(a)
The amber SELF MONITOR light comes on to indicate that the computer has disabled itself due to a problem with the autoslat control valve coil or the circuits which control the coil.
(b)
The coil monitor circuit continuously monitors the hot and cold legs of the autoslat valve solenoid coil. The coil monitor will detect an open circuit between the computer and the coil, or a disagreement between the hot and cold leg relays. When such a fault is detected, the coil monitor turns on the SELF MONITOR light.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH AUTOSLAT ú
27-83-00
COMPUTER P/N 65-52818 ú CONFIG 1 ú 02 Page 4 ú Mar 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(c)
When you push the H LEG TEST or C LEG TEST button to test one of the solenoid coil wires, the SELF MONITOR light will come on until you push the RESET button.
(5)
Alpha COMPARE HI and Alpha COMPARE LO lights
(a)
The alpha COMPARE HI and COMPARE LO lights come on to indicate that the AOA signal used by one computer does not agree with the AOA signal used by the other computer. This gives an indication of a mechanically jammed sensor vane, and also detects faults in the synchro wiring or AOA signal processing circuits.
(b)
This "dynamic alpha compare" test is enabled when wheel speed is greater than 60 knots, main gear is off the ground, and power is OK on the other computer. The test is automatically performed immediately after liftoff.
(c)
Immediately after liftoff, the dynamic alpha compare circuit compares the AOA signal of the hot leg path with the AOA signal of the cold leg path from the other computer. If the circuit detects a vane angle that exceeds the angle from the other computer by more than 3 degrees, the alpha COMPARE HI light is turned on. If the circuit detects a vane angle that is less than the angle from the other computer by more than 3 degrees, the alpha COMPARE LO light is turned on. The light will remain on until the computer is reset on the ground.
(d)
When an alpha COMPARE HI or LO light is turned on, the autoslat computer is not disabled. However, it will illuminate the AUTOSLAT FAIL light on the P5 panel on the flight deck when the master caution recall button is pressed.
C.
Autoslat Computer Switches
(1)
Switches on the face of each computer assist in testing and trouble shooting. The circuitry associated with each switch is described as follows:
(2)
RESET switch
(a)
The self monitor and the dynamic alpha compare hi and lo fault relays are mechanically latched when set. They will remain set until they are reset by pressing the RESET pushbutton switch.
(3)
H LEG TEST and COLD LEG TEST switches
(a)
Built-in test equipment (BITE) is provided for testing operation of the autoslat system. One test switch is for testing the hot leg path and one for testing the cold leg path. This test procedure verifies the ability of the summer/output switch circuits to energize their respective relays and checks the ability of the coil monitor to detect a disagreement between the two legs. This test feature is disabled if any fault relays in the computer are already set.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH AUTOSLAT ú
27-83-00
COMPUTER P/N 65-52818 ú CONFIG 1 ú 03 Page 5 ú Mar 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(b)
Each leg path is tested by pressing one of the pushbutton LEG TEST switches. The switch simulates air mode and sends a test signal to activate the leg under test while deactivating the other leg. Successful operation of the leg under test is indicated by illumination of the SELF MONITOR light, which indicates a disagreement between the two legs. Then the computer is reset and the test is repeated for the other leg.
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