CFDIU Menu (SHEET 9)
Figure 013
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. NWS ANGLE 3GC: RVDT COM angle (-75 deg. < NWS ANGLE 3GC < +75
deg.),
. SSV SPOOL: LVDT spool position (-0.6 mm < SSV SPOOL < +0.6 mm).
The REFRESH key is used to refresh of the NWS parameter values, as
required.
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BRAKES AND STEERING - BITE - DESCRIPTION AND OPERATION
______________________________________________________
1. BITE and Maintenance Test
_________________________ (Ref. Fig. 001) Depending on the different phases of flight, the BSCU automatically triggers the tests below:
-Power-up test,
-Permanent test,
-Functional test: in flight with the landing gear extended until touchdown of the main gear,
-Tachometer test: rolling without brake application,
-
Permanent monitoring: during operation of the braking or steering system.
A.
Power-up Test
The BSCU has two types of reset:
-long reset
-short reset
(1)
Long reset
(a)
The conditions for triggering a long reset are :
-detection of energization subsequent to a 115V/400 Hz cut lasting 5 seconds or more, or switching of the A/SKID & NOSE WHEEL switch from OFF to ON
-and aircraft condition in STOP phase. The STOP phase corresponds to:
-MLG shock absorbers compressed
-engines shut down
-wheels at stop.
(b)
The operations performed during a long reset are:
-initialization of the microprocessors and memories (Flash if necessary, RAM, EEPROM,...)
-keeping all the BSCU outputs in the inactive state
-running of all the self-tests
-writing of the fault codes into the memory (if applicable)
-unlocking of the switching logic.
(2)
Short reset
(a) The conditions for triggering a short reset are :
-detection of energization subsequent to a 115V/400 Hz cut lasting less than 5 seconds - or a 115V/400 Hz cut lasting more than 5 seconds out of the STOP phase
- or switching of the A/SKID & NOSE WHEEL switch from OFF to ON out of the STOP phase
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BITE System - Specifications
Figure 001
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- or an auto-reset
- or return of the power supply monitoring to OK.
(b) The operations performed during a short reset are:
-initializations of the microprocessors and of the memories (RAM, ...)
-keeping all the BSCU outputs in the inactive state
-unlocking of the switching logic.
R **ON A/C 106-149, 221-299,
B. Operation of the Functional Test The functional test starts as soon as the gears are locked down. Its purpose is to do the test of the hydraulic equipment under pressure and the electronic control components of the selected BSCU system. It also monitors the availability of the automatic braking and of the nosewheel steering systems until the touchdown. This is to meet the safety requirements of a CAT III B landing. For this purpose, the BSCU sends four availability discretes to the two FMGCs. The functional tests are performed by a single system (SYS1 or SYS2), selected by the BSCU. At each flight, the BSCU changes the system performing the tests. The functional test has two parts, running on the active system:
-
the functional test of the braking system
-
the functional test of the nosewheel steering system.
(1)
Functional test of the braking system. (Ref. Fig. 002) The functional test of the braking system consists in sending successive brake application/release orders on the NORMAL system. These tests are in five successive sequences.
(2)
Functional tests of the nosewheel steering (Ref. Fig. 003) These tests are performed after the normal braking functionaltests. During these tests the BSCU generates low amplitude reference angle signals and monitors the nosewheel steering response. These tests are in five successive sequences, the fifth sequence being performed cyclically until the end of the test phase (Main Landing Gear touch down).
R (3) Not Applicable
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