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R  (Ref. Fig. 006, 007, 008, 009, 010, 011, 012) The Menu mode corresponds to a phase of maintenance on the ground. In this mode, the computer displays a menu on the screen. The selection of the menu items is made with keys placed at level of the lines displayed on the side of the screen. The procedure is conversational. This means that the operator can call certain sub-functions of the menu (for example: auto test, reminder of the last failures) and receive in return this information in plain language. The functions accessible in Menu mode are:
 -LAST LEG REPORT The purpose of this function is to present the internal and external failure messages detected by the braking system, that appeared during the last flight. Recorded Class 1 and 2 failures: Class 1: failures which have an operational consequence on the current flight. They are indicated to the crew in flight. Class 2: failures which do not have operational consequence on the current flight but which may affect the aircraft availability. They are not indicated to the crew but are the subject of an ECAM report.
 -PREVIOUS LEGS REPORT The purpose of this function is to present the internal and external failure messages (Class 1 and 2) that appeared during the 64 previous flights (failure history). This is the "sum" of the LAST LEG REPORT items over several flights.
 -LRU IDENTIFICATION The purpose of this item is to present the P/N of the BSCU hardware and software configuration (configuration of software of BSCU calculation, acquisition and monitoring board).
 -TROUBLE SHOOTING DATA This function presents the complementary information concerning the failures. ("Snapshot" of the system environment at the moment of the failure). (Ref. Fig. 011)
 -CLASS 3 FAULTS The purpose of this function is to present the Class 3 messages that appeared during the previous flights. Class 3: failures having no consequence on the aircraft safety and availability. They are not indicated to the crew.
 -GROUND SCANNING
R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 32-46-00Page 13 1201-220, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1

 CFDIU Menu (SHEET 2) R Figure 006
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 CFDIU Menu (SHEET 4) R Figure 007
 1EFF : 001-049, 051-099, 101-105, 151-199, 1 32-46-00Page 15 1201-220, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1

 CFDIU Menu (SHEET 5)
 Figure 008

R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 32-46-00Page 16 1201-220, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1

 CFDIU Menu (SHEET 6) R Figure 009
 1EFF : 001-049, 051-099, 101-105, 151-199, 1 32-46-00Page 17 1201-220, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1

 CFDIU Menu (SHEET 8) R Figure 010
 1EFF : 001-049, 051-099, 101-105, 151-199, 1 32-46-00Page 18 1201-220, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1

 Trouble Shooting Data - Hexadecimal
 Figure 011

R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 32-46-00Page 19 1201-220, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1

 CFDIU Menu (Sheet 9) R Figure 012
 1EFF : 001-049, 051-099, 101-105, 151-199, 1 32-46-00Page 20 1201-220, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1 The purpose of this function is to present the internal and external failures. These will be detected as failures only in the ground stop configuration.

 -TEST
R  (Ref. Fig. 012) This function is to be activated after any maintenance action on the aircraft. Its purpose is to re-configure the BSCU (if necessary) and to check its correct operation and the continuity with the different peripherals. Its system is separately actuated. The test control must trigger: *the power-up test of the system concerned *the peripheral continuity test (permanent monitoring and specific test for the ALTERNATE and NWS servovalves, through transmission and check of calibrated currents).
 -PIN PROG SELECTION
R  (Ref. Fig. 009) This function is to be performed after removal/installation of the BSCU. Its purpose is to adapt the BSCU pin programming to the aircraft pin programming (strap connection). At the end of the Menu mode, the system must be set to OFF then to ON to be correctly reset. Moreover, the pin programming selection must also be performed on the second BSCU system. The various configurations available depend on the parameters below: . aircraft type, . brake type, . wheel type (different diameters), . deceleration rate in special automatic braking mode.
 -STEERING DATA (Ref. Fig. 013) The purpose of this function is to present the main parameters of the nose wheel steering system. The parameters are: . SELV ORDER: Nose Wheel Steering (NWS) electro-distributor status (OPEN or CLOSED), . SSV CURRENT: NWS servovalve current (-10 mA < SSV CURRENT < +10 mA), . STEER ORDER: Commanded steering angle (-75 deg. < STEER ORDER < +75 deg.), . CAPT ANGLE: CAPT steering handwheel angle (-75 deg. < CAPT ANGLE < +75 deg.), . FO ANGLE: F/O steering handwheel angle (-75 deg. < FO ANGLE < +75 deg.), . PEDAL ANGLE: ELAC angle (-75 deg. < PEDAL ANGLE < +75 deg.),
　
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