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 ALL  05 Page 402  Aug 25/8534-44-02
 AF TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) -
___________________________________________________
 AF DESCRIPTION AND OPERATION
_________________________ AF 1. _______
General AF A. The Traffic Alert and Collision Avoidance System (TCAS) keeps AF surveillance on proximate airplane traffic and supplies safe separation AF between your airplane and other airplanes, that have ATCRBS or Mode S AF transponders, in the event of flight path conflict. AF B. One TCAS system is installed on the airplane. The TCAS system consists AF of one TCAS computer, two phased array directional antenna, and a control AF unit (ATC control panel). TCAS information is shown on the captain's and AF first officer's RA/TA VSI (Resolution Advisory/Traffic Advisory Vertical AF Speed Indicator). AF C. TCAS interrogates proximate airplanes and receives the altitude and other AF data from the intruder airplane via Air Traffic Control (ATC) system. AF The TCAS computer will analyze the data and determine if the intruder AF airplane pose a threat to your airplane. If there is a potential threat, AF TCAS will issue resolution advisories which will instruct the pilot to AF avoiding the conflict. If there is no threat the TCAS will track the AF intruder airplane's position. AF D. TCAS operates in two modes: TA ONLY mode which only tracks the proximate AF airplane traffic and TA/RA mode which tracks intruder airplanes and issue AF resolution advisories. AF E. The TCAS uses this equipment (Fig. 1): AF (1) TCAS Computer AF (2) Two Phased Array Directional Antennas AF (3) A Mode S Transponder System that has this equipment: AF (a) One Mode S Transponder (ATC No. 1) AF (b) A TCAS/ATC Control Panel AF (c) Two Omnidirectional Antennas AF F. The TCAS computer, directional antenna, and control unit are included in AF this section. Other TCAS equipment is included to a level necessary to AF understand the TCAS operation. See Chapter 34-53-00 for the ATC mode S AF operations and Chapter 34-13-00 for the RA/TA VSI operations. AF 2. _____________
TCAS Computer (Fig. 1, 2) AF A. The TCAS computer is located in the main equipment center on the AF electronic equipment rack, E3-4. The TCAS computer receives its primary AF power from the 115V AC Essential Instrument Bus. AF B. The TCAS computer reads and keeps this information about your airplane: AF (1) Heading AF (2) Radio altitude AF (3) Mode control requests and traffic display control inputs from the AF Mode S Transponder AF (4) Mode S identification code AF (5) Maximum airspeed data AF (6) Landing gear level position AF (7) AIR/GND relay switch status AF (8) Advisory delay discrete inputs AF C. The TCAS gets heading data from the MHRS selected by the captain's source AF select switch. Heading data used with the pressure altitude data lets AF the TCAS find your airplanes position, altitude and flight path.
 EFFECTIVITY
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 F71270
..........................................................................................................AF

FIRST OFFICER'S  TOP TCAS ANTENNA 
INSTRUMENT PANEL  STA 450 
SEE  D  TCAS SPEAKER OVERHEAD PANEL  SEE  C 

CAPTAIN'S BOTTOM TCAS ANTENNAINSTRUMENT STA 450
PANEL SEE C
SEE D TCAS COMPUTER SEE B TCAS ANTENNAS
PILOTS'
CONTROL STAND

SEE A
OFF ON
ATC RPLY

123
XPNDR ALT RPTG
TA
a
CT

IDNT 456 2 FAILA
C
ABV STBY S N TEST
1

7 0 CLR
TA ONLYBLW TCAS
TA/RA

ATC/TCAS CONTROL UNIT
A

PASS TTR
FAIL X PNDR UPPER ANT LOWER ANT RAD ALT HDNG R/A
TEST SWITCH T/A
TESTTTR-920
TCAS COMPUTER
B

Traffic Alert and Collision Avoidance System Component Location Figure 1 (Sheet 1)
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 F71536
..........................................................................................................AF

0-RING
SEALANT
TCAS ANTENNA

Traffic Collision Avoidance System Component Location
Figure 1 (Sheet 2)

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...........................................................................................................AF

TCAS CPTR
TCAS Schematic Figure 2
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 AF D. TCAS receives radio altitude from the No. 1 and 2 radio altimeter. TCAS AF normally uses the No. 1 radio altimeter. If the No. 1 radio altimeter AF fails, TCAS automatically switches to the No. 2 radio altimeter. TCAS AF uses the radio altitude to set sensitivity levels and to calculate AF intruder advisories and to set low altitude inhibits. AF E. The RA/TA VSI switch controls the TCAS traffic display ranges shown on AF the RA/TA VSI. AF F. The mode control data from the ATC control panel sets the mode of AF oepration for the TCAS computer. AF G. The Mode S identification code comes from the ATC mode S transponder. AF The identification code is permanently encoded in the airplane with wire AF straps in the 24 discrete bit strapped inputs to the transponder. The AF Mode S identification code is used by the TCAS computer during collision AF avoidance routines with intruders. AF H. The maximum airspeed data is used in RA calculations and to make a AF projection of the maximum rate that two airplanes can come together. AF I. The AIR/GND input tells TCAS whether your airplane is in-flight or AF on-ground. TCAS operation is inhibited on ground, and testing is not AF inhibited on air. TCAS also uses the AIR/GND discrete to increment AF flight legs in the TCAS flight history when the CMC fails. AF J. The landing gear position and radio altimeter inputs tell TCAS that the AF airplane is preparing for a landing. TCAS will not give the "Increase AF descend" voice command during landing. Also, the bottom TCAS antenna AF performs as an omnidirectional antenna when the landing gear is down. AF K. The advisory-inhibit signals suppress RA and TA indications if ground AF proximity warning occurs (TCAS OFF shown on RA/TA VSI), and suppress TCAS AF aural annunciations only if a glide/slope advisory occurs (TA only shown AF on RA/TA VSI). AF L. The TCAS program pins set the audio level of voice outputs, the climb AF resolution advisories inhibit at an altitude of 30,000 feet, and the AF self-test function in air mode. AF M. If a failure is found on any of these system failure inputs, the TCAS AF FAIL indication is displayed on the RA/TA VSIs. AF (1) Failure inputs from the mode S transponder, radio altimeters, and AF pressure altitude from CADC. AF (2) Continuity failure in the TCAS antenna or antenna cables. AF (3) Failure data or data leakage on the ARINC 429 data bus from the AF mode S Transponder. AF (4) Internal TCAS computer failures and failure of internal power AF supplies. AF (5) Incorrect data from the radio altimeter. AF (6) Failures that occur in the TCAS computer/transponder rf loop-around AF test. AF (7) If a failure makes the TCAS operate unsatisfactorily, the TCAS AF computer stops all TCAS operations and shows the applicable AF indication on the front panel of the TCAS computer. AF N. The TEST switch on the TCAS computer starts a self-test that operates as AF follows: AF (1) All of the LED indicators are normally off. AF (2) Push the TEST button on the front panel of the TCAS computer. AF (3) All of the LED indicators come on.
　
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本文鏈接地址：747飛機(jī)維護(hù)手冊(cè)AMM CHAPTER 34 - NAVIGATION 第34章導(dǎo)航4(32)