(e)
The captain's ND is located on the captain's instrument panel (P1). The first officer's ND is located on the first officer's instrument panel (P3).
(6)
Engine indicating and crew alerting system (EICAS) displays
(a) The EICAS displays are CRT's that provide displays for several electronic systems. Caution messages relating to the operation of the ILS are displayed on the main EICAS display. ILS status messages are displayed on the auxiliary EICAS display.
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(b) The main EICAS display is located on the pilots' center instrument panel (P2). The auxiliary EICAS display is located on the forward electronic control panel (P9).
(7) EICAS display select panel
(a)
The STAT button on the EICAS display select panel is used to select the screen on the auxiliary EICAS display that contains the status messages.
(b)
The EICAS display select panel is located to the left of the first officer's EFIS control panel on the pilots' lightshield.
D. Standby Attitude/ILS System
(1)
The components of the standby attitude/ILS system that interface with the ILS are the:
(a)
Static inverter/ILS processor
(b)
Standby attitude/ILS indicator
(2)
Static inverter/ILS processor
(a)
The static inverter/ILS processor accepts ILS digital data from the left ILS receiver and converts it to analog to drive the deviation pointers and flags on the standby attitude/ILS indicator.
(b)
The static inverter/ILS processor is located in the E1 electronics equipment rack in the main equipment center. It is located on the No. 3 shelf.
(3)
Standby attitude/ILS indicator
(a)
The standby attitude/ILS indicator displays lateral (localizer) and glide path (glide slope) deviation data provided by the left ILS. Deviation is indicated by the intersection of the two deviation pointers.
(b)
The APP switch is used to select the normal ILS approach display on the indicator when in the APP position. For display during a back course approach, turn the APP switch to B/CRS.
(c)
If an NCD condition exists in either channel, the affected pointer is removed from view. If an invalid data condition exists in either channel, the affected pointer is removed from view and the LAT or G/P flag is driven into view.
(d)
The standby attitude/ILS indicator is located on the pilots' center instrument panel (P2).
E. Ground Proximity Warning System (GPWS)
(1)
The component of the GPWS that interfaces with the left ILS is the ground proximity warning computer.
(2)
Ground proximity warning computer (GPWC)
(a) The ground proximity warning computer accepts glide slope deviation, localizer deviation, ILS mode, and ILS valid data from the ILS navigation system. Glide slope deviation and valid data are used for computation of modes 2 and 5. Localizer deviation and valid data are used for computations of envelope modulation. The ILS mode data enables the G/S warning operation in the GPWC. The ILS valid data ensures the GPWC that the ILS navigation system operation is normal.
F. Flight Management Computer System (FMCS)
(1) Components of the FMCS that interface with the ILS are the:
(a) Control display unit
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(b) FMC select switch
(2)
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