Table 4-1. Master Mode Symbology Display (HUD) (Cont)
No. Symbol Source Range/Description
NOTE: After ACK is used to acknowledge a fault, the fault will not reappear until BIT is selected or power is cycled off and on.
4.4.5 Operation.
4.4.5.1 Starting Procedure.
1. ADJ/ON/OFF switch -OFF. 2. Optical unit support clamps -Installed ANVIS. Verify clamps can by rotated. on The AN/AVS-7 system should not be used if the quick-release connector is not in working order.
NOTE Check surface of lens for cleanliness. Clean in accordance with TM 11-5855-300-10. 7. PSCU -Connect. Connect PSCU to quick-release connector by rotating the connector en-gagement ring.
3. DU lens -Check.
Keep the protective caps on the ANVIS whenever it is not in use. Operate the ANVIS only under darkened conditions. Failure to remove the ANVIS neck cord prior to operation of the HUD may pre-NOTE vent egress from the aircraft in an emer-gency. Ensure ANVIS operator procedures have
been completed.
4. ANVIS neck cord -Removed.
8. P-PGM/OP/CP-PGM switch -OP.
5. Optical unit -Install on ANVIS. Attach optical unit to either monocular housing. Do not 9. ADJ/ON/OFF switch -ON. System ON and tighten OU clamp completely with thumbscrew FAIL lights illuminate and BIT will initiate au-at this time. The OU (display) may have to be tomatically. rotated to horizon after the system is operating.
10. FAIL light -Check. Light should go out after
NOTE
ten seconds. BIT is complete.
The helmet may now have to be rebalanced.
NOTE
6. EYE SELECT switch on PSCU -L or R. Allow one minute for display warm-up. Dis-play intensity is preset to low each time
ADJ/ON/OFF switch is set from OFF on
ON.
If a fault is displayed in the DU, acknowl-
CCU ADJ/ON/OFF switch must by OFF edge fault and re-run BIT to con.rm fault.
before connecting or disconnecting quick-
release connector. 11. BRT/DIM switch -As desired.
12.
DSPL POS control -As required. Center dis-play in .eld of view.
13.
Display aligned to horizon -Check. Tighten OU clamp.
4.4.5.2 Operator Self Test (BIT).
1.
BIT/ACK switch -Press to BIT and hold. The ON and FAIL light will illuminate. At end of BIT, FAIL indicator will extinguish.
2.
BIT/ACK switch -Release.
4.4.5.3 Displayed System Faults. The system self test is divided into power-up or operator initialized built-in-test (BIT) and in.ight BIT. The faults result as warnings and messages that blink at a rate of two per second in the dis-play units. Part of the BIT is a periodic test that is per-formed automatically along with normal system operation. This BIT monitors and/or tests SDC functions and/or sig-nals. A failure of the SDC, NAV signals pilot’s DU, will illuminate the converter control FAIL light and display a FAIL message CPM, SDR, SDA, PS, NAV, PDU or CPDU on the display unit. An attitude (ATT) sensor indi-cation will be displayed when a gyro invalid condition exits. ATT, NAV, PDU, CPDU, and all SDC faults can be cleared by setting BIT/ACK switch to ACK. The follow-ing helicopter status messages are also displayed.
1.
The caption MST (.rst priority) indicates op-eration of the master caution warning lamp. This message will disappear during the rest of the main warning lamp operation.
2.
The caption MEM (second priority indicates that the doppler data is not updated. a previous computed data is available. This message will appear simultaneously with the MEM lamp on the doppler operating panel.
3.
The caption HOOK (third priority) indicates the cargo hook is open. The message will ap-pear simultaneously with the indication lamp in the cockpit.
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