Continental
Rev. 12/01/00 #29 Flight Manual
Ground Proximity Warning System
The ground proximity warning system (GPWS) interfaces with the radio altimeter, CADC, landing gear lever switch, VOR/LOC/GS receiver, and flap position switch. The system utilizes radio altitude, barometric rate (vertical speed), Mach, DH, and glideslope deviation information to determine adverse proximity to the ground.
The system provides warning annunciations for the following conditions: excessive rate of descent; excessive terrain closure rate, altitude loss after takeoff, descent in wrong configuration, descent below the glideslope, and descent below DH. A GPWS warning light or a BELOW G/S warning light, located on the Captain’s and F/O’s instrument panel, will illuminate, accompanied by aural annunciation, to advise the crew of adverse proximity to the ground. The GPWS does not operate on Emergency Power.
The GPWS computer provides an additional warning applicable to the decision height warning system. A vocal annunciation, “MINIMUMS-MINIMUMS” is generated whenever the airplane passes through the selected DH as set by the DH “bug” (between 1000 feet to 50 feet). The mode will not function again until 1000 feet or 50 feet AGL has been transitioned.
Radio Altimeters
Two radio altimeters, radio altimeter 1 and radio altimeter 2, are installed in the airplane. A radio altimeter indicator on the Captain’s instrument panel provides radio altimeter 1 indications, and a radio altimeter indicator on the F/O’s instrument panel provides radio altimeter 2 indications. Each indicator provides radio altitude indications to a maximum of 2500 feet AGL.
During an ILS approach, the radio altimeters actuate the rising runway symbol on the respective ADI at approximately 200 feet AGL. A SET/TEST knob on each indicator permits preselection of a desired decision height (DH) that is set in a digital readout. Each radio altimeter has a test function that is activated when the respective SET/TEST knob is pushed. Each indicator contains a DH light that illuminates at 2500 feet and when the airplane reaches the selected DH. The function of the DH light on the Captain’s ADI is associated with the function of the DH light on the Captain’s radio altimeter indicator, and the function of the DH light on the F/O’s ADI is associated with the function of the DH light on the F/O’s radio altimeter indicator. Radio altimeter 1 and 2 interface with DFGC 1 and 2. The Radio Altimeters do not operate on Emergency Power.
Air Traffic Control Transponders
Two ATC transponders are installed. One control panel allows selection of either transponder, ATC 1 or ATC 2, for transmission. The other transponder remains in a standby status. The control panel also contains controls for function and mode selection, and test and altitude reporting.
Altitude information for ATC 1 is provided by CADC 1, and altitude information for ATC 2 is provided by CADC 2. The transponders do not operate on Emergency Power.
Flight Recorder
The flight recorder is a digital flight data recorder (DFDR). The DFDR stores the last 25 hours of flight operations on a crash survivable magnetic tape.
The Flight Recorder operates when the aircraft is inflight - or - if on the ground, the recorder operates if the Parking Brake is released and at least one Fuel Control Lever is ON. The flight recorder does not operate on Emergency Power.
A FLIGHT RECORDER OFF light illuminates when the recorder is not powered or has malfunctioned.
Continental
Rev. 12/01/00 #29 Flight Manual
TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM
General
The traffic alert and collision avoidance system (TCAS) is an aircraft-based system that provides information, independent of ground stations, on the status of nearby traffic within a specified range. By interrogating other aircraft transponders, the system analyzes the replies to determine range, bearing, and if reporting altitude, the relative altitude of the intruder. Should the system processor determine that a possible collision hazard exists, it issues visual and audio advisories to the crew for appropriate vertical avoidance maneuvers. TCAS is unable to detect any aircraft without an operating transponder.
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本文鏈接地址：MD-80 Flight Manual 麥道80飛行手冊 2(178)
