(c)
Modulated rf test signals, generated by the self-test oscillators, are applied to the input of the VHF and UHF receiver sections to simulate a VOR signal on any VOR channel or localizer and glide slope signals on any ILS channel. These signals provide an overall operational test for the VOR/ILS navigation system.
(d)
Prior to self-test initiation control logic will allow normal operation of the GS and VOR/LOC flags. When self-test is initiated the GS and VOR/LOC flags will be driven out of view and remain out of view through completion of test. There is a 3-second delay on flag action for an ILS self-test and up to a 5-second delay for VOR self-test.
(3)
KING RADIO KNR 6030 Receiver
EFFECTIVITY AZ ALL AT ALL
IB ALL CONFIG 2 SN ALL 01 Page 19 Apr 25/86
34-31-00
(a)
The self-test operation is initiated on the VHF NAV control panel or at the VOR/ILS receiver front panel and provides a checkout of both the VOR/ILS receiver and the VOR/ILS displays in the flight instruments. Deviation signals and flags are both tested. Execution of either the VOR or the ILS self-test is dependent upon the frequency selected upon the control panel. The self-test is inhibited when the AFCS is operating in VOR/LOC, ILS or LAND mode with channel A, B or C in command.
(b)
When a self-test is initiated, either a VOR or ILS test sequence will take place according to the frequency selected on the control panel. All flag outputs come on for 3 |1 seconds, go off for 24 |6 seconds, come back on and remain on until the test switch is released. The timing of the flags during the self-test ensure that the delay circuits are operating properly. The self-test light located just above the self-test switch allows the flag sequence to be monitored at the VOR/ILS receiver. The light comes on to indicate that the flags should be out of view at the flight instruments. Its sequence is off for 3 |1 seconds, on for 24 |6 seconds, and then off.
(c)
The VHF and UHF synthesizers disable the LOs during self-test and are used to inject test frequencies into the VHF and UHF receivers. The test frequencies result in a 180. VOR deviation signal within 10 seconds as viewed on the RMI. The GS deviation and the LOC deviation test frequencies will either result in a one dot up and one dot left, or a one dot down and one dot right deflection as viewed on the ADI and HSI (according to the position of the self-test switch).
E. Control
(1) Turn-On Procedure (Fig. 3)
(a) Provide electrical power to system (Ref 24-22-00).
CAUTION: MAKE SURE THAT THE EQUIPMENT COOLING SYSTEM IS
_______ OPERATING BEFORE TURN-ON OF THE ELECTRICAL OR ELECTRONIC SYSTEMS OR HEAT DAMAGE COULD RESULT. REFER TO 21-58-00, EQUIPMENT COOLING SYSTEM -ADJUSTMENT/TEST.
(b) On XA ALL EXCEPT AT airplanes, check that the following circuit breakers on electronics circuit breaker panel P7 are closed: ADF RMI 1, ADF RMI 2, ALT ADF RMI 1, ALT ADF RMI 2, ALT VOR RMI 1, ALT VOR RMI 2, ATT ADI 1, ATT ADI 2, GS 1, GS 2, HDG SYNC EXCIT 1, HDG SYNC EXCIT 2, HDG SYNC EXCIT 3, HSI-1, HSI-2, MHRS 1, MHRS 2, VOR 1 AC, VOR 1 DC, VOR 2 AC, VOR 2 DC, VOR RMI 1, VOR RMI 2, CAPT FLT INST SW RELAYS and F/O FLT INST SW RELAYS. On SN 351-399 and IB 406-499,
EFFECTIVITY
AZ ALL
AT ALL
IB ALL CONFIG 2 SN ALL 02 Page 20 Apr 25/86
34-31-00
check that VHF NAV CONT-1 and VHF NAV CONT-2 circuit breakers on panel P7 are closed.
(c)
On AZ 221-234, 281 and IB 406-499 prior to incorporation of SB 34-2261, on overhead lightplate circuit breaker panel P126, check that ALT ADI 1, ALT ADI 2, ALT HSI 1, ALT HSI 2, GS 3, VOR 3, CAPT ILS BUFFER and F/O ILS BUFFER circuit breakers are closed.
(d)
On AZ 235-280, 282-299 and SN 351-399, plus AZ and IB airplanes incorporating SB 34-2261, On overhead lightplate circuit breaker panel P126, check that ALT ADI 1, ALT ADI 2, ALT HSI 1, ALT HSI 2, GS 3, VOR 3 AC, VOR 3 DC, CAPT ILS BUFFER and F/O ILS BUFFER circuit breakers are closed.
(e)
On AT ALL, check that the following circuit breakers on electronics circuit breaker panel P7 are closed: ATT ADI 1, ATT ADI 2, CAPT FLT INST SW RELAYS, F/O FLT INST SW RELAYS, GS 1, GS 2, HDG SYNC EXCIT 1, HDG SYNC EXCIT 2, HDG SYNC EXCIT 3, HSI 1, HSI 2, ALT A HSI 1, ALT A HSI 2, MHRS 1, MHRS 2, VOR RMI 1, VOR RMI 2, ALT VOR RMI 1, ALT VOR RMI 2, VOR 1 AC, VOR 2 AC, VOR 1 DC, VOR 2 DC, CAPT ILS BUFFER 2, F/O ILS BUFFER 2.
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本文鏈接地址：747飛機(jī)維護(hù)手冊(cè)AMM CHAPTER 34 - NAVIGATION 第34章導(dǎo)航2(11)
