350B3e (2D Eng) Performance and Information > Flashcards

AIRBUS H125 / AS350B3e (2D Eng) Performance and Information Flashcards

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

MINIMUM BATT VOLTAGE DURING START PROCEDURE

A

22V

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3
Q

PROCEDURE IN CASE OF FAILED / ABORTED START

A

Return the engine starting selector to OFF, wait 30 sec., perform an engine crank before next start attempt.

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4
Q

WHEN DOES THE UPPER VEMD CHANGE TO THE FLI DURING START?

A

WHEN N1 IS ABOVE 60%

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5
Q

CAN HEATING DEMISTING SYSTEM BE USED DURING TAKEOFF?

A

Heating and demisting system can be used during takeoff but this degrades the aircraft hover and climb performance shown in SECTION 5 when operating at engine limits (N1, TOT)

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6
Q

WHAT IS MAX CLIMB Vy?

A

IAS kt = 65 kt at 0 HP - (1 kt per 1000 ft)

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7
Q

WHEN IS THE FLIGHT REPORT PAGE DISPLAYED?

A

ON SHUT DOWN BELOW 60% N1

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8
Q

FUEL CELL CAPACITY

and

(Usable Amount)

A
  1. 7 Gallons
  2. 1 Usable
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9
Q

YELLOW ZONE ON FUEL GAUGE

A

15.8 Gallons Remaining

15 Minutes Flight Time at MCP

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10
Q

DOES THE FUEL GAUGE YELLOW ZONE INCLUDE NON-USABLE FUEL?

A

NO

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11
Q

DEMONSTRATED WIND ENVELOPE FOR STARTING AND STOPPING ROTOR

(Not Limitation)

A

Starting and stopping the rotor has been demonstrated for winds of 40 kt from any direction and 50 kt with a headwind (forward center axis +/- 30°).

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12
Q

WHEN MUST BLADES BE TIED DOWN (Wind)?

A

Above 40 kt

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13
Q

HOW DO YOU CHECK ENGINE POWER IN HOVER BEFORE TAKEOFF?

A

In HIGE at 5ft and before initiating forward flight, pull the collective pitch lever slightly to ensure that the N1 can increase by at least 1%, without exceeding the max. transient rating

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14
Q

HOW DO YOU PERFORM A FADEC/ENGINE HEALTH CHECK?

A
  • The engine health check is performed in level flight MCP, heating and demisting system and ECS OFF.
  • Prefer an altitude where the engine is operating close to the N1 MCP limit.
  • Stabilize level flight MCP for at least 2 min. before initiating the engine health check.
  • Read the results displayed on VEMD after the end of the procedure.
  • The engine health check is satisfactory if:
  • TRQ MARGIN / TOT is above 0%, “GOOD” displayed, and
  • TRQ MARGIN / N1 is above 0%,“GOOD” displayed
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15
Q

DESCRIBE THE 3 ANCILLARY SYSTEMS

(PCB’s under the rear right passenger seat)

A

PCB1 - Fire warning lights, Aural NR warning horns, Gong

PCB2 - ENG chip, MGP chip, TGB chip caution lights, NR/NF signals, BATT TEMP warning light and processes VEMD electrical supply

PCB3 - EBCAU backup unit

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16
Q

CAN PILOT PERFORM AN EBCAU CHECK DURING FLIGHT OR ON THE GROUND?

A

NO

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17
Q

IS OUR GARMIN ACCEPTABLE FOR IFR FLIGHT?

A

NO, VFR only

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18
Q

WHAT TYPE OF ENGINE

A

Safran (Turbomeca) Arriel 2D

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19
Q

SAFRAN ARRIEL 2D Power Rating

A

MTOP 952 SHP

MCP 856 SHP

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20
Q

ENGINE MODULES

A
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21
Q

LIST DIFFERENT WARNING SOUNDS

A

GONG - When a red warning appears on panel

CONTINUOUS HORN - When NR is below 360 rpm, When maximum takeoff limits are exceeded for more than 1.5 seconds

INTERMITTENT HORN - NR above 410 rpm

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22
Q

OVERALL LENGTH

from tip of rotor to tail

A

42.47’

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23
Q

ROTOR DIAMETER

A

35.07’

24
Q

FENESTRON SPECS

A

6.01’ DIAMETER

3086 RPM

25
Q

Vy USED FOR TAKE OFF, LAND, APPROACH AND EMERGENCY MANUEVERS

A

65 Knots

26
Q

MAXIMUM TEMP FOR HOT AIR DE-ICE

A

80c

27
Q

AUTOROTATION FLARE HEIGHT

A

70 Feet

28
Q

SCU

A

System Contorl Unit

To tell you which button on the console is engaged before applying power, because the buttons do not stay depressed

29
Q

VEMD

(stands for)

A

Vehicle Engine Multifunction Display

30
Q

WHAT VEMD SCREENS ARE AVAILABLE UNDER FLIGHT MODE?

A
  • Engine
  • Vehicle
  • Flight Report
  • HIGE
  • HOGE
  • Engine Power Check
31
Q

WHERE ARE THE SCROLL BUTTONS LOCATED?

A

One on the collective

Right side of the VEMD unit

32
Q

WHICH VEMD PAGE IS FOR THE ENGINE?

A

Top page

33
Q

HOW MANY CHIP DETECTORS ARE ON THE ENGINE?

A

3

1 electrical

2 magnetic

34
Q

HOW MANY FUEL PUMPS ARE THERE?

A

3

1 boost pump .5 bar

1 low pressure pump 10 bar

1 high pressure pump 40 bar

35
Q

WHAT PART DOES THE OIL FILTER HAVE TO DO WITH THE FUEL SYSTEM?

A

Heats the fuel so anti ice additive is not needed

(anti ice, Prist, only needed if below -20c)

36
Q

EECU

(STANDS FOR)

A

ELECTRONIC

ENGINE

CONTROL

UNIT

37
Q

WHAT DOES

THE EECU

DO?

A
  • Automatic engine starting, preventing TOT overlimit
  • Proportional integral power turbine speed control
  • Protection against engine surge and flame out during transients
  • Bleed valve monitoring
  • Protection against N1 and TOT overlimits
  • Failure detection and indication
  • Engine Health Check
  • N1 and N2 cycle counting
38
Q

WHAT IS

THE EECU

ALSO KNOWN AS?

A

“FADEC”

FULL AUTHORITY DIGITAL ENGINE CONTROL

OR

“DECU”

DIGITAL ENGINE CONTROL UNIT

39
Q

HOW IS THE

EECU SUPPLIED

POWER?

A

2 channel gas generator

driven independent

alternator

40
Q

HOW IS FUEL FLOW DETERMINED AND ADJUSTED?

A

By the EECU

41
Q

WHAT IS AUTOMATIC

2nd CHANCE

ENGINE START?

A

During the engine starting procedure if the ignition does not occur after 5 sec. when N1 greater than 17%, the EECU automatically stops the starting procedure, lets the N1 decrease to 10% and then automatically launches a new starting sequence. This sequence is totally managed by the EECU without pilot action.

NOTE
If the 2nd chance engine start fails, the pilot must carry out a new engine starting procedure as follows:
- engine starting selector to OFF position,
- wait 30 sec.,
- perform a cranking procedure
- perform the engine starting procedure

42
Q

WHAT DOES THE

DUAL STAGE STEPPED MOTOR DO?

A

Provides fuel flow modulation by driving a metering valve in the engine’s ‘hydro-mechanical unit’

43
Q

EECU SYSTEM

FAILURES

3 LEVELS

A

LEVEL 1 - FLASHING YELLOW GOV LIGHT

Reset EECU if before start

In flight, continue to nearest maintenance center

Applicable maintenance before next flight

LEVEL 2 - SOLID YELLOW GOV LIGHT

Avoid operating at engine or torque limits, cautious flight

LAND AS SOON AS PRACTICAL

DO NOT START ENGINE

  • Applicable maintenance before next flight*
  • LEVEL 3* - RED GOV LIGHT (Total EECU failure, metering valve frozen. EBCAU has taken over

During start: IMMEDIATELY SHUT DOWN

Avoid operating at engine or torque limits, cautious flight

LAND AS SOON AS PRACTICAL

44
Q

WILL THE AIRCRAFT START WITH THE ROTOR BRAKE OUT OF THE LOCKED POSITION?

A

NO

45
Q

IS THE OVERHEAD FUEL CUT-OFF LEVER SAFETEY WIRED?

A

No, a plastic cover protects it

46
Q

HOW MANY HYDRAULIC PUMPS?

A

2

Left hand gear driven for for lower portion of servos

Right hand belt driven upper portion of servos

47
Q

DO THE HYDRAULIC PUMPS USE SEPARATE RESERVOIRS?

A

YES

48
Q

WHAT IS THE PURPOSE OF THE ROTARY DISTRIBUTION VALVE?

A

If one of the systems fails, the two valves move as an independent unit and supply pressurized fluid and return

49
Q

IN THE EVENT OF HYDRAULIC FAILURE HOW DO THE HYD ACCUMULATORS HELP?

A

There are NO accumulators

50
Q

WHAT DOES

THE DAY

SETTING DO?

A

VEMD and CWP and DMP lights are set to normal brightness

Position lights on

51
Q

WHAT DOES

NIGHT 1 AND 2

SWITCH DO?

A

2 shuts off compass light

VEMD and CWP lights are dimmed accordingly

Position lights on

52
Q

WHEN DOES GEN TAKE OVER POWER PRODUCTION

A

When it produces .5 volt above battery

53
Q

FAN OPERATION TEMP

A

On at 77c

Off at 68c

54
Q

TR SHAFT SPEED

A

6000 RPM

55
Q

WHY IS THE GPS

CRITICAL TO

THE EECU?

A

It provides a clock for EECU exceedences or failures

56
Q

DIFFERENCE BETWEEN SBT and SLT

A

SBT (Service Bulletin) Due to an incident or event

SLT (Service Letter) Information

AIRBUS H125 /AS350B3 / B3e (6 decks)

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