Honeywell SPZ-8000 - Engine Instruments Failure Indications

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2. E. (4) Engine Instruments Failure Indications
(a)
(b)
(c)
(d)
(e)
(f)
Data Acquisition Unit (DAU) Failure -
A DAU failure is
indicated on the primary engine display by removing the data
pointers from all the arc displays. Additionally, the current
value digits are replaced with amber dashes. The failure
indication on the secondary engine display consists of
replacing the digital readout with amber dashes.
Figure 227
shows the indication
for a single DAU (No. 1) channel failure.
Engine Sensor/Interface Failure - The failure indication of a
particular
sensor or interface is a subset of the DAU failure
previously discussed.
The difference is that the failure
indication is shown only on the affected parameter as
appropriate (Figure 227).
Display Controller Failure -
In the event of a dual display
controller failure, EPR mode annunciations and command/limit
bugs are removed from the EPR scale and the EPR target digital
readout is replaced with amber dashes (Figure 227).
Bus Controller Failures
- In
the event the three bus
controllers fail the indication given would be that of a dual
display controller failure and a dual DAU failure as previously
discussed.
FMS Failure - Failure of the PFD commanded FMS-PZ causes the
command bug to be removed from the display with the
corresponding digital readout replaced with amber dashes.
FMS
calculated limit tickmark and mode annunciations are also
removed from the display.
EICAS Self-Test -
This test is initiated through either display
controller TEST mode when airspeed is valid and less than 60
knots and the WOW switch is active.
Selecting the EICAS self-
test gives the following indications on the engine display:
● DAU lA-lB Failure
Indication
. DAU 2A-2B Over-Range
- TGT
- LP
- HP
- Oil Temperature
- Engine Fuel Temperature
. Fuel Quantity Low Indication
. A/I, IGN, and SVO Annunciations
The above indications are also given on the system pages (refer
to paragraph 2.G.) as appropriate.
22-14-00
Page 275
Aug 15/91
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