GE-CF6-80E1-68

Prévia do material em texto

FMGEC‘S/FCU
ADIRU (2)
T25 (2x)
N1 (2x)
N2 (2x)
T12 (2x)
PS3 (2x)
T49 (1x)
T3 (2x)
FF (2x)
TEO (2x)
PS14 (2x)
P25 (2x)
T5 (1x)
P49 (2x)
REVERSER POSITION (2x)
CONTROL ALTERNATOR (2x)
HARDWIRE SIGNALS(28 VDC / 115 VAC)
A
C
M
S
C
C
D
L
ABBREVIATIONS :
ACMS = AIRCRAFT CONDITION MONITORING SYSTEM
CCDL = CROSS CHANNEL DATA LINK
HMU
VSV
VBV
HPTCC
LPTCC
FUEL METERING
IGNITION
STARTING
CCCS
BCS
CCCS = CORE COMPARTMENT COOLING SYSTEM
INDICATION
ECU
TWO SINGLE LVDT FEEDBACK
TWO SINGLE LVDT FEEDBACK
TWO SINGLE FMV RESOLVER FEEDBACK
ONE DUAL LVDT FEEDBACK
ONE DUAL LVDT FEEDBACK
ECAM
HMU = HYDRO MECHANICAL UNIT
FMGEC = FLIGHT MANAGEMENT GUIDANCE ENVELOPE COMP
FCU = FLIGHT CONTROL UNIT
ADIRU = AIR DATA INERTIAL REFERENCE UNIT
ECU = ENGINE (ELECTRONIC) CONTROL UNIT
NOTE:
THE ECU CONTROLS SYSTEMS EITHER WITH CH A OR CH B
WICHEVER IS THE CHANNEL IN COMMAND.
VSV
VBV
ECU CH B
ECU CH A
EACH ECU CHANNEL HAS ITS OWN SET OF SENSORS & FEED-
BACKS. EXCEPT T49 AND T5.
PO (2x)
BCS = BORE COOLING SYSTEM
Ps12 (2x)
T-FUEL (1x)
REVERSER
7
A330 - ENGINE ATA 71 up 80
GE CF6-80E1 135 of 394
 
 
 
 
 
 
 
 
 
 
 
ECU ARINC 429 digital data bus output
 The ECU transmits to the aircraft computers, on four ARINC 429 buses (two
per channel A1 A2 B1 B2), the propulsion system status information.
Information contained on ECU output buses includes the following general
items:
 engine rating parameter information 
 parameters used for engine control 
 FADEC system maintenance data 
 engine condition monitoring parameters 
 ECU status and fault information 
 propulsion system status and fault information.
The ECU ARINC 429 bus outputs are received by the following aircraft
computers:
 EIVMU 
 Flight Warning Computers (FWC) 
 Display Management Computers (DMC) 
 Flight Management Guidance and Envelope Computer (FMGEC).
The EIVMU uses FADEC system data for the following functions:
 aircraft systems logic use 
 transmission of ECU ARINC data to the Data Management Unit (DMU).
The DMCs and the FWCs use FADEC system data for engine parameter
displays and engine fault warning messages respectively.
ECU analog outputs
The ECU provides analog output (power supply) signals to the throttle control
unit.
ECU discrete outputs
Each ECU (both channels) sends one ”engine running” signal (N2 > 50%) to:
 Hydraulic System Monitoring Unit (HSMU) for automatic Ram Air Turbine
(RAT) extension and automatic electrical pump activation
 flight control system for surface deflection speed limitation in case of RAT
extension
 electrical shedding logics.
Each signal is monitored by the corresponding EIVMU.
A330 - ENGINE ATA 71 up 80
GE CF6-80E1 136 of 394