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 1.  General_______
 A.  The brake temperature monitoring system indicates to the captain and first officer the actual temperatures of each main gear brake, and alerts them to a brake high temperature condition.
 B.  Brake temperatures are monitored continuously by individual sensors (thermocouples) in each of the eight main gear brakes. The individual brake temperature signals are received by the Brake Temperature Monitor Unit, and transmitted by separate circuit to the two EICAS (Engine Indicating and Crew Alerting System) computers. The two computers are connected in parallel for redundancy.
 C.  The individual brake temperatures are displayed on the status page of the flight compartment EICAS module on the pilot's P2 panel.
 D.  A high temperature condition in any brake will illuminate a BRAKE TEMP light on the first officer's P3 panel.
 E.  The Brake Temperature monitor unit includes monitor test and sensor test BITE features. The unit also compensates for ambient temperature, at the negative input of the sensor.
 2.  Component Details_________________
 A.  Brake Sensors (Fig. 1)
_____________
 (1)  
One sensor is installed in each of the 8 main landing gear brakes. The function is to sense temperature and supply the monitor unit with a voltage input that is proportional to brake temperature. The sensor is a chromel-alumel thermocouple encased in an inconel mesh sheath attached to a stainless steel housing and electrical connector. The connector has chromel and alumel receptacles that mate with chromel and alumel pins in the airplane connector. Each sensor is connected by a pair of thermocouple wires enclosed in conduit to junction boxes on the lower end of each main landing gear shock strut.

 B.  
Brake Temperature Monitor Unit (Fig. 1)

______________________________
 (1)  
The monitor unit is located in the E6 Aft Equipment Center. It has two plug-in printed circuit boards mounted internally which contain the system electronic circuitry. Nine light emitting diodes (LED), and a spring return test switch are mounted on the front panel of the monitor to provide test indication of the monitor unit and sensor circuit integrity.

 (2)  
The monitor unit senses brake temperature signals from the sensors, and produces outputs which activate various temperature indicators on the airplane.

 (a)  
Continuous brake temperature signals are provided to the EICAS system for display on the flight compartment P2 panel. 1) Temperature values range from 0 to 9 on the display

 corresponding to a brake temperature range of 100 to 650°C (212 to 1202°F).
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MAINTENANCE MANUAL

FWD
SEE A BRAKE
A
A MAIN GEAR BRAKE
BRAKE TEMPERATURE SENSOR
T591 NO. 1 BRAKE TEMP SENSOR
(TYPICAL-8 PLACES)
A-A
A
SENSOR
FASTENER
(2 PLACES)

PLACARD
BRAKE ASSEMBLY (REF) ELECTRICAL CONNECTOR
FWD
Brake Temperature System Component Location
Figure 1 (Sheet 1)

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MAINTENANCE MANUAL

INDICATOR LIGHT
SELECTOR
MONITOR BRAKE TEMPERATURE 
MAINTENANCE INSTRUCTIONS R 8765 432 SENSOR TESTTEST MONITOR MONITOR GEARGEAR L SENSORS 1 

AFT EQUIPMENT CENTER  BRAKE TEMPERATURE 
(E6 RACK)  MONITOR UNIT 

 

Brake Temperature Monitoring System Component Location
Figure 1 (Sheet 2)

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MAINTENANCE MANUAL

 2)  The indicated numbers are displayed with a surrounding box. Either or both the digits and boxes can be shown in blue or white color, dependent on the temperature condition. The color blue indicates a normal condition and white either a threshold or high temperature condition.
　
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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(86)