1EFF : ALL 1 31-33-00Page 58 1 1 Aug 01/05 1 1 1CES 1
R **ON A/C 001-049, 051-099, 101-105,
R R R R R R (7) Mandatory Parameter Integrity Check The FDIU contains software to perform a Mandatory Parameter Integrity Check for a reasonable range during the flight. The results are stored in a nonvolatile memory and recorded on the DFDR and QAR in word 116 of subframe 2. The three parameters shown below are checked during the flight phase 'ENG SHUT DOWN'.
R R R R R R -------------------------------------------------------------No Parameter Valid Value -------------------------------------------------------------9 Normal Acceleration 1 +/- 0.2 g 10 Lateral Acceleration 0 +/- 0.2 g 11 Longitudinal Acceleration 0 +/- 0.2 g
R R R R R R The test condition is 15% less than N2 for both engines. The valid value is available for 8 seconds. The check is done once per second. When the flight phase and the test condition criteria are met, the valid value must be true for at least one second for a pass result, if not the integrity result is flagged as failed. If the test is failed or not done during flight phase 10, it is a Class II failure.
R **ON A/C 106-149, 211-299, 301-399, 401-499,
(7) Mandatory Parameter Integrity Check The FDIMU (FDIU-part) does a mandatory parameter integrity check during the flight. The results are stored in a non - volatile memory and recorded on the DFDR and the QAR (if installed). The three parameters shown below are checked during the flight phase 'ENG SHUT DOWN'.
-----------------------------------------------------------------
No Parameter Valid Value
-----------------------------------------------------------------
R R 9 10 11 Normal Acceleration Lateral Acceleration Longitudinal Acceleration Average for 8 sec 1 +/- 0.2 g Average for 8 sec 0 +/- 0.2 g Average for 8 sec 0 +/- 0.2 g
The test condition is 15% less than N2 for all engines. The valid value is available for 8 seconds. The check is done once per second. When the flight phase and test condition criteria are achieved, the valid value must be true for at least one second for a pass result, otherwise the integrity result is flagged as failed. If the test is
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failed, it is processed as a Class II failure and the bit 17 in the coded information label 350.00 is set to one.
The internal Class II fault ACCELEROMETER (6TU) is only detected on ground. To avoid the lost of the failure from the DFDRS LAST LEG CLASS REPORT this failure is copied from the ground memory corresponding to the end of current leg into the flight memory corresponding to the beginning of the new leg. This failure is stored, transmitted in normal mode and available via CFDIU menu after landing.
R **ON A/C 151-199, 201-210,
R R R R R R (7) Mandatory Parameter Integrity Check The FDIU contains software to perform a Mandatory Parameter Integrity Check for a reasonable range during the flight. The results are stored in a nonvolatile memory and recorded on the DFDR in word 116 of subframe 2. The three parameters shown below are checked during the flight phase 'ENG SHUT DOWN'.
R R R R R R -------------------------------------------------------------No Parameter Valid Value -------------------------------------------------------------9 Normal Acceleration 1 +/- 0.2 g 10 Lateral Acceleration 0 +/- 0.2 g 11 Longitudinal Acceleration 0 +/- 0.2 g
R R R R R R The test condition is 15% less than N2 for both engines. The valid value is available for 8 seconds. The check is done once per second. When the flight phase and the test condition criteria are met, the valid value must be true for at least one second for a pass result, if not the integrity result is flagged as failed. If the test is failed or not done during flight phase 10, it is a Class II failure.
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-210,
(8) Test Connector To enable the connection of a Portable MCDU or a Portable Data Loader (PDL), a test connector is installed on the front panel of the FDIU. The interface for test and program is RS 232.
(8) Test Connector To enable the connection of a Portable MCDU or a Portable Data Loader (PDL), a test connector is installed on the front panel of the FDIMU. The interface for test and program is RS 232.
**ON A/C ALL
(9) DFDR-CVR Synchronization The full 32 data bit word received from the GMT clock bus (label 150) is used to generate a frequency modulated output. This time code word is send to the CVR via audio output at a rate of 768 bit/sec every four seconds (at a beginning of each data frame) with LSB transmitted first.
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