Flashcards in Flight Instruments Deck (11)
EFIS Data Sharing
The Avionics Standard Communications Bus allows data travel between the various computers of the aircraft. It is controlled by the AFCS computer.
The Private Line links the AHRU to the SGU in the event of ASCB failure.
The Video Bus distributes signals fro the SGU to the various CRTs in the system.
The Auto Flight Control System receives data from the two ADC, AHRS, SGU, the radio altimeter, the GNSS and from some sensors. It generates commands to the flight control actuators and to the FD bars. The AFCS is the ASCB controller too.
Attitude and Heading Reference Unit includes an Inertial measurement unit (INU) composed of three gyrometers and three accelerometers. The AHRU receives inputs from its associated flux valve and the TAS, fed by both ADC, is used to compute gyro erection and also sends attitude and heading signals to indicators, AFCS, Wx Radar, and FDAU. Vert. accuracy +/-1.4* Heading accuracy +/-2*
SGU 1- attitude and heading
FO RMI- heading
FDAU- attitude and heading
SGU2- attitude and heading
CA RMI- heading
Air Data Computers is supplied with static air pressure (static ports), total air pressure (pitot ports), total air temperature (TAT probe). With these inputs, the ADC computes pressure altitude, VS, IAS, TAS, TAT, SAT.
Symbols Generator Unit:
– collects all the data, coming
* from the ASCB (AFCS, AHRU, ADC)
* from navigation sources (VOR, ILS, DME, ADF, GNSS)
* from the remote controller (CRS, HDG)
– converts the data in video format, for the EFIS (EADI, EHSI)
– transfers the video data, from the weather radar or the EGPWS to the EHSI
AHRS and ILS systems are monitored by the SGUs an amber alert and EFIS COMP CCAS is generated for:
HDG- >6* and bank 12* and bank >6*
PIT- >6* pitch
ROL- >6* roll
ATT- both pitch and roll disagree
LOC- >0.6* localizer
GS- >0.2* glide slope
ILS- both loc and gs disagree
SGU FAILURE alert
A and B part failure and all information disappears from EADI and EHSI
the associated information immediatly disappear from both CRTs. ATT FAIL message is displayed
SGU FAILURE alert
C part failure and a red cross appears on EADI and EHSI
the associated information immediatly disappear from both CRTs. HDG FAIL message is displayed