(2)
The BITE test is operable on the ground only. The test is initiated by operating the STALL L or R test switches. The BITE checks operation of the stick shakers, cross channel faults, and interface faults.
(a)
The WARN ELEX message will display continuously on EICAS during a BITE test. After the BITE test, the EICAS message will not be displayed if the stall warning system normal.
(b)
If the SWC detects a fault, the BITE will display the highest priority fault code. Lower priority fault codes will be displayed in order of priority as higher priority faults are corrected. This process will continue until all faults are cleared, then the BITE will display the airplane configuration and option code.
(c)
If the system is normal, the stick shaker will operate during the BITE test. and the slats will extend to the fully extended position of the flaps and slats are in the takeoff position.
(d)
During a BITE test, the two pairs of hex indicators will illuminate until the test switch is released. After release of test switch, the numeric value of the software version will display for approximately 1 second, followed by either the fault code or the configuration/option code.
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A
757 MAINTENANCE MANUAL
(e)
The software version code uses only the numeric digit values between 01-09 and 80-99. This code represents only the software version configuration, and is independent from either the airplane configuration or the option selected.
(f)
The configuration code (most significant digit) is 4, and the option code (least significant digit) is F.
(3)
Faults are identified by codes and categorized into internal and interface faults.
(4)
Internal faults are coded A0 thru C5, with code A0 having highest display priority. Table 1 lists internal faults in priority order and their most probable causes.
~.............................................................................. | TABLE 1 | ................................................................................ | INTERNAL FAULT | | | CODE *[1] | PROBABLE CAUSE | ................................................................................
| A0 | More than one board failure on SWC |
| A1 | Slats retracted input circuit on SWC |
| A2 | Slats partially extended input circuit on SWC |
| A3 | Slats fully extended input circuit on SWC |
| A8 | Spare Input input circuit on SWC |
| A9 | Test input circuit on SWC |
| B0 | Air/ground input circuit on SWC |
| B1 | Gear down input circuit on SWC |
| B2 | Opposite channel fail input circuit on SWC |
| B6 | ARINC 429 input circuit on SWC |
| C0 | Analog to digital converter output circuit on SWC |
| C1 | Stick shaker output circuit on SWC |
| C3 | Auto slat enable output circuit on SWC |
| C4 | EICAS status message output circuit on SWC |
| C5 | Channel OK output circuit on SWC |
2...................…..........................................................1 *[1] Missing codes are not used.
(5) Interface faults have a lower display priority than internal faults and will be displayed only after all internal faults are corrected. Interface fault codes range from D0 thru D9 plus code FX , with code D0 having the highest display priority. Table 2 lists interface faults in priority order, and their most probable causes.
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