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T81686
A 737-300/400/500MAINTENANCE MANUAL
8. Antiskid Built-in-Test Circuit
______________________________
A. The antiskid built-in-test circuit is a continuous function during operation of the antiskid system. Any loss of power to the system, an open valve, or transducer circuit fault will cause the inoperative light to come on. Also if the antiskid system is switched off, the inoperative light will remain on. This is a constant reminder that antiskid protection is off and that manual, antiskid off braking techniques should be used.
B. A manual built-in-test feature is available at the antiskid control unit in the electronic compartment. The control unit front panel provides for fault isolation. The front panel contains six light emitting diode (LED) indicators, a wheel circuit selector switch and five pushbutton switches (Fig. 1).
C. The top center amber LED is marked ABS and limited to a test of the autobrake system. Two red LEDs flank the ABS light. In general, the right red shows a full open circuit and the left red a grounded circuit. Three green LEDs are located below the red and amber, indicating from left to right; low, medium and high voltages. With the selector switch, a choice is provided of the four wheel circuits for test. Included on the dial are positions for left and right alternate brake and parking brake circuits. Selector OFF positions are mounted at each end of the selector switch dial. The choice of component test is made by pushing one or more of five pushbutton switches labelled VALVE, XDCR (transducer), LW (locked wheel), SKID and ABS (autobrake system).
9. Operation
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A. Antiskid Control Switches
(1)
A guarded switch on the P2 flight deck center panel provides both inboard and outboard power for the antiskid unit. If the switch is turned off the antiskid system becomes inoperative, and power from the ANTI-SKID FAIL circuit breaker on the P6 panel through the landing gear lever up switch and fail annunciator logic in the antiskid unit will turn on the ANTISKID INOP light on the P2 panel.
B.
Normal Antiskid Mode
(1)
Wheel speed tranducers, one driven by each wheel, produce electrical frequency outputs which are proportional to wheel speed. The signals are processed by individual wheel circuits in the antiskid control unit to control brake pressure to the applicable wheel. The transducer frequency output signal is processed on the wheel circuit card and converted to an analog dc voltage proportional in amplitude to the ac frequency.
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A 737-300/400/500MAINTENANCE MANUAL
E11 LANDING GEAR LOGIC SHELF
Antiskid System Schematic Figure 3 (Sheet 1)
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A 737-300/400/500MAINTENANCE MANUAL
V8 RIGHT INBD
ANTISKID VALVE
V10 RIGHT OUTBD
LEFT OUTBD
VALVE DRIVE
RIGHT ALT
ANTISKID
VALVE DRIVE
LEFT ALT
ANTISKID
VALVE DRIVE
M162 ANTISKID CONTROL UNIT
V7 LEFT INBD ANTISKID VALVE
V9 LEFT OUTBD
ANTISKID VALVE
V124 RIGHT ALT
ANTISKID VALVE
V125 LEFT ALT ANTISKID VALVE
Antiskid System Schematic Figure 3 (Sheet 2)
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A
737-300/400/500MAINTENANCE MANUAL
(2)
The analog signal is compared to a reference velocity loop circuit which provides a commanded wheel velocity based on average aircraft deceleration. A velocity comparator provides a velocity error voltage. Maximum braking occurs when this error is minimized.
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