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BA Knowledge Flashcards

1
Q

5 modules

A
  1. Transmission shaft and accessory gearbox
  2. Axial compressor
  3. Gas generator
  4. Power turbine
  5. Reduction gearbox
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2
Q

Fuel low pressue switch PSI

A

8.4

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3
Q

Gas Generator

A

N1

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4
Q

N1C sent to?

A

EBCAU and EICAS

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5
Q

N1A and N1B sent to?

A

FADEC and EICAS

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6
Q

Free Power Turbine

A

N2

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7
Q

N2A sent to?

A

CDU for indication on the MFD

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8
Q

N2B and N2C

A

FADEC and EICAS for N2 speed control and overspeed protection

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9
Q

Overspeed protection provided by

A

BIM

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10
Q

When N2 reaches a speed of ___, the DECU will stop the electro valve via the ___

A

429+/-4 RPM, BIM

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11
Q

Once an engine is shut down by the FADEC/BIM, overspeed protection is

A

automatically inhibited on the second engine

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12
Q

BIM acts as a ___

A

start relay

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13
Q

TOT is measured at the ___

A

free power turbine inlet

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14
Q

Engine oil tank capacity

A

approximately 2 gal

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15
Q

Temperature probe located on __ and sends signal to ___

A

outlet side of tanks, EICAS

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16
Q

Engine oil coolers location?

A

mounted forward of the MGB in series with the MGB oil cooler

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17
Q

Engine oil pressure is monitored by

A

a pressure switch and a transmitter located downstream of the engine oil filter on the left side of each engine accessory gearbox

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18
Q

When oil pressure drops below the __ minimum, the respective warning light illuminates on the ___

A

25, EICAS

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19
Q

Indicators for temp, pressure, and chip detection are provided on the ___ page

A

EICAS

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20
Q

Thermostatic bypass switch for engine oil is located

A

between the cooler and the reservoir

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21
Q

Type of fire detectors?

A

bimetallic

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22
Q

How many engine fire detectors, and what temp?

A

3 total
Two 200C on the accessory/reduction gearbox
One 400C on the gas generator

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23
Q

Engine oil filter pre-blockage indicator PSI?

A

36PSID

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24
Q

Engine oil filter bypass?

A

82PSID

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25
Q

When engine oil is less than __ degrees C, it will bypass the oil cooler.

A

45

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26
Q

Above __ KIAS, ram air alone is sufficient for oil cooling.

A

75

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27
Q

FADEC main functions?

A
  1. Starting
  2. Speed control
  3. Automatic back-up control
  4. Over-speed protection
  5. System monitoring and fault management
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28
Q

FADEC powered by?

A

Engine driven, dual channel alternators AND aircraft power supply

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29
Q

FADEC is a ___ that controls engine operation an is designed to match the __ of both engines.

A

dual channel computer, N1

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30
Q

If neither channels of the FADEC can control the engine, back up operation is available through the ___

31
Q

At sea level, under standard day conditions, the NR speed is ___

32
Q

NR HI increases the NR RPM to?

33
Q

NR HI switch usage is limited to?

A

135 KIAS / 40 degrees angle of bank

34
Q

Another function of the N2 controller allows it to increase ___ at higher altitudes to maintain rotor efficiency.

35
Q

Above __ ft, NR is increased 1 RPM for every 840 ft to a maximum of __ RPM.

36
Q

If the NR system fails, the NR will default to __ RPM.

37
Q

In the normal torque limitation flight envelope, the FADEC stops torque at ___

38
Q

FADEC failures

A

Level 1: loss of redundancy
Level 2: loss of non-redundancy
Level 3: Major FADEC failure (dual-channel FADEC failure)

39
Q

Any time the FADEC detects a __% split or a ___, the OEI HI operation is enabled (OEI LO in training).

A

6%, frozen fuel

40
Q

Training mode governs an engine to __ RPM

41
Q

MGB oil quantity

A

9.34 quarts

42
Q

MGB had two lubricating systems consisting of a two stage oil pump, connected by a __

A

shear shaft

43
Q

Above ___ KIAS, ram air alone is sufficient for engine cooling.

44
Q

A MGB minimum pressure of ___ at the filter outlet will cause the ___ warning light to illuminate and the two master warning lights located on the instrument panel to illuminate.

A

9 (+/- 1), MGB PRESS

45
Q

When AUX pump is providing lubrication, you will see a _ and _

A

increase in oil temp, lower pressure

46
Q

No. 1 fuel system and No. 2 fuel system capacity?

47
Q

PRI SERVO P and SEC SERVO P warning message at what PSI?

48
Q

Secondary hydraulic high/low pressure?

49
Q

Hydraulic isolate shuts off what?

A 
Landing gear
Wheel Brake
Talon 
Normal Hoist power
Left body of the tail rotor flight control servo
50
Q

How much hydraulic fluid to trigger an isolate condition?

A

below 1 gal

51
Q

Primary hydraulic system provides 870 PSI to

A

The upper bodies of the MRH flight control servos and the right body of the tail rotor control servo

52
Q

How much hydraulic fluid in the primary system?

53
Q

Where are the hydraulic manifolds located?

A

Primary: Distribution on both sides of the MGB, regulation on the transmission deck

Secondary: Distribution on both sides of the MGB, Generation on the transmission deck, regulation by the A/C

54
Q

Secondary hydraulic system provides PSI to what?

A

3000 to the hoist
2000 to the landing gear, talon, and brake
870 to the lower bodies of the main rotor flight control servos and left body of the tail servo

55
Q

The secondary hydraulic system regulation manifold has a pressure relief valve installed to limit secondarily pressure to _ psi.

56
Q

What are the three reduction ratios of the MGB gear system?

A

17 to 1 to 1.5 to 1

57
Q

The MGB auxiliary pump provides only what?

A

Internal oil flow

58
Q

Where are the NR Tach gen and magnetic sensor on the phonic wheel located?

A

Lower forward section of the MGB, upper MGB housing

59
Q

The rotor shaft transmits MGB output power to the tail rotor at approximately ___ at a main rotor speed of 355 RPM (100% NR).

60
Q

Scavenge ejector pumps, driven by boost pump pressure, are located within the ___ and the ___

A

left forward cell, aft cell

61
Q

A two-way transfer pump, rated at approximately ___ lb per hour, connects the two center cells by allowing fuel transfer between systems.

62
Q

If operating above ___ ft MSL, both boost pumps shall be on to prevent a possible feed tank failure.

63
Q

In the normal hover attitude (4 degrees nose up), indicated fuel is approximately _ percent less than actual fuel.

64
Q

The FUEL QTY TOTAL is located between each system’s tape and digital readout, which displays yellow when the total fuel quantity is ≤__ lb.

65
Q

The engine-driven low-pressure fuel pump continues to draw fuel from its respective system until approximately __ lb is indicated in the event of a left failure or __ lb for a right failure.

66
Q

If fuel is not transferred immediately, flameout of the corresponding engine occurs when the feed tank empties (approximately _ minutes).

67
Q

Maximum allowable pressure for pressure refueling is __ psi.

68
Q

The fuel jettison rate is approximately __ lb per minute and will exhaust jettisonable fuel within __ minutes.

69
Q

Remaining fuel will consist of __ lb in each feed tank plus residual fuel which is retained by those cells not having a jettison valve. This amounts to approximately __ lb in the left (No. 1) system, and approximately __ lb in the right (No. 2) system.

A

43 ; 150 ; 170

70
Q

During normal (two-engine) operation, the remaining fuel is consumable except for approximately __ lb in the left system and __ lb in the right system which is unusable.

71
Q

If an engine failure occurs after jettisoning all available fuel, transferring fuel to the operating engine will ensure sufficient fuel for approximately __ minutes of flight at
maximum endurance power setting.

72
Q

Placing the emergency ELECTRICAL CUTOFF switch to CUTOFF removes power to the__.

A

tail rotor hydraulic isolation valve, closing the valve ; all communications

73
Q

Two 4.5-kVA starter/generators, mounted on the accessory gearbox of each respective engine, supply a
regulated output of 28 VDC whenever the engines are operating at or above __% N1.

FM (4 decks)

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