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FLIGHT INSTRUMENTS Description Vol. 2 11.10.52
Oct 05/06
Reversion L.PFD Failure Figure 11.10.45
R-PFD Failure
Turning the R DISPLAYS selector knob to MFD REV reverts the R.MFD to a PFD format, disables the radio tuning, and turns off the R.PFD. Maintenance and checklist functionality are also lost.
Reversion R.PFD Failure
Figure 11.10.46
FLIGHT INSTRUMENTS Description Vol. 2 11.10.53
Oct 05/06
DISPLAY REVERSION (CONT'D) MFD Display Reversion L-MFD Failure When the L-MFD fails, EICAS data is automatically presented on the R-MFD, and radio tuning is lost until PFD is reverted. Turning the L DISPLAYS selector knob to PFD REV reverts the L-PFD to a compressed format and turns off the L-MFD. The PFD includes a compressed EICAS page and a compressed PFD.
When compressed, the L-PFD can display a SUMMARY page (set via DCP FRMT pushbutton).
Reversion L.MFD Failure Figure 11.10.47
R-MFD Failure
When the R.MFD fails, radio tuning is lost until PFD is reverted.
Turning the R DISPLAYS selector knob to PFD REV reverts the R.PFD to a compressed format and turns off the R.MFD. The PFD includes a compressed EICAS page and a compressed PFD.
When compressed, the R.PFD can display a SUMMARY page (set via DCP FRMT pushbutton). Maintenance and checklist functionality are also lost.
FLIGHT INSTRUMENTS Description Vol. 2 11.10.54
Oct 05/06
Reversion R.MFD Failure
Figure 11.10.48
STANDBY FLIGHT INSTRUMENTS
Description
The standby flight instruments are comprised of a self.contained Thales model no. J42551AA LCD integrated standby instrument (ISI) and a standby compass.
The standby flight instruments are used as an alternative source of flight and navigation data, or as a cross.check to the electronic flight instrument system.
Integrated Standby Instrument (ISI)
The integrated standby instrument (ISI) replaces the 3 conventional standby flight instruments (ADI, altimeter and airspeed). In addition, the ISI provides the flight crew with:
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Slip/skid indicator;
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VMO/MMO indications
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MACH number;
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Barometric unit in inches and/or hectopascals;
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Altitude in feet and meters;
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ILS deviation scales; and
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Static source error correction (SSEC).
The ISI receives air data information from the standby pitot static system (P3 and S3). The ISI receives electrical power from the DC ESS BUS.
An internal inertial measurement unit measures the rotation speed and acceleration, in order to compute and display the attitude (pitch and roll).
FLIGHT INSTRUMENTS Description Vol. 2 11.10.55
Oct 05/06
An internal pressure measurement unit measures the total and static pressures, in order to compute and display the altitude and the airspeed, taking into account the static source error correction (SSEC) law tables.
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