(2)
Static correction evaluation During the retraction phase, there is a comparison between the controlled pressure and the pressure read by each pressure sensor. Any deviation detected between these two values is memorized in the form of a servovalve control-current shift in EEPROM. The static correction of the control current of each servovalve is then applied when the brake system is pressurized in order to avoid braking jerks at pressure rise, before application of a dynamic correction (closed loop).
**ON A/C 106-149, 221-299,
E. Braking during Landing Gear Retraction
(1) Principle In order to ensure main gear wheel braking before landing gear retraction, a braking pressure command is sent to the Normal braking system when landing gear retraction is commanded.
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
F. Pedal Artificial Feel The artificial feel at the pedals is identical in the Normal and Alternate braking modes. The master cylinders of the Alternate system give the artificial feel (master cylinder spring + pressure in the master cylinder). The pressure supplied to the brakes in the Normal mode is in relation to the pedal load/angle.
1EFF : 001-049, 051-099, 101-149, 151-199, 1 32-42-00Page A40 1201-299, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1 **ON A/C 001-049, 051-060, 101-101,
5. Test
____
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
A. Power-up Tests Initialization and Cockpit Repercussions
(1)
Conditions of power-up tests initialization
-de-energization time of computer: 5 s.
-A/C configuration:
-whatever the A/C configuration on ground.
(2)
Progress of power-up tests
-Duration: < 5 s.
-Cockpit repercussions directly linked to power-up test accomplishment:
-BSCU ECAM warnings, audio warning, pushbutton flashing.
(3)
Results of power-up tests (cockpit repercussions, if any, in case of test passed/tests failed).
(a)
Tests passed:
-All warnings and indications disappear after 5 s.
(b)
Tests failed:
-
ECAM MAINTENANCE:
-At least one BSCU ECAM warning remain displayed
NOTES:
In case of double BSCU failure: MASTER CAUT light on red and
single chime.
-
ECAM warning:
-BRAKES A/SKID NWS FAULT.
-
ECAM WHEEL page: 1* STEERING and A/SKID in amber, 2* if AUTO/BRK selected: AUTO BRK in amber.
1EFF : 001-049, 051-099, 101-149, 151-199, 1 32-42-00Page A41 1201-299, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1
BSCU Failure Categories R Figure 067
1EFF : 001-049, 051-099, 101-105, 151-199, 1 32-42-00Page A42 1201-220, 301-399, 1Config-1 Aug 01/05 1 1 1CES 1 NORMAL BRAKING - DESCRIPTION AND OPERATION
__________________________________________
1. General
_______
(Ref. Fig. 001)
The braking is normal:
-
when the Green high pressure is available,
-
when the A/SKID & NOSE WHEEL control switch is in the ON position,
-and when the PARK BRK control switch is in the OFF position or the PARK BRK control is in the ON position and the parking brake pressure really applied is less than 35 bar (507 psi).
The control is electrical and the Normal braking uses the first set of brake pistons.
1EFF : 401-499, 1 32-42-00Page 1 1 1 Config-2 Aug 01/05 1 1 1CES 1
Normal Braking Schematic
Figure 001
1EFF : 401-499, 1 32-42-00Page 2 1 1 Config-2 Aug 01/05 1 1 1CES 1
2. Component Location
__________________
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL | ZONE| ACCESS| ATA | | | | DOOR | REF. -------------------------------------------------------------------------------
9GG XMTR UNIT-BRK PEDAL 121 811 32-42-47
10GG BSCU 94VU 122 811 32-42-34
11GG PRESS XDCR-NORM BRK WHEEL 1 731 32-42-21
12GG PRESS XDCR-NORM BRK WHEEL 3 741 32-42-21
13GG PRESS XDCR-NORM BRK WHEEL 2 731 32-42-21
14GG PRESS XDCR-NORM BRK WHEEL 4 741 32-42-21
15GG SERVO VALVE-NORM BRK WHEEL 1 731 32-42-48
16GG SERVO VALVE-NORM BRK WHEEL 3 741 32-42-48
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM LANDING GEAR 起落架6(100)
