If the IRCM INOP caution legend appears, place the power switch OFF.
4.3.4 Stopping Procedure. ON-OFF switch -OFF. The transmitter will continue to operate for about 60 sec-onds during the cooldown cycle. IRCM INOP caution leg-end should appear during cooldown cycle.
4.4 HEADS UP DISPLAY AN/AVS-7.
Heads up display (HUD) AN/AVS-7; (Figure 4-2) con-
sists of signal data converter CV-4229/AVS-7 (SDC) lo-cated in the avionics compartment, the converter control C-12293/AVS-7 (CCU) located on the lower console, and the display, SU-180/AVS-7 (DU) consisting of the optical unit (OU) and power supply calibration unit (PSCU). Two thermocouple ampli.ers are located in the avionics com-partment and two HUD control switches are located on the pilot’s collective sticks. The HUD system serves as an aid to pilots using the AN/AVS-6 (ANVIS) during night .ight operations by providing operational symbology information about the aircraft. There are two programming modes and one operational mode which allow both pilots to indepen-dently select the symbology for their respective display modes from a master set of symbols in the signal data con-verter. Power to operate the HUD system is provided by the No. 1 ac primary bus and the No. 1 dc primary bus through circuit breakers marked HUD REF and HUD SYS.
4.4.1 Basic Principles of Operation. The pilots can independently select from four normal symbology modes and four declutter modes that were pre-programmed. De-clutter mode has four vital symbols that will always be displayed: Airspeed, Altitude (MSL), Attitude (pitch and roll), and Engine Torque(s). An adjust mode, during opera-tion, is used to adjust barometric altitude, pitch, and roll. If the HUD system loses operating power after adjustments have been made, the brightness, mode, barometric altitude, pitch, and roll must be adjusted as necessary. The system self test is divided into power-up or operator initialized built-in-test (BIT) and in-.ight BIT. The system BIT is initialized during power-up or selected by the operator. Part of the BIT is a periodic test that is performed automatically along with normal system operation. A failure of the SDC, or the pilot’s DU will illuminate the CCU FAIL light and display a FAIL message on the display unit. When a FAIL message is displayed on the DU, the operator should ac-knowledge the failure and re-run BIT to con.rm the fault.
4.4.2 Controls and Functions. The CCU, located on the lower console, (Figures 2-8 and 4-2), and the control switches on the pilot’s collective stick (Figure 2-11) are controls and indicators necessary for HUD operation. The EYE SELECT L/R position is set when display units are connected prior to operation. A focus ring on the OU pro-vides control for focusing the display. The OU is adjusted by the manufacturer and under normal conditions adjust-ment is not required.
a. The converter control is described below:
CONTROL/ FUNCTION
INDICATOR
CPLT
BRT/DIM Copilot’s control for display
brightness.
DSPL POS D/U/ Copilot’s control for display
L/R position down/up (outer knob) and left/right (inner knob).
MODE 1-4/ Copilot’s mode select 1-4 and DCLT declutter switch.
PLT
BRT/DIM Pilot’s control for display brightness.
DSPL POS D/U/ Pilot’s control for display position L/R down/up (outer knob) and left/right (inner knob).
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：UH-60Q 直升機技術手冊 直升機操作手冊 1(121)
