GE-CF6-80E1-69

Prévia do material em texto

A330 - ENGINE ATA 71 up 80
GE CF6-80E1 137 of 394
 
 
 
 
 
 
 
 
 
 
 
ECU INTERFACES
The ECU receives: 
 Aeronautical Radio Incorporated (ARINC) 429 digital data bus inputs 
 analog and discrete inputs.
The ECU provides: 
 ARINC 429 digital data bus outputs 
 analog and discrete outputs.
ECU ARINC 429 digital data bus input
Each channel of the ECU has input ports for two Air Data and Inertial
Reference Units (ADIRU) (Ref. 34 12 00) and one Engine Interface and
Vibration Monitoring Unit (EIVMU).
ADIRU/ECU
Each ADIRU ARINC 429 bus is wired to one channel of the ECU and
crosswired internally to the other channel. Each ECU channel receives digital
data buses from two ADIRUs which provide: 
 corrected static pressure signals (PS) 
 total air temperature signals (TAT)
 total air pressure signals (PT) 
 one discrete word from the aircraft. 
In addition, the ECU has dedicated sensors that provide a complete
complement to the ADIRU sensors. This provides the capability to detect,
isolate and accommodate failures of these signals through validation and
selection logic.
The following ECU sensors are of the dual element type (one element per
channel):
 ambient pressure sensor (PO) 
 total temperature probe (T12) 
 air inlet pressure sensor (PS12). 
One ARINC 429 output bus of each ADIRU is dedicated to one engine control
only.
EIVMU/ECU
The EIVMU interfaces with various aircraft computers and with the associated
propulsion system control to perform the following main functions: 
 transmission of cockpit panel and aircraft computer data to the associated
engine control
 internal processing of some airframe status signals needed by the engine
control systems
 control of airframe power supplies to the engine control system
 engine to engine segregation.
The EIVMU is wired directly to the ECU through an ARINC 429 digital bus and
crosswired internally to both channels. 
The following categories of aircraft data are transmitted by the EIVMU to the
ECU:
 general aircraft data 
 idle setting data 
 engine starting data 
 autothrust function data 
 maintenance function data.
ECU analog and discrete inputs
The analog signal input from the aircraft to the ECU is the Throttle Resolver
Angle (TRA).
Discrete inputs from the aircraft to the ECU include: 
 engine position discretes 
 ENG/MASTER switch 
 autothrust engagement and disconnect 
 alternate start/ignition command.
The local engine discrete inputs establish configuration information from two
programmed plugs that include:
 the engine family and rating 
 the engine serial number (S/N) 
 engine oil pressure transmitter type (KULITE or ARMTEC) 
 the bump selection status 
 the Propulsion Multiplexer (PMUX) inhibit 
 the N1 trim 
 chip detector inhibit.
The aircraft also provides interfaces with the cockpit ENG/MASTER switch.
These include the High Pressure Shut Off Valve (HPSOV) solenoid and the
ENG/MASTER switch/Reset discrete.
A330 - ENGINE ATA 71 up 80
GE CF6-80E1 138 of 394