(a)
AOA sensor transition fault: sensor vane did not move more than 3 degrees on the last flight.
(b)
Flap position transition fault: flaps did not move more than 3/4 degrees on the last flight.
(c)
N1 tachometer transition fault: maximum and minimum values of N1 did not differ by more than 10% on the last flight.
(d)
N2 tachometer transition fault: maximum and minimum values of N2 did not differ by more than 5% on the last flight.
(e)
Discrete on-ground fault: air/ground relay indicated on ground when airspeed was greater than 160 knots on the last flight.
(4)
When the indicated fault has been corrected, the fault memory must be cleared. To clear the fault memory, press and hold the START BITE switch for 10 to 20 seconds until the lights flash on and off. Any stored faults from the previous flight will be erased and the corresponding lights will go off. A BITE test performed after clearing the memory will indicate any real time faults which still exist.
(5)
Any stored faults must be cleared prior to a test of the stall warning system. Stored faults will be automatically cleared at the next airplane takeoff.
(6)
Fault Indicator Lights
(a)
The stall warning computer continuously monitors its inputs and internal circuits. Any fault detected by the computer will turn on the appropriate light during the next BITE test. The faults associated with each light are described below:
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú
27-32-00
COMPUTER P/N 65-52819 ú CONFIG 1 ú 08 Page 7 ú Mar 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
(b)
(c)
(d)
(e)
(f)
(g)
(h)
A
737-300/400/500MAINTENANCE MANUAL
INTERNAL FAILURE
1) Indicates a fault with one of the following: stall warning computer internal input circuits, output circuits, analog/digital converter, ARINC 429 transmitter or receiver, memories, or power supplies.
AIR DATA COMPUTER
1) Indicates that no data is received from the DADC, or that the data received is out of range or in error.
AOA SENSOR
1) Indicates one or more of the following: no data is received from the AOA sensor, the data received is out of range, a problem exists with the computer's synchro to digital converter, or there was an AOA transition fault.
FLAP POSITION
1) Indicates one or more of the following: no data is received from the flap position transmitter, the data received is out of range, a problem exists with the computer's synchro to digital converter, or there was a flap position transition fault.
N1
1) Indicates that no signal is received from the N1 tachometer indicator, that the signal received is out of range, or that there was an N1 transition fault.
N2
1) Indicates that no signal is received from the N2 tachometer indicator, that the signal received is out of range, or that there was an N2 transition fault.
DISCRETE 1) Indicates one of the following faults: a) On-ground fault: air/ground relays indicate ground mode when airspeed is greater than 160 knots. b) In-air fault: air/ground relays indicate air mode when airspeed is less than 60 knots.
c) Asymmetry fault: the leading edge light module signal indicates asymmetry when the flap position transmitter indicates flap position is less than 1 degree.
d) Self-test fault: the self-test switch on the P5-18 module is held on for more than 20 seconds.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú
27-32-00
COMPUTER P/N 65-52819 ú CONFIG 1 ú 06 Page 8 ú Mar 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
5. Self-Test Switch
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