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C.  Glide slope information is displayed by the glide slope pointers in the ADI and HSI. The pointers remain horizontal and move vertically across the glide slope scale to show airplane deviation about the glide path.
D.  Rotation of the remote course knob selects the desired VOR/LOC course and positions the HSI course arrow. At the time the course arrow is positioned, the selected course is also displayed in digital form on the course counter. The manual resolver and course select synchro are also positioned in accordance with the selected course. A signal from the resolver is fed to the manual VOR portion of the navigation unit, where after comparison in the phase detector, it is fed back as the VOR deviation signal to deflect the course deviation bar.
E.  The VOR/LOC and GS super flag signals control the respective ADI and HSI warning flags.
F.  A system self-test feature is controlled by the test switches on the VHF NAV control panel.
NOTE: If the autopilot is in a radio mode, VOR/ILS self-tests are inhibited.
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Oct 20/87  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-31-01 Page 7 

 

G.  For VOR test, a VOR station is tuned in and a course of zero degree 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 RDDMI pointer drives to 180 .3 degrees with respect to indicator compass card.

(4)  
HSI NAV flag and RDDMI narrow pointer flags retract from view after 3 seconds.

H.  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.
I.  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 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 retract from view after 3 seconds.
J.  Interface of the navigation systems is shown in Fig. 3. RF signals from the VOR/LOC, localizer, and glide slope antennas are fed to the nav receivers. The localizer antenna is selected through the ILS relays by mode logic in the AFCS accessory box. The logic requires that an ILS frequency be tuned; AFCS approach mode must be selected; and one of the following logics must be available: LOC arm; LOC engage; GS arm; or GS engage. Heading generated in the compass system is also sent from the compass couplers or RDDMI's to the VHF NAV receivers. 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 single (narrow) pointer in the RDDMI. Signals from nav receiver No. 1 also go to the autopilot, flight director, ground proximity warning and instrument warning systems. NAV receiver No. 2 and the first officer's ADI, HSI, and RDDMI 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 RDDMI receive 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.
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5C8 VOR/ILS Navigation System SchematicJun 20/85 Figure 3 (Sheet 1) 34-31-01Page 9/10 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

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5C8 VOR/ILS Navigation System SchematicFeb 20/86 Figure 3 (Sheet 2) 34-31-01Page 11/12 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

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5C8 VOR/ILS Navigation System SchematicFeb 20/86 Figure 3 (Sheet 3) 34-31-01Page 13/14 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

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5C8 VOR/ILS Navigation System SchematicFeb 20/86 Figure 3 (Sheet 4) 34-31-01Page 15/16 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

VOR/ILS NAVIGATION SYSTEM - TROUBLE SHOOTING
EFFECTIVITY
GJ B-2509 and B-2510

1. General
A.  The following trouble shooting procedures are based on performance of the system self-test using VOR/ILS navigation system 1. Trouble shooting system 2 can be accomplished using the same procedures with the substitution of first officer for captain and wide (No. 2) bearing pointer for narrow (No. 1) bearing pointer. The procedures are presented in tree-type format. The test steps are connected to show the OK condition path. When all steps in the OK condition path check out, the system is operable.
　
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