32-46-00
ú ú 06 Page 6 ú Dec 20/93
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757
MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. GUN 051 ú
32-46-00
ú ú 04 Page 7 ú Jan 28/02
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757
MAINTENANCE MANUAL
(2)
Thermocouple sensors installed at each of the eight main-gear-wheel brake locations supply a compensated (ambient adjusted) input signal corresponding to the sensed brake temperature, to the monitor unit.
(3)
The monitor unit provides a 0 to 5 volt output signal to the EICAS computers corresponding to the brake temperature signal from each brake.
(4)
The EICAS system then displays the brake temperatures, in numerals ranging from 0 to 9, corresponding to the brake temperature range of each brake.
(5)
The brake temperature monitor system can be tested using a self-test BITE feature. The BITE tests either the monitor indicator circuit or the sensor circuits.
(6)
If any brake temperature value should exceed 5 (above 371°C, 700°F) a BRAKE TEMP light on the flight compartment P3 panel will illuminate. This indication will extinguish when the actual brake temperature falls below 315°C (600°F).
B.
Brake Temperature Monitor Unit Buit-In Test Equipment (BITE)
(1)
The brake temperature monitor system can be tested using a self-test BITE feature. The BITE tests either the monitor indicator circuit or the sensor circuits.
(2)
A BITE control/display panel and an instruction placard are on the front face of the unit. The panel face consists of the following:
(a)
Nine red LED indicator lights. Eight brake sensor lights and one monitor unit light.
(b)
Rotary spring loaded MONITOR/SENSOR test selector switch.
1) When the selector is held in the MONITOR position, the monitoring and test logic circuits are checked. All nine LED indicator lights should illuminate.
2) Failure of the MONITOR light to illuminate indicates a control or test logic malfunction. 3) Failure of a SENSOR light and MONITOR light to illuminate indicates a sensor channel malfunction.
(c) With the selector held in the SENSOR position, the eight sensors are checked for open and short circuits. 1) If a faulted sensor is detected, the MONITOR and affected
SENSOR light(s) will not illuminate.
(3)
During the MONITOR test, the following flight compartment
indications should be displayed:
(a)
BRAKE TEMP light will illuminate.
(b)
On EICAS status page in lower unit, all eight unit brake temperatures display a 7 or greater and box and numeral will be white in color.
(4)
When performing a BITE test of the brake temperature monitor unit, always perform the MONITOR TEST prior to performing the SENSOR TEST to ensure that all monitor unit circuits are functioning properly.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. GUN 051 ú
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ú ú 04 Page 8 ú Jan 28/02
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757
MAINTENANCE MANUAL
C. Control
(1)
Provide electrical power (Ref 24-22-00).
(2)
Energize the EICAS system (Ref 31-41-00).
(3)
Close BRAKE TEMP circuit breaker on the flight compartment P11 panel.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. GUN 051 ú
32-46-00
ú ú 05 Page 9 ú Dec 20/93
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757
FAULT ISOLATION/MAINT MANUAL
BRAKE TEMPERATURE MONITORING SYSTEM
COMPONENT FIG. 102 SHT QTY ACCESS/AREA REFERENCE
BRAKE ASSEMBLY (REF 32-41-00, FIG. 101) CIRCUIT BREAKER FLT COMPT, P11
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本文鏈接地址：757 AMM 飛機維護手冊 起落架 CHAPTER 32 - LANDING GEAR 3(88)
