-No response from the system to the test request or no results displayed: In this case, the test has not been completed.
 Return to initial condition is obtained by pressing the MCDU MENU key then CFDS key and selecting the system again. If the same sequence reoccurs then the computer managing the BITE of the system or the wiring from the CFDIU must be the cause.
 (f) Test stop In some cases, a key is allocated to stop a test in progress.
 EFF : ALL
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 (g)
 Configuration resetting after a test The operator may be requested to reconfigure after a test if the initial conditions required by the test have had a significant effect on the aircraft (instructions are in the AMM). If the operator wants to repeat the test he is not obliged to apply these instructions on configuration resetting.

 (h)
 Ground handling of the tests As maintenance messages are stored in the PFR or the GROUND REPORT they will not be erased until the next beginning of flight. Therefore, a test is a means of checking whether a fault is still present and a means of isolating a failed LRU. Activation of a test will be requested in the TSM by the fault isolation procedure related to a maintenance message. It will be used to confirm the presence of a fault or to eliminate any ambiguity. As a general rule, the test of the system including the LRU incriminated by the maintenance message (message ATA) will be activated. By default, the test of the system which generated the message (SOURCE) may be activated. The activation of a test may also be part of the removal/installation procedure of an LRU given in the AMM.

 (3) 3rd group
 (a) AVIONICS STATUS This function displays the identity of the systems detecting a class 1, 2 or 3 internal or external fault when the function is called. The AVIONICS STATUS thus rapidly provides a global overview of the status of all systems. It is a user-friendly monitoring device providing direct access to system menus which detect a fault (for example, flag displayed on the PFD). Furthermore, after aircraft power up, it enables to check that all computers have correctly satisfied the related power up tests. In order to know the reason for which a system is displayed in the AVIONICS STATUS it is recommended to get access to the system menu and to activate the system test (or test).
 NOTE : Certain systems are listed in the AVIONICS STATUS due to
____ normal absence of a ground power supply. Therefore, it is recommended to supply all systems prior to gaining access to the AVIONICS STATUS. It shall be noted that when a computer is not supplied it is not directly displayed in the AVIONICS STATUS as it no longer detects, itself, this fault. However, the systems using the signals from this computer appear in the AVIONICS STATUS.
 EFF : ALL
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 (b) GROUND REPORT This function displays on ground the class 1, 2 and 3 internal maintenance messages related to new faults detected on ground and which are therefore not recorded in the PFR. The faults detected during flight and which remain present on ground are in the PFR and not in the ground report. It is necessary to confirm all faults of the ground report by activating a test or a procedure described in the TSM.
 NOTE : Case related to Type 2 systems:
____ This function is in the LAST LEG/GROUND REPORT section specific to type 2 systems. The messages in this section concern faults detected during flight and on ground, the wording GND preceding the list of messages related to the faults detected on the ground in accordance with the same ground report logic as for type 1 systems. Case related to Type 3 systems: There is no ground report function for Type 3 systems. The test function shall be used in this case.
 (c)
 GROUND SCANNING The GROUND SCANNING enables fault trouble shooting based on ground activation by the operator himself of functions normally performed during a flight. The advantage of this is that it is not restrictive as far as actions are concerned. In fact, the operator decides what type of actions to be performed on the system, which is in GROUND SCANNING, as a function of the problems to be processed. This action may include dynamic phases (for example: engine startup, flight control surface movement, etc.). This is also an aid in trouble shooting faults difficult to resolve. All maintenance messages (class 1, 2 and 3, internal and external) related to all faults detected in real time by the system will be displayed during the GROUND SCANNING. In order to indicate a transient fault source to the operator, the maintenance messages, automatically displayed in GROUND SCANNING, are only erased when exiting from the function. Furthermore, GROUND SCANNING must always be preceded by a system test in order to identify, sooner, the possible static faults. The use of this function may also be requested by the TSM procedures.
　
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