E. Selecting an ILS frequency enables the ADI and HSI localizer and glide slope displays for making an instrument landing approach.
F. Localizer deviation is displayed by the ADI runway symbol and the HSI course deviation bar which move laterally across a scale to show airplane deviation from the localizer beam.
G. Glide slope information is displayed by the glide slope pointers in the ADI and HSI. The pointers remain horizontal and move vertically across the scale to show airplane deviation about the glide path.
H. When the system is tuned to a VOR frequency, the ADI and HSI glide slope flags and pointers and the ADI runway flag and symbol are biased out-of-view.
I. The VOR/LOC super flag signals control the respective ADI RUNWAY and HSI NAV warning flags.
J. The glide slope super flag signals control the respective ADI and HSI GS warning flags.
K. A system self-test feature is controlled by test switches on the VHF NAV control panel.
L. For VOR test, a VOR station is tuned in and a course of zero degrees is selected. When the VOR self-test is actuated, test displays on the associated instruments are as follows:
(1)
HSI course deviation bar centered
(2)
HSI to/from pointer indicates from
(3)
Associated RMI pointer drives to 180 degrees with respect to indicator lubber line.
(4)
HSI NAV flag remains in view for 3 seconds depending on the RMI pointer slew time, retracts from view and 25士5 seconds after initiating VOR self-test, flag reappears and remains in view as long as the VOR test pushbutton is held depressed.
M. If during the VOR self-test, the HSI course arrow is positioned 5 degrees on either side of the selected course, the course deviation bar will deflect to the appropriate first dot position on the course deviation scale.
N. For an ILS self-test, an ILS frequency is selected on the VHF nav control panel and either the up/left or the down/right self-test is actuated in turn. Selecting either an up/left or a down/right ILS self-test causes the ADI and HSI glide slope pointers to deflect up or down and the ADI runway symbol and the HSI course deviation bar to deflect left or right. The HSI NAV and GS flags and the ADI RUNWAY and GS flags will remain in view for 3 seconds, disappear, and 20 士5 seconds after initiating test, reappear and remain in view.
NOTE: 1. On GJ ALL EXCEPT B-2504, B-2505 AND B-2524, if the autopilot is in a radio mode and as VOR/ILS self-test is performed, the autopilot mode selector will switch to the manual mode.
2. On GJ B-2504, B02505 and B-2524, if the autopilot is in a radio mode, VOR/ILS self-tests are inhibited.
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34-31-0 Page 8 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/89
O. Interface of the navigation systems is shown in Fig. 3. RF signals from the VOR or GS antenna are fed to their respective nav receivers. Heading generated in the compass system is also sent from the RMI's to the NAV receiver. Using these signal inputs, the receiver processes the signals used by the navigation system. With the navigation transfer switch in NORMAL position, the signal output of nav receiver No. 1 controls the warning flags and GS and course deviation displays in the captain's ADI and HSI, and the signal (narrow) pointer in the RMI. Signals from nav receiver No. 1 also go to the autopilot, flight director computer, ground proximity warning system computer, and to the nav warning comparator. NAV receiver No. 2 and the first officer's ADI, HSI, and RMI operate in a similar manner. When the navigation transfer switch is in BOTH ON 2 position, the captain's and the first officer's ADI, HSI, and RMI receiver their inputs from nav receiver No. 2. When the nav transfer switch is in BOTH ON 1 position all instruments indicate nav receiver No. 1 outputs. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737 AMM 飞机维护手册 导航 NAVIGATION 2(15)
