Hawker 800 XP, Руководство по подготовке пилотов

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When the mode captures, “VASL” in green
will be displayed on the EADI vertical capture
location. The mode annunciation will flash
for 5 seconds emphasizing the transition from
arm to capture.
VALT (Altitude Hold)
VALT will operate identically to ALT mode.
VALT will engage automatically after VASL
has captured the target altitude. VALT will
also engage whenever VNAV pushbutton is
pushed and the aircraft is within 250 feet of
the FMS target altitude. The FMS ALT mode
is annunciated on the EADI by a green "VALT"
at the vertical capture location.
VPTH (Vertical Path Mode)
VPTH mode is used to fly a fixed flight path
angle to a vertical waypoint during descent.
VPTH mode will engage whenever FMS ini-
tiates a path descent which may occur while
in VFLC or VALT modes. When the mode
captures, "VPTH" in green is annunciated on
the EADI at the vertical capture location. The
mode annunciation will flash for 5 seconds to
emphasize this transition.
MONITORS
AFCS Failure Monitors
The AFCS incorporates monitors which assess
the validity of the computer and other system
components. These monitors are in addition
to those monitors which provide fail-passive
and failoperational operation described below.
The power supply, the micro-processors, and
other hardware within the system are moni-
tored for availability. If a failure is detected
the system is rendered inoperative.
Upon application of electrical power to the
system the AFCS goes through a power-up
pre-flight test. The “L FAIL” annunciator is
on during the test. Upon successful comple-
tion of the test by both computers, the “L
FA I L ” a n n u n c i a t o r t u r n s o ff a n d t h e “ L
AFCS” annunciator turns on. If a failure is de-
tected in either flight guidance computer the
appropriate “L (R) FAIL” annunciator latches
on.
A failure within the flight guidance computer
which prevents operation of the flight direc-
tor function will result in a red “FD” flag on
the EADI.
AFCS Performance Monitors
The AFCS, also, incorporates monitors within
hardware and software that ensure the safety
of the system. These monitors provide the
fail-passive and fail-operational capability of
the system. It is beyond the scope of this doc-
ument to describe these monitors in detail,
but the following list identifies the monitor
functions and the resultant annunciation.
Servo Monitors
The servo control loops are monitored to de-
tect failures of the servo amplifiers, loss of
feedback, or existence of an uncommanded
output. If the monitors detect a failure condi-
tion within the priority computer the computer
will be shut down and the remaining computer
will continue operation. Assuming that the
left computer is active (engaged), the amber “L
FAIL” annunciator turns on. This is followed
by a green “R AFCS” annunciation to indi-
cate that the right side computer is now active.
NOTE
In the event of a nuisance monitor
trip within the priority computer, the
control will be transferred to the re-
maining computer and the down com-
puter will perform an automatic reset.
If the down computer is successful in
resetting itself, no fail annunciation
will be displayed. The down com-
puter will not try to reset itself if the
AFCS is in the capture or track phase
of LOC, BC, VAPP or GA.
16A-10
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP PILOT TRAINING MANUAL
FlightSafety
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