2.
Component Location
__________________
(Ref. Fig. 001)
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF.
-------------------------------------------------------------------------------1WZ GPWC 88VU 128 824 34-48-34 2WZ C/B - EIS/GPWS/28VDC 121VU 212 4WZ P/BSW - GPWS/G/S 500VU 212 5WZ P/BSW - GPWS/G/S 301VU 211 7WZ P/BSW - GPWS/FLAP MODE 21VU 211 9WZ P/BSW - GPWS/SYS 21VU 211
11WZ P/BSW - GPWS/G/S MODE 21VU 211
13WZ P/BSW - GPWS/LDG FLAP 3 21VU 211
R 1EFF : 001-049, 051-060, 101-104, 1 34-48-00Page 1 1 1 Config-2 May 01/05 1 1 1CES 1
GPWS - Component Location
Figure 001
R 1EFF : 001-049, 051-060, 101-104, 1 34-48-00Page 2 1 1 Config-2 May 01/05 1 1 1CES 1
3. System Description
__________________
A. General The GPWS monitors data inputs from the navigation sensors. This information is used to provide suitable aural warnings to alert the crew of insufficient terrain clearance or excessive descent rate.
B. Warnings Warnings are generated by the Ground Proximity Warning Computer (GPWC) which is installed on the shelf 88VU, in the aft electronics rack 80VU. Aural warnings are broadcast from the cockpit loud speakers.
R **ON A/C 001-004, 051-060,
C. Digital Data Inputs (Ref. Fig. 002) The GPWC receives serial digital data inputs from the following:
-radio altimeter transceiver 1 (radio altitude)
-Air Data/Inertial Reference Unit 1 (ADIRU)
-ADR portion (barometric altitude, barometric altitude rate, computed airspeed)
-IR portion (latitude, longitude, magnetic heading)
-ILS receiver 1 (glide slope deviation, localizer deviation, selected runway heading)
-Flight Management and Guidance Computer (FMGC) (latitude, longitude, track).
R **ON A/C 001-049, 051-060, 101-104,
R Post SB 34-1147 For A/C 001-004,051-060,
C. Digital Data Inputs (Ref. Fig. 002A) The GPWC receives serial digital data inputs from the following:
-radio altimeter transceiver 1 (radio altitude),
-Air Data/Inertial Reference Unit 1 (ADIRU),
-ADR portion (barometric altitude, barometric altitude rate, computed airspeed),
-IR portion (latitude, longitude, magnetic heading),
-Multi-Mode Receiver 1 (MMR) (glide slope deviation, localizer deviation, selected runway heading),
-Flight Management and Guidance Computer (FMGC) (latitude, longitude, track).
R 1EFF : 001-049, 051-060, 101-104, 1 34-48-00Page 3 1 1 Config-2 May 01/05 1 1 1CES 1
GPWS - Inputs (Buses)
Figure 002
R 1EFF : 001-004, 051-060, 1 34-48-00Page 4 1 1 Config-2 May 01/05 1 1 1CES 1
GPWC - Inputs (Buses)
Figure 002A
R 1EFF : 001-049, 051-060, 101-104, 1 34-48-00Page 5 1 1 Config-2 May 01/05 1 1 1CES 1
R **ON A/C 001-049, 051-060, 101-104,
D. Discrete Data Inputs
R **ON A/C 001-049, 101-104,
(Ref. Fig. 003)
R **ON A/C 051-060,
R (Ref. Fig. 003A)
R **ON A/C 001-049, 051-060, 101-104,
Discrete data inputs are received from the following: - Slat Flap Control Computer 1 (SFCC) (3 and FULL flap position) - Flight Warning Computer 1 and 2 (FWC) (stall warning inhibition) - main landing gear - ECAM control panel (audio suppression) - FLAP MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides a flap abnormal condition input - SYS pushbutton switch which, when pressed (in) (white OFF legend on), overrides all the GPWS warnings - G/S MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides the glide slope mode - GPWS/G/S pushbutton switch which, when pressed (in), enables the GPWC to perform test - Weather Radar with Predictive Windshear System (WR/PWS), inhibition of GPWS aural alert each time there is a PWS aural alert.
E. Warning Outputs (Ref. Fig. 004) - two discrete outputs from the GPWC control the GPWS/G/S pushbutton switches located on Captain and First Officer main instrument panels. Each pushbutton switch is a momentary contact pushbutton switch with an illuminated split legend cap. The upper legend identified GPWS, controlled by the first output, comes on red when a ground proximity warning is generated by the GPWC for modes 1 to 4. The lower legend identified G/S, controlled by the second output, comes on amber when a glide slope (Mode 5) advisory alert is generated by the GPWC. The pushbutton switch provides a facility to cancel a glide slope warning, if in progress, or to initiate a GPWS self-test.
R 1EFF : 001-049, 051-060, 101-104, 1 34-48-00Page 6 1 1 Config-2 May 01/05 1 1 1CES 1R GPWS - Inputs (Discretes) R Figure 003 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320飞机维护手册 AMM NAVIGATION 导航4(53)
