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Q300 Notes > C5 Dash 8 Component Acronyms > Flashcards

C5 Dash 8 Component Acronyms Flashcards

1
Q

RGB

A

Reduction Gear Box

Reduces high RPM of Power Turbine to lower RPM of the Propeller

Driven off the RGB are:

  1. Hydraulic Pump
  2. AC Generator
  3. Propeller Control Unit
  4. Propeller Overspeed Governor
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2
Q

PSEU

A

Proximity Sensor Electronics Unit

  1. Sequences gear and doors during gear movement
  2. Controls gear and door advisory lights
  3. Activates Warning Horn
  4. Routes inputs into other non-gear systems.
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3
Q

WOW

A

Weight on Wheels Switch

Feeds into multiple systems

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4
Q

HPSOV

A

High Pressure Shut Off Valve

Controls High Pressure Bleed Air

  1. HPSOV will on close on the ground at pressures above 65 psi.
  2. In flight HPSOV will remained closed above 55 psi.
  3. Activation of Deice Boots opens HPSOV in flight.
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5
Q

NSOV

A

Nacelle Shut Off Valve

Controlled by Bleed Air Control Switches. (selecting OFF also closes HPSOV)

Shuts off all bleed air from a given nacelle, preventing Bleed Air from entering ACM supply ducts.

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6
Q

HBOV

A

Handling Bleed Off Valve

Allows LP Bleed Air to cool HP Bleed Air via a heat exchanger. LP Air is then vented overboard.

Also prevents conpressor surges and stalls during slam acceleration / deceleration.

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7
Q

ECU

A

Engine Control Unit

(also refered to as the EEC)

Provides electronic control functions to the engine and related components.

Controlled by ECU Panel: TOP, MCL, and MCR on the -200, TOP only on the -300.

  1. Refines the manual fuel scheduling of the MFC
  2. Controls NP Underspeed Governing
  3. Controls HBOV
  4. Provides Power Uptrim
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8
Q

PROV

A

Pressure Regulator Valve

(-200 Only)

Regulates Bleed Air Pressure to ACM.

18 psi Consumer

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9
Q

PRSOV

A

Pressure Regulator and Shut Off Valve

(-300 only)

Both regulates Bleed Air Pressure and can cut off Bleed Air Supply to either pack.

Controlled by Pack Switches

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10
Q

APU

A

Auxiliary Power Unit

(-300 only)

Provides Bleed Air to AC Packs and 28v DC Power to Right Main Bus.

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11
Q

ESU

A

Electronic Sequence Unit

(-300 only)

Provides automatic control of APU operation. Controlled by APU Control Panel

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12
Q

MFC

A

Manual Fuel Controller

Mechanical fuel metering unit.

Mechanically linked to both Power and Condition levers, uses lever angle and pneumatic inputs to detirmine manual fuel scheduling.

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13
Q

PCU

A

Propeller Control Unit

Controls Propeller Blade Angle by metering engine oil to one side of a double acting pitch change mechanism.

Receives mechanical inputs from Condition Levers for constant speed operation.

Receives mechanical inputs from Power Levers while in Beta Mode.

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14
Q

POG

A

Propeller Overspeed Governor

Provides Protection from Propeller Overspeed conditions.

In flight POG will dump fine pitch oil to drive prop towards feather, thereby reducing prop speed.

On ground POG will bleed P3 air from MFC, accomplishing a reduction in engine speed.

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15
Q

TRU

A

Transformer Rectifier Unit

Converts AC from 115 vAC Bus to 28v DC to power Secondary Buses.

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16
Q

BBPU

A

Bus Bar Protection Unit

Part of the DC Logic system that monitors Main DC Buses for potential bus faults.

Upon detecting a fault BBPU will automatically protect the DC electrical system from the fault.

17
Q

EADI

A

Enhanced Attitude Direction Indicator

Electronic Attitude Indicator and Single Cue Flight Director.

Receives pitch and roll inputs from associated AHRS. Graphics generated by associated Symbol Generator. Unit can be driven by other AHRS or Symbol Generator using reversionary modes.

18
Q

AHRS

A

Attitude Heading Reference System

Provides aircraft attitude and heading information to the EADI, EHSI, and RMI.

19
Q

SG

A

Symbol Generator

Combines inputsProvides graphical information to EADI.

20
Q

EHSI

A

Electronic Horizontal Situation Indicator

Receives heading information from the AHRS.

21
Q

ACM

A

Air Cycle Machine

Uses bleed air to provide air conditioning and pressurization.

22
Q

GCU

A

Generator Control Unit

Controls DC Starer / Generator units. One for each engine.

  1. Converts respective Starter / Gen from starer to gen mode during automatic start sequence at roughly 60% NH
  2. Monitors and regulates Starter / Gen’s voltage output to maintain a constant 28v output.
  3. Prohibits the DC electrical system by taking generator offline and isolating it in case of fault.
23
Q

RSOV

A

Rudder Shut Off Valve

Isolates the #2 Rudder Actuator and #2 SPU in case of major fluid loss in #2 hydraulic system, thereby providing rudder control.

18 psi Consumer

24
Q

ARPS

A

Alternate Rudder Power System

Consisting of #2 Standyby Hydraulic Pump, #2 Rudder Actuator, and RSOV, the system provides hydraulic power to the rudder in the event of major fluid loss in #2 hydraulic system.

25
Q

TCAS

A

Traffic Alert and Collision Avoidance System

Uses Mode C and Mode S readouts from nearby aircraft to provide Traffic Alerts (TA) and Resolution Advisories (RA)

26
Q

EGPWS

A

Enhanced Ground Proximity Warning System

Relies on a variety of aircraft parameter inputs and provides flight crew with aural alert messages and visual annunciations when any proximity envelope is exceeded.

27
Q

ADC

A

Air Data Computer

Receives input from Pitot / Static system, temperature probes and supplies information to systems on the aircraft.

28
Q

FMS

A

Flight Management System

29
Q

HGS

A

Heads-Up Guidance System

AKA HUD, or Heads Up Display

30
Q

RASU

A

Remote Airspeed Select Unit

Used to select desired target airspeed for HGS approaches.

31
Q

HCP

A

HGS Control Panel

Used to select:

  1. HGS Mode
  2. Runway Elevation for the approach
  3. Glideslope Angle for the approach
32
Q

SPU

A

2 SPU normally powered by left 115 vAC Bus. In case of left bus failure #2 SPU will automatically switch to right AC BUS and illuminate #2 SPU AUX PWR warning light.

Standby Power Unit

Another name for the Standby Hydraulic Pumps.

Powered by 115v variable AC.

33
Q

PTU

A

Power Transfer Unit

Assists in retracting the landing gear in the event of a #2 engine failure. Is triggered the the PSEU senses loss of #2 engine oil pressure coupled with a gear up command.

Consists of hyraulic motor driven by the #1 hydraulic system mechanically coupled to a hydraulic pump running the #2 hydraulic system.

Can be manually activated per E&A checklist to extend landing gear in event of #2 engine failure.

Q300 Notes (12 decks)

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