Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов

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Page 2-9
Pilot’s Operating Manual
Revision A1: Nov, 2002
Sub-section 2
ENGINES
Hawker 800XP Pro Line 21
Section III - SYSTEMS DESCRIPTION
ENGINE INDICATING SYSTEM (EIS)
The EIS provides full time displays of engine Fan RPM N
1
, ITT and a part time, pop-up or
pilot-selectable display of engine RPM N
2
, fuel flow, oil pressure and oil temperature on the left MFD.
Fuel quantity for each wing tank and ventral tank status are normally displayed on the right MFD. The
EIS also displays alerts and warnings for operation outside normal limits.
The digital read-outs for the engine parameters and the pointers for N
1
and ITT will flash for 5 seconds
when they first turn yellow and stop flashing if they turn green (white for ITT) in less than the 5 second
time period. The digital read-outs and pointers will flash for 5 seconds when they first turn red, continue
to flash if they turn yellow within the 5 second period, but stop flashing if they turn green (white for ITT)
in that 5 second time period.
The part time engine parameters (N
2
, fuel flow, oil temperature, oil pressure and fuel temperature read-
outs and legends) are automatically displayed when an out of limit or engine miscompare condition
occurs.
The ENGINE button on the Display Control Panel (DCP) is used to manually control the display of the
part time engine parameters. The first push of the DCP ENGINE button removes the parameters,
provided that all read-outs are within normal operating limits. The last change by either pilot controls
the EIS on all currently enabled displays. Declutter is not allowed when an engine miscompare is active.
Two sources for N
1
, N
2
and ITT exist for each engine. One is the Data Concentrator Unit (DCU) and the
other is the Engine Data Concentrator (EDC). The left DCU is the priority source for the left engine, and
the right DCU is the priority source for the right engine with the cross-side DCU being the secondary
source.
The EDC is the third priority source with automatic selection between data sources being provided. The
DCU is the source for fuel flow, oil pressure, oil temperature and engine fire warning data. The DCU is
the interface between the avionics and the airplane subsystems. The primary function of the DCU is
acquisition, concentration, and transmittal of analog and discrete engine data. The EDC provides partial
control of the respective engine when it is ON (active). In the event of loss of either EDC data, the
current declutter state remains until manually changed or an out of limit condition automatically calls up
the parameters.
Engine information normally appears only on the Multi-Function Display (MFD). If display reversion
switching causes the MFD to become a Primary Flight Display (PFD), the engine information remains
displayed on that MFD (now a PFD). When display reversion switching shuts off the MFD display, then
the engine information shows on the on-side PFD.
L ft MFD E i Di l
Left MFD Engine Display