(e) Structure of the BITE system pages (example with TROUBLE SHOOTING DATA of SDAC 1)
------------------------------------------------------------------| Character | Content | ------------------------------------------------------------------| 1 to 5 | control/accountability header | | 6 | C | | 7 to 9 | downlink message sequence code | | 10 to 12 | SMD | | 13 | CR | | 14 | LF | | 15 to 23 | spaces | | 24 | S | | 25 | D | | 26 | A | | 27 | C | | 28 | space | | 29 | 1 | | 30 | CR | | 31 | LF | | 32 | space | | 33 | T | | 34 | R | | 35 | O | | 36 | U | | 37 | B | | 38 | L | | 39 | E | | 40 | space | | 41 | S | | 42 | H | | 43 | O | | 44 | O | | 45 | T | | 46 | I |
R 1EFF : 001-049, 051-099, 101-105, 1 31-32-00Page A28 1 1 May 01/05 1 1 1CES 1
------------------------------------------------------------------| Character | Content |
------------------------------------------------------------------
| 47 | N |
| 48 | G |
| 49 | space |
| 50 | D |
| 51 | A |
| 52 | T |
| 53 | A |
| 54 | CR |
| 55 | LF |
| 56 | CR |
| 57 | LF |
| 58 | space |
| 59 to n-1 | page content |
| n | ETX |
| (n = 186 max. for a block) |
**ON A/C ALL
F. Interface with the Systems which Provide Aircraft Configuration (AMU, CIDS1, FWC1, DMC1) The AMU, CIDS1, FWC1 and DMC1 provide aircraft configuration information. These parameters are acquired 45 s after CFDIU power-up, and on flight phase 1/2 transition.
G. Interface with the Multi Mode Receiver (MMR)
The MMR is installed on the aircraft in place of the ILS. To be in MMR configuration, the CFDIU only needs one of the two labels 271 MMR1 and MMR2.
NOTE : When the MCDU MENU page comes into view, you must wait between 30s
____ and a maximum of one minute before you can push the line key adjacent to the CFDS indication to get access to the MMR BITE through the SYSTEM REPORT/TEST/NAV menu pages. In this way, these pages will show the actual aircraft configuration. The MMR item is valid when the MMR is powered up at the same time as the CFDIU or within 15s after CFDIU powerup. After 15s, the CFDIU must be reset.
There is no modification in the failure correlation processing. Access to the GPSSU BITE through the SYSTEM REPORT/TEST/NAV item is active depending on the state of the GPSSU1(2) installation pin programming (M/11A - T/11K).
1EFF : ALL 1 31-32-00Page A29 1 1 May 01/05R 1 1 1CES 1
R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
H. Interface with the Air Traffic Service Unit (ATSU)
When the ATSU is connected, it fulfills all the functions provided by the
ACARS MU.
Particulars:
The ATSU is connected to the ACARS MU input.
The ATSU must be pin-programmed.
System specificity:
In this case, the CFDIU specifies, on the aircraft configuration labels,
ATSU aircraft installation and ACARS MU aircraft installation.
**ON A/C ALL
6. Component Description
_____________________
**ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
A. Architecture
(Ref. Fig. 024)
(Ref. Fig. 025)
The CFDIU consists of two distinct channels:
-
a normal channel which ensures operation in normal conditions (no fault)
-
a back-up channel which ensures restricted operation when the normal
channel is faulty. These two channels are located in a 4MCU housing and they are physically segregated within the housing
1EFF : ALL 1 31-32-00Page A30 1 1 Aug 01/05 1 1 1CES 1
CFDIU - Internal Architecture
Figure 024
R 1EFF : 001-049, 051-099, 101-105, 151-154, 1 31-32-00Page A31 1201-207, 1May 01/05 1 1 1CES 1
CFDIU - Exploded View
Figure 025
R 1EFF : 001-049, 051-099, 101-105, 151-154, 1 31-32-00Page A32 1201-207, 1May 01/05 1 1 1CES 1
R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
B. Architecture
The CFDIU consists of one channel which ensures operation in normal conditions.
**ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
C. Characteristics of the Normal Channel
The normal channel consists of:
-A power supply unit: -15V, +15V, +5V.
-2 input/output boards
-
A logic/monitoring and interface board essentially consisting of a normal/back-up channel selection device
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