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the HD6 mode. After capture, if the VHF navigation receiver, compass
data, or vertical gyro go invalid, the ADI command cue biases out of
view. The NAV CAP annunciator on the mode selector and NAV
annunciator on the ADI go out if the VHF navigation receiver becomes
invalid.
VOR Approach Mode
The VOR approach mode is selected by pressing the VOR APR switch/light
on the flight director mode selector with the VHF navigation receiver
tuned to a VOR frequency. The mode operates identically to the VOR
mode with gains optimized for VOR approach. The NAV and APR
annunciators on the ADI come on.
RNAV Mode
The RNAV mode is selected by pressing the NAV switch/light when the
RNAV deviation is supplied to the system. The RNAV approach mode is
selected by pressing the VOR APR switch/light as for the VOR approach
mode. Operation is similar to the VOR and VOR approach modes with
separate gains provided to optimize for the RNAV input. RN
annunciation on the HSI identifies the RNAV mode. Flight director
mode selector and ADI annunciations are the same as in the VOR modes.
Localizer Mode
The localizer mode is selected by pressing the NAV switch/light on the
flight director mode selector with the VHF navigation receiver tuned
to a LOC frequency. Mode selection and annunciation in the LOC mode
are the same as in the VOR mode except LOC is annunciated on the ADI.
The localizer deviation signal is gain programmed as a function of
radio altitude, time and airspeed. If the radio altimeter is invalid,
gain programming is a function of glideslope capture, time and
airspeed. Other valid logic is the same as the VOR mode.
Back Course Mode
The back course mode is selected by pressing the BC switch/light on
the flight director mode selector. Back course operates the same as
the LOC mode with the deviation and course signals reversed to make a
back course approach on the localizer. Glideslope capture is locked
out when in the BC mode. When BC is selected and outside the lateral
beam sensor trip point, BC ARM and HDG are annunciated on the mode
selector along with HDG on the ADI. At the capture point, BC CAP is
annunciated, BC ARM and HDG go out and BC is annunciated on the ADI.
SECTION 4
Page 33
Oct 03/83
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OPERATING MANUAL
(8) Localizer Approach Mode
The localizer approach mode is used to make an ILS approach. Pressing
the APR switch/light on the flight director mode selector with a LOC
frequency tuned on the VHF navigation receiver arms both the localizer
and glideslope modes. No alternate NAV source can be selected and the
receiver must be tuned to an ILS frequency. When the APR switch/light
is pressed and the above conditions are met, the NAV and APR modes are
armed to capture the localizer and glideslope respectively. Operating
the LOC mode is the same as described above. With the APR mode armed,
the pitch axis can be in any one of the other pitch modes except
go-around. When reaching the vertical beam sensor trip point, the
system automatically switches to the glideslope mode. The pitch mode
and APR ARM annunciators go off and the APR CAP annunciator comes on
along with GS on the ADI. At capture, a command is generated to
approach the glideslope beam. Capture can be made from above or below
the beam. The glideslope deviation is gain programmed as a function
of radio altitude, time and airspeed. The vertical speed signal is
used on the approach to improve glideslope tracking. The APR CAP
annunciator on the mode selector and GS annunciator on the ADI go out
if the GS receiver becomes invalid after capture. Glideslope capture
is interlocked so that the localizer must be captured prior to
glideslope capture. If the glideslope receiver is not valid prior to
capture, the vertical beam sensor does not trip and the system remains
in the pitch mode. After capture, if the glideslope receiver or
vertical gyro become invalid, the ADI command cue goes out of view.
(9) Pitch Hold Mode
Whenever a roll mode is selected without a pitch mode, ADI command cue
displays a pitch attitude hold command. The pitch attitude can be
changed by pressing the touch control steering (TCS) button on the
control wheel (refer to Figure 13) and manoeuvring the aircraft. The
ADI command cue is synchronized to fly-straight while the button is
pressed. Upon release of the button, the pitch command is such as to
maintain the new pitch attitude. In the pitch hold mode, the ADI
command cue goes out of view if the vertical gyro is not valid.
(10) Altitude Hold Mode
The altitude hold mode is selected by pressing the ALT switch/light on
　
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