(2)
The motor driver provides an interface with the power supply to pass the binary encoded scan and elevation drive signals from the R/T to the receiver/monitor driver, and the scan and elevation monitor signals from the receiver/monitor driver to the system R/T. The receiver/monitor driver buffers and translates the binary encoded scan and elevation drive signals to provide motor positioning control signals to the motor driver. It also buffers the incremental and zero monitor signals and provides a binary encoded output to the R/T for interpretation. When commanded by the receiver/monitor driver, the motor driver provides drive voltages to incrementally rotate the scan and elevation stepper motors to move the antenna .90 degrees in scan and 40 degrees in elevation in 0.25-degree steps.
(3)
Incremental monitors track the motor shaft rotation of the scan and elevation stepper motors from a zero reference point to provide constant monitoring for use by the system receiver-transmitter.
(4)
Zero monitors provide a reference synchronizing point for the scan and elevation stepper motors from which incremental changes in antenna position can be measured by the incremental monitors.
(5)
Scan and elevation toggle switches provide a manual means of disabling the input power to the scan and elevation stepper motors. When the pedestal cover is closed, the switches are tripped to ON position by the cover. This prevents the switches from being inadvertently left in OFF position and disabling the antenna drive.
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34-41-02 Page 12 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/86
7. Control
A. The weather radar system requires 115 volts ac, 400 Hz from the ELEX PWR bus.
CAUTION: DO NOT OPERATE WEATHER RADAR WHILE THE AIRPLANE IS BEING REFUELED OR DEFUELED AND DO NOT OPERATE IN ANY RADIATING MODE WHILE A FUELING OPERATION IS BEING CONDUCTED WITHIN 200\FEET OF THE ANTENNA OR AN EXPLOSION MAY OCCUR.
PERSONNEL MUST NOT ENTER AN AREA CLOSER THAN 10 FEET IN FRONT OF A RADIATING ANTENNA OR INJURY TO PERSONNEL MAY OCCUR.
B. The ground test procedure is contained in 34-41-02, Adjustment/Test (Operational Test). WEATHER RADAR SYSTEM - TROUBLE SHOOTING
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Feb 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-41-02 Page 13
EFFECTIVITY
Airplanes with Collins WXR-700X Weather Radar
1. General
A. The trouble shooting procedure is based on the performance of the weather radar system fault isolation circuits. These circuits continuously monitor system operation in all modes.
B. The circuits identify most system malfunctions, and display alphanumeric messages (in message slots on the display unit) as an aid to trouble shooting system failures.
C. The message slot locations (Fig. 101) and the message(s) displayed are described as follows:
(1)
Message slot 1 - Located at the top left corner, presents the selected mode of operation. These will be displayed as WX, WX+T, MAP, and TEST.
(2)
Message slot 2 - Located at the top center of the display, annunciates the alert messages of HOLD, WEAK, and FAIL. HOLD will flash (1 second on, 1 second off) when the HOLD mode is selected on the indicator. FAIL will flash whenever a system failure is detected. WEAK will flash when the system detects a loss of calibration, such as the transmitted power, or receiver sensitivity has fallen below the desired level but the system is still usable.
(3)
Message slot 3 - located at the top right corner, displays the selected range.
(4)
Message slot 4 - Located directly below message slot 1 (selected mode). In normal operation, a color bar, consisting of green, yellow and red colors, will be present.
(5)
Message slot 5 - located directly below message slot 3 (range), indicates range mark intervals.
(6)
Message slot 6, 7, 8 and 9 - located directly below message slot 4 (color bars), display system detected LRU faults. The failure message consists of T/R (receiver - transmitter), ANT (antenna), DSP (display indicator).
(7)
Message slot 10 - Located at the bottom left corner, displays the system gain setting in the MAP mode. One of the following set of characters will be displayed: MAX, -01, -02, -03, -04, -05, -06, -07, -08, MIN. Each gain step reduces the system sensitivity by 2 dB. In all other modes or when in calibrated operation (CAL), this message slot is blank.
(8)
Message slot 11 - Located at the bottom left, immediately to the right of message slot 10, displays IDNT when clutter suppression (GCS) is selected. Otherwise this slot is blank.
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Jun 20/85 34-41-02 Page 101
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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