-
the BSCU CHAN 1(2)/NORMAL BRAKINGTEST page 1/2 comes into view with INITIAL CONDITIONS
On the lower ECAM DU, the ELEC page
comes into view.
On the ELEC page:
-
the TR1(2) energizes the DC1(2) busbar.
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ACTION RESULT -------------------------------------------------------------------------------
- on the panel 402VU, make sure that the A/SKID & NOSE WHEEL switch is at ON.
- on the ECAM control panel, push the HYD key
- on the panel 402VU, make sure that no autobrake mode is armed.
- on the panel 110VU, make sure that the PARK BRK control switch is at OFF.
-do not operate the brake pedals during the test.
- on the MCDU, push the next page function key
-make sure that the engines are not running.
5. Push the line key adjacent to the START TEST indication.
NOTE : If the IN PROGRESS 10S
____ indication stays in view, push the line key adjacent to the RETURN indication. Do a check of all the initial conditions and do the test again.
- on the lower ECAM DU, the HYD pagecomes into view and make sure that the Green hydraulic system is pressurized.
-
the BSCU CHAN 1(2)/NORMAL BRAKINGTEST page 2/2 comes into view.
On the BSCU CHAN 1(2) page:
-
the IN PROGRESS 10S indication is shown
-then the NO FAULT DETECTED indicationcomes into view when the system isserviceable.
If the system is not serviceable:
-a list of faults comes into view whenthe test finds faults.
NOTE : The prompt ">" to the right of
____ the class number shows that there are TSD pages associated to this fault. Push the line key adjacent to the prompt to get access to these pages.
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- or if one or more of the initial conditions is not satisfactory, these indications come into view: . TEST NOT PERFORMED . the initial condition(s) that is (are) not satisfactory
- or the TEST TIME OUT indication comes into view when the test is not completed in the time limit. Push the line key adjacent to the RETURN indication and do the test again.
6. Push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
5. Close-up
________
Subtask 32-46-00-860-064
A. Put the aircraft back to its initial configuration.
(1)
On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.
(2)
Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).
(3)
Depressurize the Green and Yellow hydraulic systems after operation of the PTU (Ref. TASK 29-23-00-864-001).
(4)
De-energize the aircraft electrical circuits
(Ref. TASK 24-41-00-862-002).
(5)
Remove the warning notice(s).
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____________________________________________________
1. General
_______
The brake temperature system comprises:
-four temperature sensors (one chromel-alumel thermocouple per brake),
-
two brake-temperature monitoring units (one per gear), - one braking/steering control unit (BSCU). A twisted pair cable connects each brake temperature sensor to a brake-temperature monitoring unit. The brake-temperature monitoring unit processes the signals and compensates the thermocouple cold junction. The BSCU provides the indicating systems with the temperature at each of the four brakes and the BRAKE HOT warning.
A.
Temperature Sensor (Ref. Fig. 001) The chromel-alumel temperature sensor delivers a voltage proportional to the temperature difference between the cold junction and the hot junction. It is possible to obtain a signal proportional to the brake temperature if you cancel the term k theta j from the equation. The compensator resistor does this function.
B.
Brake-Temperature Monitoring Unit
(Ref. Fig. 002)
The brake-temperature monitoring unit is equipped with two printed
circuits required to:
-process the data from the temperature sensor,
-compensate the thermocouple cold junction.
-Send a voltage proportionnal to the temperature to the BSCU.
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