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(2) Verify VOR/ILS switching interlocks and flag operation per following table:
NOTE: Blank spaces in table indicate NAV and GS flags are out of
____ view and the system is receiving a valid ILS signal.
(3) On XA ALL EXCEPT AT Airplanes, verify VOR/ILS switching interlocks and flag operation per following table:
NOTE: Blank spaces in table indicate NAV and GS flags are out of
____ view and the system is receiving a valid ILS signal.
SWITCH/POSITION INDICATOR/FLAG IN VIEW CONDITION
VOR/ILS ADI CAPT HSI ADI F/OHSI ILS TEST SIGNALAPPLIED TO SYSTEM
CAPT 1 F/O 2 1, 2 and 3
CAPT 3 F/O 2 1, 2 and 3
CAPT 1 F/O 3 1, 2 and 3
CAPT 1 R F/O 2 WY,GS NAV,GS 2 and 3
CAPT 3 F/O 2 2 and 3
CAPT 1 F/O 2 RWY,GS NAV,GS 1 and 3
CAPT 1 F/O 3 1 and 3
(4) On AT ALL,
verify VOR/ILS switching interlocks and flag operation per following table:
NOTE: Blank spaces in table indicate NAV and GS flags are out of
____ view and the system is receiving a valid ILS signal.
EFFECTIVITY
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SWITCH/POSITION INDICATOR/FLAG IN VIEW CONDITION
CAPT F/O
VOR/ILS 3 DEV CAPT F/O ADI HSI ADI HSI ILS TEST SIGNALAPPLIED TO SYSTEM
NORM NORM CAPT 3 NORM NORM NORM NORM NORM NORM R WY,GS NAV,GS 1, 2 and 32 and 32 and 3
NORM NORM NORM F/O NORM ON F/O NORM ON F/O ON CAPT NORM NORM 3 NORM NORM NORM ON CAPT RWY,GS NAV NAV,GS 2 and 32 and 31 and 31 and 31 and 3
NORM NORM ON F/O ON CAPT NORM NORM NAV 1 and 31, 2 and 3
J. Glide Slope Antenna Coaxial Relay Test (AF 115-151 AND AF 157, 161, 183, 184 WITHOUT SB 34-2264)
(1)
The following tests provide two methods for testing the nose gear door glide slope capture and track antenna switching circuits. Either or both tests may be used to check operation of the glide slope antenna coaxial relays. The relays are normally de-energized with the landing gear down to connect the glide slope track antennas to the VOR/ILS receivers. Both tests energize the relays to connect the glide slope capture antennas to the VOR/ILS receivers using different methods.
(2)
Test No. 1 energizes the relays by disconnecting and grounding pin 35 of connector DM93 for relay No. 1 and pin 36 of connector DM809 for relay No. 2. This bypasses the gear-up logic circuits in the primary and alternate landing gear logic units.
(3)
Test No. 2 uses a ferrite bar to target the gear-up and locked proximity switches S397 (primary) and S424 (alternate) on the nose landing gear strut to switch the landing gear logic units to the gear-up mode and energize the relays.
(4)
Relay Test No. 1
(a)
Disconnect glide slope track antenna cables DB554B and DB555B from glide slope antenna hybrids on panels P31 and P32.
(b)
Tune VOR/ILS navigation system to ILS frequency of 108.10 MHz. Check that ADI and HSI glide slope flags and pointers are in view.
(c)
Operate signal generator to provide a maximum ON-COURSE glide slope test signal at 334.70 MHz.
(d)
De-energize primary and alternate landing gear logic units (Ref 32-61-00).
(e)
Open GS 1 and GS 2 circuit breakers on P7.
(f)
Disconnect electrical connectors DM93 and DM809 from primary and alternate landing gear logic units.
(g)
Ground pin 35 of DM93 and pin 36 of DM809.
EFFECTIVITY
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(h)
Close GS 1 and GS 2 circuit breakers on P7. Check that ADI and HSI glide slope flags disappear and that glide slope pointers are centered.
(i)
Reduce glide slope test signal level until ADI and HSI glide slope flags appear.
(j)
Increase glide slope test signal to a level just above ADI and HSI glide slope flag retraction.
(k) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航2(31)
