B.
 FM Level Computation of RESANA from the results of the FM and MCDU safety tests.

 -Transmission of malfunction reports : The malfunction reports are sent to the FIDS on the FMGC OWN line in a manner similar to that described in ATA REF 22-91-00 (para 3.B.(7)).

 C.
 Overall Result Indication
 The FIDS memorizes the FG and FM AFS TEST result.

 (1)
 Correct FG and FM result
 In this case the indication is PASS.

 (2)
 Incorrect FG and/or FM result
 The indication is PRESS LINE KEY.

 (a)
 FG incorrect
 The computer concerned is the FMGC.

 (b)
 FM incorrect The computer concerned is the FMGC, but FM section is specified.

 1EFF : ALL 1 22-96-00Page 6 1 1 Feb 01/98 1 1 1CES 1 6. Operation

_________ The following figures show an example of AFS TEST utilization from the selection of the AFS TEST option on the AFS MAIN MENU to the primary data of the analysis performed during the test. Utilization:
 -Message : FMGC1; FMGC1 internal fault
 -RESANAM : * type : AFS TEST, ground area
 *
 S : 0 ; fault not symmetrical

 *
 CD : 0 ; no 3rd phase analysis in the FIDS

 *
 error code : O1H ; FMGC OWN F/W

 *
 event : 1 ; AFS TEST

 -Snapshot utilization. Word 5 : bit 3 = 0 ; A/THR TEST FAILED Safety test of the A/THR function incorrect on the MONITOR side. (Ref. Fig. 001, 002)
R **ON A/C 001-049, 051-060, 101-101,
 7. Power-up Tests Initialization and Cockpit Repercussions
_______________________________________________________
 A. Computer FMGC
 (1)
 Conditions of power-up tests initialization

 -How long the computer must be de-energized: > 4s.
 -A/C configuration: A/C on ground with engines stopped.

 (2)
 Progress of power-up tests

 -Duration: 120s.
 -Cockpit repercussions directly linked to power-up test accomplishment ( some other repercussions may occur depending on the A/C configuration, but these can be disregarded ).
 -ECAM STATUS page:------------------aural warning: AP 1(2) INOP
 -FCU: AP 1(2) P/BSW flashes--------------cavalry charge A/THR 1(2) P/BSW flashes
 -EFIS:
 FD 1(2) boxed on PFD during 10s
 FD 1(2) on PFD

 1EFF : ALL 1 22-96-00Page 7 1 1 May 01/05 1 1 1CES 1

 (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed).
 (a)
 Tests pass:

 -EFIS PFD:
 FD 1(2)

 -ECAM STATUS page:
 AP 1(2) INOP disappears

 (b)
 Tests failed:

 -EFIS PFD:
 FD 1(2) not displayed

 -ECAM STATUS page:
 AP 1(2) INOP

 B. Computer FAC
 (1)
 Conditions of power-up tests initialization

 -How long the computer must be de-energized: > 4s.
 -A/C configuration: (a): A/C on ground and engines stopped for electrical power-up tests. (b): A/C on ground and hydraulically energized for yaw damper power loop power-up tests.

 (2)
 Progress of power-up tests

 -Duration:
 Configuration (a): 90s.
 Configuration (b): 5s.

 -Cockpit repercussions directly linked to power-up test accomplishment ( some other repercussions may occur depending on the A/C configuration, but these can be disregarded ).
 (a)
 Configuration (a):

 -ECAM warning:----------------------aural warning: AUTO FLT RUDDER TRIM 1(2)----------single chime AUTO FLT RUD TRAV LIM 1(2) displayed three times AUTO FLT RUDDER TRIM 1(2)----------single chime AUTO FLT YAW DAMPER 1(2) displayed once
 -FLT CTL panel: FAC 1(2) P/BSW FAULT---------------single chime legend flashes

 (b)
 Configuration (b):
 none

 (3)
 Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed).

 (a)
 Tests pass:
 Configuration (a):

 -ECAM warnings no longer displayed
 -FAULT legend of FAC 1(2) P/BSW not on
 Configuration (b):
 none

 (b)
 Tests failed:
 Configuration (a):

 -ECAM warnings
 -FAULT legend of FAC 1(2) P/BSW on
 Configuration (b):

 -ECAM warning:
 AUTO FLT YAW DAMPER 1(2)

 -NOTE: The yaw damper power loop power-up tests are performed only if the electrical ones are correct.
　
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