747-400 AMM 飞机维护手册 导航 NAVIGATION 2(163)

曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

 D.  TCAS receives radio altitude from the left or right radio altimeter. TCAS normally uses the left radio altimeter. If the left radio altimeter fails, TCAS automatically switches to the right radio altimeter. TCAS uses the radio altitude to set sensitivity levels and to calculate intruder advisories.
 E.  The traffic display control inputs from the EFIS control panel controls the TCAS traffic display formats shown on the navigation displays.
 F.  The mode control data from the ATC control panel sets the mode of operation for the TCAS computer.
 G.  The Mode S identification code comes from the ATC mode S transponder. The identification code is permanently encoded in the airplane with wire straps in the 24 discrete bit strapped inputs to the transponder. The Mode S identification code is used by the TCAS computer during collision avoidance routines with intruders.
 H.  The maximum airspeed data is used in RA calculations and to make a projection of the maximum rate that two airplanes can come together.
 I.  The AIR/GND input tells TCAS whether your airplane is in-flight or on-ground. TCAS operation is inhibited on ground, and testing is inhibited on air. TCAS also uses the AIR/GND discreet to increment flight legs in the TCAS flight history when the CMC fails.
 J.  The landing gear position and radio altimeter inputs tell TCAS that the airplane is preparing for a landing. TCAS will not give the "Increase descend" voice command during landing. Also, the bottom TCAS antenna performs as an omnidirectional antenna when the landing gear is down.
 K.  The advisory delay signals suppress RA and TA indications if windshear or ground proximity conditions occur.
 L.  The TCAS program pins set the audio level of voice outputs, the climb resolution advisories inhibit at an altitude of 48,000 feet, and the self-test inhibit in air mode.
 M.  If a failure is found on any of these system failure inputs, the TCAS FAIL indication is displayed on the Navigation Display:
 (1)  
Failure inputs from the mode S transponder, radio altimeters, and PFD/ND displays

 (2)  
Continuity failure in the TCAS antennas or antenna cables

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 34-45-00
 ALL  ú ú 03H Page 6 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 (3)  
Failure data or data leakage on the ARINC 429 data bus from the mode S Transponder.

 (4)  
Internal TCAS computer failures and failure of internal power supplies

 (5)  
Incorrect data from the radio altimeter.

 (6)  
Failures that occur in the TCAS computer/transponder rf loop-around test

 (7)  
If a failure makes the TCAS operate unsatisfactorily, the TCAS computer stops all TCAS operations and shows the applicable indication on the front panel of the TCAS computer.

 N.  The TEST switch on the TCAS computer starts a self test that operates as follows:
 (1)  
All of the LED indicators are normally off.

 (2)  
Push and hold for 2 seconds, the TEST button on the front panel of the TCAS computer.

 (3)  
All of the LED indicators come on.

 (4)  
The TTR PASS LED indicator stays on if there is no failure to the TCAS computer or other essential system that interface with TCAS .

 (5)  
The applicable LED failure indicator comes on if there is a failure. ~........................................................ | LEDs | FAILURE | .......................................................... | TTR PASS | TCAS OK (NO FAILURE) | .......................................................... | TTR FAIL | TCAS COMPUTER | .......................................................... | XPNDR | ATC TRANSPONDER OR DATA LINK| | | INTERFACE | .......................................................... | UPPER ANT | TOP TCAS ANTENNA | .......................................................... | LOWER ANT | BOTTOM TCAS ANTENNA | .......................................................... | RAD ALT | NO RADIO ALTITUDE DATA | .......................................................... | HDNG | NO HEADING DATA | .......................................................... | R/A | RA DISPLAY | .......................................................... | T/A | TA DISPLAY | 2.................…......................................1

 3.  Directional Antenna (Fig. 2)
　
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 导航 NAVIGATION 2(163)