C5 Dash 8 Component Acronyms Flashcards
RGB
Reduction Gear Box
Reduces high RPM of Power Turbine to lower RPM of the Propeller
Driven off the RGB are:
- Hydraulic Pump
- AC Generator
- Propeller Control Unit
- Propeller Overspeed Governor
PSEU
Proximity Sensor Electronics Unit
- Sequences gear and doors during gear movement
- Controls gear and door advisory lights
- Activates Warning Horn
- Routes inputs into other non-gear systems.
WOW
Weight on Wheels Switch
Feeds into multiple systems
HPSOV
High Pressure Shut Off Valve
Controls High Pressure Bleed Air
- HPSOV will on close on the ground at pressures above 65 psi.
- In flight HPSOV will remained closed above 55 psi.
- Activation of Deice Boots opens HPSOV in flight.
NSOV
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.
HBOV
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.
ECU
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.
- Refines the manual fuel scheduling of the MFC
- Controls NP Underspeed Governing
- Controls HBOV
- Provides Power Uptrim
PROV
Pressure Regulator Valve
(-200 Only)
Regulates Bleed Air Pressure to ACM.
18 psi Consumer
PRSOV
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
APU
Auxiliary Power Unit
(-300 only)
Provides Bleed Air to AC Packs and 28v DC Power to Right Main Bus.
ESU
Electronic Sequence Unit
(-300 only)
Provides automatic control of APU operation. Controlled by APU Control Panel
MFC
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.
PCU
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.
POG
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.
TRU
Transformer Rectifier Unit
Converts AC from 115 vAC Bus to 28v DC to power Secondary Buses.
BBPU
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.
EADI
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.
AHRS
Attitude Heading Reference System
Provides aircraft attitude and heading information to the EADI, EHSI, and RMI.
SG
Symbol Generator
Combines inputsProvides graphical information to EADI.
EHSI
Electronic Horizontal Situation Indicator
Receives heading information from the AHRS.
ACM
Air Cycle Machine
Uses bleed air to provide air conditioning and pressurization.
GCU
Generator Control Unit
Controls DC Starer / Generator units. One for each engine.
- Converts respective Starter / Gen from starer to gen mode during automatic start sequence at roughly 60% NH
- Monitors and regulates Starter / Gen’s voltage output to maintain a constant 28v output.
- Prohibits the DC electrical system by taking generator offline and isolating it in case of fault.
RSOV
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
ARPS
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.
TCAS
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)
EGPWS
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.
ADC
Air Data Computer
Receives input from Pitot / Static system, temperature probes and supplies information to systems on the aircraft.
FMS
Flight Management System
HGS
Heads-Up Guidance System
AKA HUD, or Heads Up Display
RASU
Remote Airspeed Select Unit
Used to select desired target airspeed for HGS approaches.
HCP
HGS Control Panel
Used to select:
- HGS Mode
- Runway Elevation for the approach
- Glideslope Angle for the approach
SPU
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.
PTU
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.
