737 AMM 飞机维护手册 通讯描述和操作(159)

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WARNING:  DO NOT OPERATE WEATHER RADAR WHILE AIRPLANE IS BEING REFUELED OR DEFUELED AND DO NOT OPERATE IN ANY RADIATING MODE WHILE A FUELING OPERATION IS BEING CONDUCTED WITHIN 300 FEET OF THE ANTENNA OR AN EXPLOSION MAY OCCUR.
PERSONNEL MUST NOT ENTER AN AREA CLOSER THAN 50 FEET IN FRONT OF A RADIATING ANTENNA OR INJURY TO PERSONNEL MAY OCCUR.
CAUTION:  WHEN WEATHER RADAR IS OPERATED IN ANY MODE OTHER THAN STANDBY OR TEST, DIRECT NOSE OF THE AIRPLANE SO FORWARD 180-DEGREE SECTOR IS FREE OF LARGE METALLIC OBJECTS (HANGARS, TRUCKS, OTHER AIRPLANES, ETC.) FOR A DISTANCE OF 300 FEET AND TILT ANTENNA UPWARD 15 DEGREES OR DAMAGE TO RECEIVER MAY OCCUR.
2.  Remove Control Panel
A.  On Sperry Primus 90, open WEATHER RADAR AC and DC circuit breakers on P18-1 circuit breaker panel and tag with DO-NOT-OPERATE identifiers.
B.  On Collins WXR-700X, open WEATHER RADAR AC circuit breakers on P18-1 circuit breaker panel and tag with DO-NOT-OPERATE identifiers.
C.  Pull control panel forward for sufficient access to mating connector.
D.  Disconnect electrical mating connector and remove control panel from forward electronic panel.
3.  Install Control Panel
A.  Connect forward electronic panel electrical mating connector to control panel.
B.  Install control panel in electronic panel and secure.
C.  On Sperry Primus 90, remove circuit breaker DO-NOT-OPERATE identifiers and close WEATHER RADAR AC and DC circuit breakers on P-18-1 circuit breaker panel.
D.  On Collins WXR-700X, remove circuit breaker DO-NOT-OPERATE identifiers and close WEATHER RADAR AC circuit breakers on P18-1 circuit breaker panel.
E.  Check that control panel lights come on.
NOTE: Check that flight deck panel lights are on bright.
E.  On airplanes with Sperry Primus 90,
perform operational test in weather radar system A/T (Ref 34-41-0).

F.  On airplanes with Collins WXR-700X,
perform operational test in weather radar system A/T (Ref 34-41-02).

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Feb 20/89 34-41-61 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

GROUND PROXIMITY WARNING SYSTEM - DESCRIPTION AND OPERATION
1.  General
A.  The ground proximity warning system (GPWS) provides the pilots with aural and visual warning of potentially dangerous flight paths relative to the ground. The GPWS processes radio altitude information from the No. 1 low range radio altimeter (LRRA), mach signal and altitude rate information from the central air data computer (CADC) glide slope deviation information from VOR/ILS system and landing gear and landing flap position signals to provide warnings of the following hazards:
(1)  
Excessive rate of descent (Mode 1).

(2)  
Level flight or too shallow climb towards rising terrain (Mode 2).

(3)  
Takeoff altitude loss (Mode 3).

(4)  
Unsafe terrain clearance (Mode 4).

(5)  
Excessive deviation below the glide slope (Mode 5).

(6)  
On GUN ALL, descent below decision height (DH) (Mode 6).

B.  The GPWS consists of a ground proximity computer, two warning lights labeled PULL UP, two glide slope warning indicator/inhibit switches labeled BELOW G/S, a ground proximity warning control module, and On GUN ALL, a warning speaker. On XIA ALL, the GPWS aural warnings are audible over the flight interphone speakers (Ref 23-52-0). Equipment location is shown in Fig. 1.
C.  Primary power for the system is 115 volts ac supplied from the essential radio bus in panel P18 through a circuit breaker labeled GND PROXIMITY WARN. The warning indicator lights receives 28 volts dc power from the master dim and test system (Ref Chapter 33).
D.  26 volts ac is also received from the central air data system as a reference voltage for the altitude rate circuits.
2.  Computer
A.  The ground proximity warning computer (GPWC) is rack-mounted on shelf No. 4 of electronic equipment rack E2. The GPWC consists of a logic and power supply module, a comparator and closure warning, audio, voice, glide slope, monitor, and self test modules. A power transformer and an interference capacitor are also mounted in the rear of the chassis above the electrical connector.
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Feb 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-42-01 Page 1 

K88869
Ground Proximity Warning System Component Location  501 
34-42-01  Figure 1  Feb 20/89 
Page 2 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

3.  GPWS Warning Lights (Fig. 1)
A.  A rectangular shaped red warning light labeled PULL UP is installed on the captain's and first officer's instrument panels. Access to the bulbs within the light assembly is provided by removing the lens cover.
　
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