EFFECTIVITY
AIRPLANES WITH DELCO INS CONFIG 1 ATG A Page 28 Apr 25/8934-41-00
the numbers in the FROM-TO display indicate either the waypoints defining the navigation leg currently being flown, or the DME station currently being used. The number identifying a DME station appears in the TO side of the display while the FROM side is blank.
K. Pressing the WY PT CHG key allows the numbers in the FROM-TO display to be changed. If the INSERT key is pressed, the INU computer will use the navigation leg or DME station defined by the new numbers in all navigation computations. If the INSERT key is not pressed, the computer will continue to use the original numbers in all navigation computations, but distance/time information based on the new leg can be called up and read in the data displays.
L. The HOLD key is used in conjunction with other CDU controls to stop displayed present position from changing, to perform a position update, and to display inertial present position. The HOLD key lights when pressed the first time and goes out when pressed the second time or when inserted data is accepted by the DCU.
XA XA NOTE:____On Carousel CIV Syst, during the gimbal slew procedure, the HOLD XA key is used to stop all slewing operations. Slewing can occur XA only when the HOLD key light is off. XA
M. The REMOTE key illuminates amber when pressed and allows simultaneous loading and insertion of waypoint and navaid data into more than one INS by using only one CDU. The REMOTE key must be pressed on all participating INS to achieve this simultaneous loading. The remote operation is disabled when the REMOTE keys are again pressed and the key light goes out.
N. The ALERT lamp illuminates amber 2 minutes before reaching a waypoint during flight. The light goes out when the INS automatically switches to the next navigation leg.
O. The BAT lamp illuminates amber when the INS is operating on battery power.
P. The WARN lamp lights red when the INS self-testing circuits detect an out-of-tolerance condition. Illumination of the WARN lamp can be caused by a continuous or intermittent condition. Intermittent out-of-tolerance conditions detected by the DCU light the WARN lamp until it is reset by the TEST switch. If the WARN lamp is lighted by a continuous condition which does not degrade attitude operation the WARN lamp goes out when the mode selector is set to ATT.
Q. The TEST switch, common to the AUTO-MAN switch, is used to test all indicating lamps and displays and associated circuits. The TEST switch is also used in conjunction with other controls to display numerical codes indicating specific malfunctions and to reset the malfunction warning circuits.
R. The DIM knob on the data selector is used to vary light intensity of the data displays, the FROM-TO display, the ALERT lamp, and the HOLD, REMOTE, INSERT, and WYPT CHG keys. The DIM knob does not, however, control the BAT or WARN lamps. The knob is detented to prevent inadvertent dimming of the lamps.
6. Navigation Unit
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EFFECTIVITY
AIRPLANES WITH DELCO INS CONFIG 1 02 A Page 29 Apr 25/8734-41-00
FLIGHT DIRECTOR COMMAND BARS
INCLINOMETER
INDICATOR
Attitude Director Indicator
Figure 12 (Sheet 1)
EFFECTIVITY CONFIG 1
AT 701-750799 Page 30
34-41-00
Oct 25/80
750832
ATTITUDE
SPHERE
FLIGHT DIRECTOR COMMAND BARS
AIRPLANE SYMBOL
AUTOTHROTTLE SPEED DISPLAY DECISION HEIGHT (MDA) LIGHT
HORIZON LINE
GLIDE SLOPE DISPLAY
RISING RUNWAY (RADIO ALTITUDE AND LOCALIZER DEVIATION)
INCLINOMETER
INDICATOR
751773
Attitude Director Indicator
Figure 12 (Sheet 2)
EFFECTIVITYATLAS ALL EXCEPT
CONFIG 1 AT 701-750
799 Page 31IB 406-499
34-41-00
Oct 25/80
A. The navigation unit (NU) is a temperature controlled unit which produces all INS output signals. Each unit is supported on three precision rack-mounted pins which slide into bushings in the NU case. Two bushings are in the rear and one in the front of the case assembly. The unit slides into the rack over a gasket which seals the aircraft forced air cooling system to the bottom of the case assembly. Exhaust cabin air is routed through heat exchangers in the NU for cooling during operation. The NU contains an inertial reference unit (IRU), a digital computer unit (DCU), and an inertial reference unit electronics section (IRUE).
B. The azimuth synchro signal is a direct output to the compass system. This signal represents a constant compass direction but it does not represent a specific compass angle. The pitch and roll signals to the attitude director indicator are direct synchro signal outputs.
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