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W The autopilothasbeendisengaged
W The airplane’s approach relative to airspeed,localizer andglideslopedeviation and crosstrack rate, verticalspeed,lateralandlongitudinalposition
W For possible unsafelandingsby evaluating the sink rate,lateraldisplacementfrom runway centerline,airspeed relative toselectedairspeed, crosstrack rate, rollangle, anddistance traveled alongthe runway.
H. System Test/Fault Codes
The HGScontinuouslychecksits operationalstatusandif afaultis detectedthesystem willblankthe CRT andthe combiner. EICAS andthe PFDswilldisplayapplicable HGS failure /approach warning messages. TheHGS controlpanelFAULTlampwill come on,theHGS controlpanelLEDunitwilldisplay an applicable fault code.
I. HGS Mode Selections/Indications
The HGS controlpanelis usedtoenterrunwayandglideslopedata,to accomplish testingtroubleshooting,to selectHGS modesandtodisplaythe modein use. Modes are indicated on the controlpanel asfollows:
W The CRTline adjacenttotheACTkeyindicatesthe current active mode
W The CRTline adjacenttotheSTBYkeyindicatesthe next available /next selectable mode
W The CRTline to thefar right sideoftheSTBYkeyindicatesHGS capability(AIII, AII,AI).
The flight mode annunciator area oftheHGS combiner andthePFDs willecho the correspondingHGS mode.
Flight Crew Operating Manual MASTER
CSP A-
013
FLIGHT INSTRUMENTS Head-
Up Guidance System Vol. 1 12-
70-
20
REV 56, Jan 31/03
<0039>
<0039> headupguidance system failure.
HGSSystem ---EICASMessages <MST> Figure 12 ---70 ---7
Flight Crew Operating Manual MASTER
CSP A-
013
FLIGHT INSTRUMENTS Vol. 1 12-
70-
21
Head-
Up Guidance System REV 56, Jan 31/03
Example: DH100
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