R. MONITORING OF THE RELEVANT DISPLAY OF THE ENGINE PARAMETERS A safety mechanism is implemented in the EIS to monitor the engine parameters N1, N2, EGT and FF (fuel flow) indications of both engines.The EIS compares the displayed digital/analog value with the signal received from the ECU's. In case of detected discrepancy, a CHECK amber message (flashes 9s then remains steady) is displayed on the PFD, above the attitude zone and on the EWD above the FOB indication. In addition the FWC's perform an external monitoring between the feedback signals (that correspond to the displayed values) and the signals that are directly received by the FWC's from the ECU's. Should a discrepancy occurs, for one or more parameters, the FWC's generate a caution:
-single chime
-master caution light
-message on the upper ECAM DU : ENG1(2) N1(N2/EGT/FF) DISCREPANCY
S. System Feedback Message The safety mechanism implemented in the EIS, also monitor the critical parameters displayed on every image. When a discrepancy between the signal sent by the sensors and the data actually displayed, an amber message is displayed on the EWD depending on the image which is monitored. It flashes 9s then remains steady (the display of these messages is also feddbacked): On the first line:
-
CHECK CAPT PFD
-
CHECK F/O PFD On the second line:
-
CHECK CAPT ND
-
CHECK F/O ND
-
CHECK SD
(Ref. Fig. 008)
Also when the software standard of an item of equipment, part of the EIS
does not match the other items a system message is displayed at the same
place:
DISPLAY SYSTEM VERSION INCONSISTENCY (amber)
And, when the DU is no more monitored the following message is displayed:
DU NOT MONITORED (amber). All these messages flash for 9s then are
steady.
R 1EFF : 106-149, 303-399, 401-499, 1 31-66-00Page 19 1 1 Aug 01/05 1 1 1CES 1 **ON A/C ALL
NOTE : (1): The processing of the engine 1 and 2 input parameters is
____ independent. (2): The values of the N1, N2, EGT red lines and transitory overlimit values are stored in 2 independent tables, one for each engine type. The same applies for the advisory thresholds as regards to the oil pressure, temperature, quantity. The N1, N2, EGT red lines and transitory overlimit values are sent to the FWCs through the DMC general high speed output bus.
R **ON A/C 106-149, 303-399, 401-499,
(1) Switching test In maintenance mode a magenta EWD1 (2 or 3) message appears above the warning mode. It shows the digital link between the DMC and the DU is valid. (Ref. Fig. 008)
**ON A/C ALL
6. Fuel on Board Information
_________________________
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302,
An indication located below the N1 LIM MODE gives the fuel on board information.
R **ON A/C 106-149, 303-399, 401-499,
An indication located above the WARNING/MEMO area gives the fuel on board information.
**ON A/C ALL
This information is in KG. In case of degraded data the two less significant digits are displayed with two dashes across. When the fuel quantity is not fully usable (for example in case of a transfer valve failure), a half amber box is displayed surrounding the FOB indication.
1EFF : ALL 1 31-66-00Page 20 1 1 Aug 01/05 1 1 1CES 1R **ON A/C 106-149, 303-399, 401-499,
(Ref. Fig. 011)
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302,
(Ref. Fig. 012)
**ON A/C ALL
7. Engine types
____________
**ON A/C 001-049, 051-099, 101-149, 201-299,
Tables, one for each engine, containing the critical thresholds of engine parameters are stored in memory. The table used by the DMC and corresponding to the type of engine installed on the aircraft is selected through pin programming on the DMC according to the following table (for CFM engines):
------------------------------------------------------------------------------| | DMC MP connector program pin | | ENGINE |---------------------------------------------------| | | D5 | E5 | D8 | G5 | | | Eng type 0 | Eng type 1 | A/C type | Eng type 2 | ------------------------------------------------------------------------------| CFM 56-5A1 | 1 | 0 | 0 | 1 | |------------------------|------------|------------|------------|------------| | CFM 56-5B4 | 1 | 1 | 0 | 1 |
1 = GROUND, 0 = OPEN
R **ON A/C 151-199, 401-499,
Tables, one for each engine, containing the critical thresholds of engine parameters are stored in memory. The table used by the DMC and corresponding to the type of engine installed on the aircraft is selected through pin programming on the DMC according to the following table (for CFM engines):
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