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霍尼韦尔报警方案霍尼韦尔报警方案报警系统5.1．系统概述安定宝电脑监控的巡更报警系统，在同一套系统、同一条线路中集成了报警与巡更系统，并且在电脑上实时监控各个报警点和巡更点，对各个报警点可以任意分区，控制其集体或单独布撤防，对巡更点可判断位置（和巡更人员），自动执行巡更计划，并且可在巡更出错时及时发出警告，提醒值班人员的注意，同时也保障巡更人员的人身安全。
安定宝电脑监控的巡更报警系统的特点是性能可靠，功能强大，安装简单，操作方便，尤其适合于象智能大厦这样需要集中控制巡更、报警信息的场合。
5.2．系统结构5.2.2．报警系统对大厦的主要区域的出入口、电梯厅、控制中心、机房、贵重物品的库房等重要部位安装门磁开关、红外探头、玻璃破碎探头、震动探测器等，由安保控制室统一监控。
同时可与CCTV系统联动，使值班人员能及时、准确地获得发生事故的信息和相关图像。
5.2.3．系统集成为方便施工布线及日后的维护，采取按楼层接线法。
即每层楼的报警、巡更布线为同一线路的不同分支，也就是所说的在同一套系统、同一条线路中集成了报警与巡更系统，并且可在电脑上实时监控各个报警点和巡更点。
5.3．具体方案如图示，每台VISTA120主机可通过两线总线连接达128个防区，这些防区可任意设置为报警点、布撤防键盘或巡更按钮（键盘），因为所有防区都是使用开关输出方式的设备，需要使用总线扩充器连接到总线上，总线扩充可使用4208U（8个防区）或4190WH/4193SN（2个防区）或4293SN （1个防区），所有扩充器都是并联在一起连接到主机，减少很多接线的麻烦。
所有防区都设置为24小时无声报警类型防区，通过软件设置来识别。
l 公共区域报警子系统是指公共区域的探测器，由多个防区组成，可以按需要通过软件设置为“布防”，“撤防”状态，并且每一个点的状态都可单独报告。
可以使用任何的探测器，如本方案中的门磁开关。
l 独立报警子系统是指一个独立的报警系统连接到监控系统中，只使用一个防区，并且只能在当地的布撤防键盘上进行布撤防操作，可以报告布撤防和报警的状态。
霍尼韦尔报警系统资料说明一、接线图1、236 plus Ⅱ2、2316 plus Ⅱ接线备注：1.警号（二芯）分正负极，红色线为正极接“BELL+”，黑色线为负极接“GND”。
2.探测器（四芯，例如：双鉴移动探测器、红外幕帘、震动探测器、等需接电源的探测设备）的供电正极接“不可关断的辅助电源”的“AUX”，负极接“不可关断的辅助电源”的“GND”;信号端不分正负但接防区的“Z”端需串接一个电阻，另一端接防区的“GND”。
3.编程键盘(三芯)的供电端“+”接“KEY+”, “_”接“GND”, 数据端“DAT”接“DATA”（数据端的负极实际是共用电源端的GDN）。
4.紧急按钮（二芯）需接常闭的两个触点，而非常开触点。
不分正负但接防区的“Z”端最好串接一个电阻（以防设备短路而烧坏主机板电路），另一端接防区的“GND”。
5.门磁（二芯）接法同紧急按钮。
6.空余防区，可接电阻（电阻一端接防区的“Z”端，一端接“GND”端），也可不接电阻。
7.移动探测器的软胶面向下安装，对着要监视的防区空间（只要检测到有人移动，LED灯就会亮，否则LED灯为灭的状态）。
8.主机箱的防拆开关引出的两根线不分正负但接防区的“Z”端最好串接一个电阻，另一端接防区的“GND”。
二、编程1.加电后，准备灯为绿色。
2.进入编程命令：按“012345*0#”，此时“准备”“布防”“服务”三灯亮，表示进入编程状态。
3.输入命令结束后按“#”结束当前项编程，继续下一项编程。
4.退出编程状态：按“*”“#”即可退出编程状态。
5.断电后在加电即可生效。
6.编程过程中，不要管指示灯的状态，只要提示音正常即可继续对下一项地址编程。
三、恢复初始值（一般用于编程混乱后使用）断电后用跳线短接“DEFAULT”的两脚不放，然后加电，大约5秒后（此时键盘灯会有变化）松开短接触点即可恢复初始值。
四、常用编程命令（以236 plus Ⅱ为例，其它型号请参考相应说明书）1.默认参数2.安装员密码编程3.用户密码编程（及布防和撤防时输入的密码）4.控制主机时间编程5.回路防区控制编程（重要）重点说明：1．某银行的探测器防区配置：1-5防区为墙面及自助机柜震动探测器，6-7防区为自助机门磁，8防区为紧急按钮，9防区为防盗门的门磁，10防区以后为红外探测器，空余防区均接了电阻。
资料范本本资料为word版本，可以直接编辑和打印，感谢您的下载霍尼韦尔(报警主机)简易编程地点：__________________时间：__________________说明：本资料适用于约定双方经过谈判，协商而共同承认，共同遵守的责任与义务，仅供参考，文档可直接下载或修改，不需要的部分可直接删除，使用时请详细阅读内容霍尼韦尔(报警主机)简易编程2316主机编程速成一、操作：布防、撤防：密码#，旁路：密码bypass旁区号 # (bypass为右下角的键)取消记忆：*1# ，复位：密码*68#C：布撤防后向中心发布撤防报告9：布撤防后不向中心发布撤防报告二、编程：1. 进入编程：０１２３４５*０ #退出编程：* #3．密码部分：０１ C __ __ __ __ # 5位,若少于5位,以*4作为1位结束,后填0；……A、B、C、D、E、F分别用相应复合键代替：A：*0B：*1C：*2D：*3E：*4F：*54.通讯部分：０Ａ 5 5 5 5 #0: 开启通讯 1：关闭通讯0 B 0 1 1 1 0 8 #2 F 0 0 0 1 0 #０C__ 六位帐号__ #填入接警中心电话号码０D__ 前６位__ __ #０E第7位_Ｅ００００#填入接警中心电话号码１１__ 前６位__ __ #１２第7位_Ｅ００００#填入遥控中心电话号码１4 __ 前６位__ __#１5第7位Ｅ００００ #5.防区部分：警号响时间：1：2分钟 2：5分钟 3：10分钟4：15分钟 5：30分钟11进入延时时间2 D 0 0 __ __ __ #退出延时时间：1：10秒 3：30秒 6： 60秒9：90秒 *2：120秒警声：1.脉冲声2.稳定声2.即时3.延时9.24小时一防区１F １ 2 １ __ __ 3 #二防区 2 0 １ 2 １ __ __ 3 #三防区 2 1 １ 2 １ __ __ 3 # 十防区 4 A １ 2 １__ __ 3 #四防区２2 １ 2 １ __ __ 3 # 十一防区 4 B １ 2 １__ __ 3 #五防区２3 １ 2 １ __ __ 3 # 十二防区 4 C １ 2 １__ __ 3 #六防区２4 １ 2 １ __ __ 3 # 十三防区 4 D １ 2 １__ __ 3 #七防区２5 １ 2 １ __ __ 3 # 十四防区 4 E １ 2 １__ __ 3 #八防区２6 １ 2 １ __ __ 3 # 十五防区 4 F １ 2 １__ __ 3 #九防区 4 9 １ 2 １ __ __ 3 # 十六防区 5 0 １ 2 １__ __ 3 #236主机编程速成操作：布防、撤防：密码＃旁路：密码bypass 旁区号 # (bypass为右下角的键)取消记忆：＊１＃复位：密码＊６８＃关键盘音：*51#例如：布防、撤防：１２３４＃旁路：１２３４ bypass ３#取消记忆：１２３４＊１＃复位：１２３４＊６８＃编程：进入编程：０１２３４５*０ #退出编程：* #密码部分：０１__ __ __ __ # 密码必须四位A、B、C、D、E、F分别用相应复合键代替：A：*0B：*1C：*2D：*3E：*4F：*5……0: 开启通讯1：关闭通讯4．通讯部分：０７１１１１１１#０８００１０００#０９０１１１００#０Ａ５３５３#０ B 六位用户帐号＃填入接警中心电话号码０ C ＃填入接警中心电话号码０ D Ｅ００００ #０ F ＃填入遥控中心电话号码１０Ｅ００００ #１２ #１３Ｅ００００ #警号响时间：1：2分钟 2：5分钟 3：10分钟4：15分钟 5：30分钟5．防区部分：11进入延时时间１Ｂ__ __ __ 1 0 0 #退出延时时间：1：10秒 2：30秒 3： 60秒4：90秒 5：120秒 6：150秒一防区１Ｄ１１１２２０ #0：即时2：延时4：24小时警声：1.脉冲声2.稳定声二防区１Ｅ１１１２２０ #三防区１Ｆ１１１２２０ #四防区２０１１１２２０ #五防区２１１１１２２０ #六防区２２１１１４２０ #238主机编程速成一、操作：布防、撤防：密码#，旁路：密码bypass旁区号 # (bypass为右下角的键)取消记忆：*1# ，复位：密码*68#例如：布防、撤防：１２３４＃旁路：１２３４ bypass ３#取消记忆：１２３４＊１＃复位：１２３４＊６８＃C：布撤防后向中心发布撤防报告9：布撤防后不向中心发布撤防报告二、编程：１．进入编程：０１２３４５*０ #２．退出编程：* #３．密码部分：０１ C １ __ __ __ __ # 密码开头必须为1，写够5位，若为4位，以*4作为1位结束；……A、B、C、D、E、F分别用相应复合键代替：A：*0B：*1C：*2D：*3E：*4F：*54.通讯部分：０Ａ 5 5 5 5 #0: 开启通讯 1：关闭通讯0 B 0 1 1 1 0 8 #2 F 0 0 0 1 #０C__ 六位帐号__ #填入接警中心电话号码０D__ 前６位__ __ #０E第7位_Ｅ００００#填入接警中心电话号码１１__ 前６位__ __ #１２第7位_Ｅ００００#填入遥控中心电话号码１4 __ 前６位__ __#１5第7位Ｅ００００ #5.防区部分：警号响时间：1：2分钟 2：5分钟 3：10分钟4：15分钟 5：30分钟11进入延时时间2 D 0 0 __ __ __ #退出延时时间：1：10秒 3：30秒 6： 60秒9：90秒 *2：120秒警声：1.脉冲声2.稳定声一防区１Ｆ１ 2 １ __ __ 3 #2.即时3.延时9.24小时二防区 2 0 １ 2 １ __ __ 3 #三防区 2 1 １ 2 １ __ __ 3 #四防区２2 １ 2 １ __ __ 3 #五防区２3 １ 2 １ __ __ 3 #六防区２4 １ 2 １ __ __ 3 #七防区２5 １ 2 １ __ __ 3 #八防区２6 １ 2 １ __ __ 3 #。
霍尼韦尔报警123VISTA120、250简易操作手册VISTAR—120简易编程操作手册一、设置6160编程键盘开机后，键盘液晶屏幕无任何显示，此时同时按1 、3键5秒，键盘显示Con Addr=31或Addr=xx，输入00按*键盘绿灯亮，显示***DISARMED***READT TO ARM键盘地址不为00时，不能编程，6148键盘不能编程二、设置每个防区在撤防状态下，才能进入编程模式输入4140 8000（4140为出厂设置的安装员密码）进入编程模式，键盘显示：Program Mode*Fill # View按*93 键盘显示ZONE PROG？1=TES 0=NO输入0 1 0，进入防区编程模式，键盘显示：ZN ZT P RC IN L001 09 1 10 HW1 此处，ZN代表防区号；ZT代表防区类型01—出入口防区1型，布防时有延时，进入时有延时，延时时间由*09和*10设定；02—出入口防区2型，布防时有延时，进入时有延时，延时时间由*11和*12设定；03—周边防区，布防时有效，撤防时无效；06—24小时无声防区；07—24小时有声防区；09—火警防区；00—无用防区。
P代表子系统；RC代表报告码，系统默认即可，无需改动；IN代表防区输入类型，1-9防区统一为01，显示为HW；10防区以后统一为06，显示为SL；L 为回路号，除了是4193SN的第二回路为2，其他都为1。
例如：编程将24防区为24小时防区则在ZN下输入024 *（下一步）在ZT下输入24防区的防区类型07（24小时放区）在P 下输入24防区所属的子系统（部分区都为1）在IN下输入06**此时，键盘显示：024 INPUT S/N :LAxxx-xxxx :1此时输入24防区地址码输入完成后按*确认，在L处选择相应的回路再按*即进入下一方的。
退出防区编程：在防区号（ZN）处输入000 *1*99 即可退出编程注意：在防区编程状态下，*代表下一步，#代表返回。
VISTAR—120简易编程操作手册一、设置6160编程键盘开机后，键盘液晶屏幕无任何显示，此时同时按1 、3键5秒，键盘显示Con Addr=31或Addr=xx，输入00按*键盘绿灯亮，显示***DISARMED***READT TO ARM键盘地址不为00时，不能编程，6148键盘不能编程二、设置每个防区在撤防状态下，才能进入编程模式输入4140 8000（4140为出厂设置的安装员密码）进入编程模式，键盘显示：Program Mode*Fill # View按*93 键盘显示ZONE PROG？1=TES 0=NO输入0 1 0，进入防区编程模式，键盘显示：ZN ZT P RC IN L001 09 1 10 HW1 此处，ZN代表防区号；ZT代表防区类型01—出入口防区1型，布防时有延时，进入时有延时，延时时间由*09和*10设定；02—出入口防区2型，布防时有延时，进入时有延时，延时时间由*11和*12设定；03—周边防区，布防时有效，撤防时无效；06—24小时无声防区；07—24小时有声防区；09—火警防区；00—无用防区。
P代表子系统；RC代表报告码，系统默认即可，无需改动；IN代表防区输入类型，1-9防区统一为01，显示为HW；10防区以后统一为06，显示为SL；L 为回路号，除了是4193SN的第二回路为2，其他都为1。
例如：编程将24防区为24小时防区则在ZN下输入024 *（下一步）在ZT下输入24防区的防区类型07（24小时放区）在P 下输入24防区所属的子系统（部分区都为1）在IN下输入06**此时，键盘显示：024 INPUT S/N :LAxxx-xxxx :1此时输入24防区地址码输入完成后按*确认，在L处选择相应的回路再按*即进入下一方的。
退出防区编程：在防区号（ZN）处输入000 *1*99 即可退出编程注意：在防区编程状态下，*代表下一步，#代表返回。
三、设置打印机（IP-2000输出）41408000*94*70 11111*71 1*72 1*73 0*99*99四、修改安装员密码安装员密码是最高级的密码，出厂设置为4140，现以0414为例41408000*00 0414*99五、系统日常操作1、外出布防绿灯（READY）亮表示所有防区未被触发，可以外出布防，输入甲级用户密码 2红灯（ARMEO）亮，表示系统外出布防2、撤防系统在布防期间没有报警，输入甲级用户密码1，系统撤防，系统在布防期间发生报警，输入甲级用户密码 1 两遍，3、旁路防区后布防报警系统有时不需要对所有防区布防，这时需要对不设防的防区旁路，对其他防区布防，输入甲级用户密码 6 XXX（防区号）XXX（防区号）``````甲级用户密码 2报警系统有防区未准备（NOT READY）时，可以旁路未准备的防区，对其他防区布防，输入甲级用户密码 6 #甲级用户密码 2撤防后原来的旁路无效。
Honeywell 报警模块使用说明
Honeywell报警转换模块与黄金视讯的3600网络转换模块类似，通过网络转换模块将报警主机的报警与我们公司软件平台结合起来。
以下将其设置与平台配置详细说明如下：
一、 Honeywell报警转换模块连接与设置
Honeywell报警转换模块如下图，接线方法其有相应的说明书。
调试前最好与PC主机用直连网线连接，其默认IP：192.168.0.3：255.255.255.0：192.168.0.1 服务器的IP地址：192.168.0.2 端口：3000，其供电一般由报警主机供给12V
连接好后，Honeywell报警转换器有自带调试程序，
双击此程序出现以下图示：
点击“广播搜索”和“启动”后此程序会找到与PC机器相连的IP模块，这个时候可以更改其IP地址与服务器地址。
注意：服务器地址一定要改成最终接收数据的主机地址，比如CMS，NVS等地址。
二：软件配置
在所需接收IP模块信息的监控单元里面添加此设备，下面以三级结构网络分控为例：
在认证中心的配置中心里面添加好网络分控单元（NVS）后，在其监控设备里面添加ELID报警器。
如下图
NVS
监控设备
添加ELID报警器
只要更改IP模块的IP地址和输入路数，一般没有输出路数添加好后，在报警输入里面加入相应的路数，如下图：
批量增加
最后，在用户里面添加上
这样配置就完成了
三注册
把IPModule.dll和注册两个文件放到C:\ 根目录下，双击进行注册，注册后会有提示注册成功
到此，全部完成，将报警主机与IP转换模块连接后即可在软件中对其进行操作。
产品简介2 防区报警模块（VICTRIX-2 Zone Alarm Module）、6 防区报警模块（VICTRIX-6 Zone Alarm Module）是霍尼韦尔VICTRIX智能社区专业报警安防系统的组成部分。
2/6防区报警模块安装在楼层中，汇集了各防区状态信号，是为用户提供防盗、报警功能、保证居家安全的报警处理设备，它包括2/6个可编程防区。
产品特点•SMT生产工艺、抗浪涌、抗雷击、防静电。
•安装方便，反应灵敏，性能可靠。
技术参数•工作电压： DC10~18V，典型值：DC12V•通讯方式/速率：10M/100M网络•工作温度：-10℃至+55℃•外观尺寸：125x42x15（mm）•防区线尾阻：2.2千欧产品示意图：配置2、6防区报警模块：2防区报警模块配置步骤与6防区报警模块一致，本说明书以6防区报警模块为例。
1. 双击程序CmsCfgPlatform.exe.，进入如下界面：2. 点击菜单栏的【Victrix】 【广播搜索】，进入如下界面：3. 搜索到各个设备后，双击选择需要配置的设备，进入如下界面：此网络配置界面仅供查看，无法保存更改。
4. 输入正确的配置密码（初始密码为0），再点击【主机配置】，进入配置主界面，对模块进行配置：•防区类型分为：常开、常闭、EOL线尾组和监控。
•选择“一致”按键，所有防区设置将与防区1设置一致。
网络配置中“账户”和“密码”必须都为数字。
5.配置完成后，点击【确认】。
中国RoHS根据信息产业部等部委颁布的《电子信息产品污染控制管理办法》及相关标准的要求，2/6防区报警模块的相关信息如下：1.产品的环保使用期限为10年, 保证该环保使用期限的安装及使用注意事项见产品使用手册；2.产品中有毒有害物质或元素的名称及含量见下表：产品中有毒有害物质或元素的名称及含量OVICTRIX-2 2防区VICTRIX-6 6防区报警模块说明书雷恒（上海）信息技术有限公司。
MK V MK VI MK VII MK VIII MK XXIIEnhanced Ground Proximity Warning SystemsLine Maintenance ManualDocument No: 060-4199-180, Rev FRelease date: 23 Jun 2009Honeywell International, Inc. Redmond, Washington 98073-9701P R O D U C T I O N - R e l e a s e - 25 J u n 2009 15:05:03 M S T - P r i n t e d o n 18 A u g 2009This document is an unpublished work.Copyright 2005, 2009 Honeywell International, Inc.All rights reserved.This document and all information and expression contained herein are theproperty of Honeywell and is provided to the recipient in confidence on a“need to know” basis. Your use of this document is strictly limited to alegitimate business purpose requiring the information contained therein.Your use of this document constitutes acceptance of these terms.Typed signatures constitute approval. Actual Signatures are on file at Honeywell in Redmond, WA.DRAWN R. Halbert 23 FEB 00CHECKENGR R. Halbert 23 FEB 00MFGQAAPVD G. Gilliland 23 FEB 00APVDREVISIONSSHT REV DESCRIPTION DATEAPPROVEDAll Initialrelease.Reason 01 Severity 10 23 FEB 0023 FEB 00R. HalbertG. GillilandAll A Directupdate:Incorporate –008 changesReason 01 Severity 10 07 AUG 0107 AUG 01R. HendersonL. MatterAll B Direct update to incorporate EGPWC/GNSSU part numbers and troubleshooting information. Revised Level 2descriptions.Reason 01 Severity 10 13 FEB 0213 FEB 02B. BreenG. GillilandAll C Direct update to incorporate Airbus and Boeing part number changes, Revised Flight History Download Card P/Ns,reformatted TOC and added the following RAAS-relatedsections:(1) Section 2.2.15(2) “Application Software Version Invalid” and “RCD Failed”(MK V/VII) aural annunciations to Table 3-2.(3) Sections 3.8.42 and 3.8.43(4) Appendix CReason 01 Severity 10 08 JAN 0409 JAN 04J. CastroL. MatterAll D 1) Deleted “Revisions Status of Sheets Index” table onSheet 3.2) Section 3.2 (Troubleshooting Guide): Added thestatement “(this sentence does not apply to internalGPS engines)” after the existing sentence “If no faultsare present, verify that position data from the GPS, IRS,or FMC is correct”.3) Section 6.1.2 (Installation): Added step 6 to account forRAAS equipped EGPWC units.4) Appendix C:- Revised Table B1-1 to C1-1.- Revised Table B1-2 to C1-2.- Table C1-2: Added note that “Operators/Installers mustrefer to their Instructions for Continued Airworthiness(ICA) documentation to identify the approved RCDconfigurations specific to their aircraft type/model havingRAAS installed”.Reason 01 Severity 10 27 SEP 0430 SEP 04K. ChristoffersonS. WrightREVISIONSSHT REV DESCRIPTION DATEAPPROVEDAll E Section 3.3.2 – added RAAS maintenance message to short Level 1 Self-Test sequence and two notes, one to ensureRAAS messages only occur if RAAS is activated and one toexplain the GPS NOT NAVIGATING enunciation.Section 3.5 - added note to ensure RAAS message onlyoccurs if RAAS is activated.Section 6.1.2 – modified step 6 to add Level 3 Self-Test.Reason 01 Severity 10 01 FEB 0503 FEB 05S. WrightK. ChristoffersonAll F Updated per ECO-65820Updated document to include MK XXII helicopter EGPWSand to include software -230-230 changes for RAAS andnewly introduced optional functions for Stabilized ApproachMonitor, Long Landing Monitor, Altimeter Monitor, andTakeoff Flap Configuration Monitor.EFF PT: 10 23 JUN 09 J. MulkinsSee AeroPDMfor additionalapprovalsTABLE OF CONTENTS1INTRODUCTION (8)1.1S COPE (8)1.2A PPLICABILITY (8)1.3R EFERENCE D OCUMENTS (9)2DESCRIPTION AND OPERATION (10)2.1G ENERAL S YSTEM D ESCRIPTION (10)2.1.1Enhanced Ground Proximity Warning Computer (EGPWC) (11)2.2O PERATION (11)2.2.1Mode 1 – Excessive Descent Rate (11)2.2.2Mode 2A/2B - Terrain Closure Rate (11)2.2.3Mode 3 - Descent After Takeoff (11)2.2.4Mode 4A/4B/4C - Unsafe Terrain Clearance (11)2.2.5Mode 5 - Descent Below Glideslope (12)2.2.6Mode 6 - Advisory Callouts (optional) (12)2.2.7Mode 7 - Windshear Detection (Optional for MK V/VII only) (14)2.2.8Envelope Modulation (not available in MK VI/VIII -001) (14)2.2.9Terrain Clearance Floor and Runway Field Clearance Floor (14)2.2.10Terrain Alerting and Display (optional) (15)2.2.11Peaks Display Mode (optional) (16)2.2.12Geometric Altitude (GPS Required) (16)2.2.13Weather Radar AutoTilt (MK V and MK VII only) (16)2.2.14System Display and Annunciation (17)2.2.15Runway Awareness and Advisory System (option for MK V and MK VII only) (17)2.2.16Stabilized Approach Monitor (option for MK V and MK VII only) (17)2.2.17Altimeter Monitor (option for MK V and MK VII only) (17)2.2.18Takeoff Flap Configuration Monitor (option for MK V and MK VII only) (18)2.2.19Long Landing Monitor (option for MK V and MK VII only) (18)2.2.20Lamp Format (19)2.3S YSTEM M AINTENANCE (20)2.3.1Maintenance Philosophy (20)2.3.2System Operation During an Inop Condition (20)2.3.3BIT Description (20)2.3.4EGPWC Front Panel (21)2.3.5Self-Test Functions (22)3FAULT ISOLATION (TROUBLESHOOTING) (23)3.1G ENERAL (23)3.2T ROUBLESHOOTING G UIDE (23)3.3L EVEL 1S ELF-T EST -G O/N O G O T EST (24)3.3.1Self-Test Preamble (24)3.3.2Short Level 1 Self-Test (25)3.3.3Long Level 1 Self-Test (26)3.4L EVEL 2S ELF-T EST -C URRENT F AULTS (26)3.4.1Current Faults - Internal (27)3.4.2Current Faults - External (27)3.5L EVEL 3S ELF-T EST -S YSTEM C ONFIGURATION (33)3.6L EVEL 4S ELF-T EST -F AULT H ISTORY (36)3.7L EVEL 5S ELF-T EST -A LERT H ISTORY (37)3.8L EVEL 6S ELF-T EST -D ISCRETE I NPUT T EST (37)3.8.1ARINC 552 / ALT 55 Radio Altitude Validity Flag Discretes (38)3.8.2GND Landing Gear Discrete (38)3.8.3+28V Landing Gear Discrete (38)3.8.4GND Landing Flap Discrete or Flap Override (39)3.8.5+28V Landing Flap or Flap Override Discrete (39)3.8.6Flap Position Discretes (40)3.8.7Self-Test Discrete (40)3.8.8Steep Approach Discretes (40)3.8.9GND ILS Tuned Discrete (41)3.8.10+28V ILS Tuned Discrete (41)3.8.11Glideslope Validity Discretes (41)3.8.12GND Glideslope Inhibit Discrete (42)3.8.13+28 V Glideslope Inhibit Discrete (42)3.8.14GND Glideslope Cancel Discrete (42)3.8.15Decision Height Discrete (42)3.8.16Mode 6 Volume Control Discrete (43)3.8.17Callouts Enable Discrete (MK V and MK VII only) (43)3.8.18GND Audio Suppress(Inhibit)/All Modes Inhibit Discrete (43)3.8.19+28 V Audio Suppress(Inhibit)/All Modes Inhibit Discrete (43)3.8.20AOA Validity Discretes (MK V and MK VII only) (44)3.8.21Display Select Discretes (44)3.8.22Terrain Awareness & TCF Inhibit (44)3.8.23Simulator Reposition (MK V and MK VII only) (44)3.8.24Weather Radar On/Off (45)3.8.25Localizer Validity Discretes (MK V and MK VII only) (45)3.8.26Attitude Validity Discretes (45)3.8.27Airspeed Validity Discrete (45)3.8.28Barometric Altitude Rate Validity Discretes (46)3.8.29Acceleration Self-Test In Progress Discrete (46)3.8.30Longitudinal Acceleration Validity Discrete (46)3.8.31Normal Acceleration Validity Discrete (46)3.8.32Magnetic Heading Validity Discrete (47)3.8.33AOA Vane Heater Discrete (47)3.8.34PLI Deselect Switch Discretes (MK V and MK VII only) (47)3.8.35Autopilot Disconnect Discretes (47)3.8.36Tactical Select Discrete (48)3.8.37Altitude Alert Discrete (48)3.8.38Corrected Barometric Altitude Validity Discrete (48)3.8.39Momentary Flap Override Discrete (48)3.8.40Weight On Wheels Discrete (49)3.8.41GPWS Inhibit Discrete (49)3.8.42RAAS EnABLE Discrete (MK V and MK VII Only) (49)3.8.43RAAS Inhibit Discrete (MK V and MK VII Only) (49)3.8.44Stabilized Approach Monitor Enable Discrete (MK V and MK VII Only) (50)3.8.45Stabilized approach Monitor Inhibit Discrete (MK V and MK VII Only) (50)4MAINTENANCE PRACTICES (51)4.1G ENERAL (51)4.2D ATABASE U PDATE (51)4.2.1Database Update Frequency (51)4.2.2Loading a Database (51)4.3F LIGHT H ISTORY D OWNLOADING (52)4.3.1Obtaining an EGPWS Flight History Download Card (52)4.3.2Download Procedure (52)4.3.3Transcription of the PCMCIA Card (53)4.4P ROGRAMMING THE C ONFIGURATION M ODULE (MK VI,MK VIII,MK XXII ONLY) (54)4.4.1Configuration Module Reprogramming (MK VI, MK VIII, MK XXII only) (55)5SERVICING (57)5.1G ENERAL (57)6REMOVAL/INSTALLATION (57)6.1EGPWC (57)6.1.1Removal (57)6.1.2Installation (57)6.2C ONFIGURATION M ODULE (MK VI,MK VIII, AND MK XXII ONLY) (57)6.2.1Removal (57)6.2.2Installation (57)6.3D ISPLAY S WITCHING R ELAYS (IF INSTALLED) (58)6.3.1Removal (58)6.3.2Installation (58)7ADJUSTMENT/TEST (58)7.1A DJUSTMENT (58)7.2T EST (58)7.2.1EGPWS Ground Tests (58)8INSPECTION/CHECK (59)8.1G ENERAL (59)9CLEANING/PAINTING (59)9.1G ENERAL (59)10REPAIRS (59)10.1G ENERAL (59)11APPENDIX A: WINVIEWS (60)12APPENDIX B: TROUBLESHOOTING DO’S AND DO NOT’S (61)13APPENDIX C: RAAS MAINTENANCE MESSAGES (AURAL & DISPLAYED) (62)14APPENDIX D: STABILIZED APPROACH MONITOR MAINTENANCE MESSAGES (64)15APPENDIX E: ALTIMETER MONITOR MAINTENANCE MESSAGES (65)16APPENDIX F: TAKEOFF FLAP CONFIGURATION MONITOR MAINTENANCE MESSAGES (66)17APPENDIX G: LONG LANDING MONITOR MAINTENANCE MESSAGES (67)1 INTRODUCTION1.1 SCOPEThis document provides information about the Enhanced Ground Proximity Warning System (EGPWS) with respect to Line Maintenance Operations. This includes Description and Operation, Troubleshooting, Removal and Installation, Adjustment and Test, and other related information. It is intended that the information in this document be combined with detailed aircraft installation documentation for operator specific line maintenance procedures. 1.2 APPLICABILITYThis manual is applicable to the MK V, MK VI, MK VII, MK VIII, and MK XXII EGPWS with the following part numbers and general description:MK V EGPWC PART NUMBERS MK VII EGPWC PART NUMBERS 965-0976-003-XXX-XXX 115 VAC, -40° to +70°965-1076-001-XXX-XXX 115 VAC, -40° to +70°965-0976-020-XXX-XXX 115 VAC, Internal 8 channelGPS, -40° to +70°965-1076-020-XXX-XXX115 VAC, Internal 8 channelGPS, -40° to +70°965-0976-040-XXX-XXX 28 VDC, -55° to +70°965-1076-030-XXX-XXX 28 VDC, Internal 8 channel GPS, 55° to +70°965-0976-060-XXX-XXX 115 VAC, Integral GNSSU,-40° to +70°965-1076-040-XXX-XXX 28 VDC, -55° to +70°965-1676-XXX (Airbus P/N) 115 VAC, -40° to +70°965-1076-060-XXX-XXX 115 VAC, Integral GNSSU, -40° to +70°965-1690-XXX (Boeing P/N) 115 VAC, -40° to +70°MK VI EGPWC PART NUMBERS MK VIII EGPWC PART NUMBERS MK XXII EGPWC PART NUMBERS965-1176-XXX 28 VDC, -55° to +70°965-1206-XXX 28 VDC, -55° to +70°965-1590-XXX 28 VDC, Internal 8 channel GPS, -55° to +70°965-1186-XXX 28 VDC, Internal 8 channelGPS, -55° to +70°965-1216-XXX28 VDC, Internal 8 channelGPS, -55° to +70°965-1595-XXX28 VDC, Improved CPU,Internal 8 channel GPS,-55° to +70°965-1180-XXX 28 VDC, Improved CPU,-55° to +70°965-1210-XXX28 VDC, Improved CPU,-55° to +70°965-1190-XXX 28 VDC, Improved CPU,Internal 8 channel GPS,-55° to +70°965-1220-XXX28 VDC, Improved CPU,Internal 8 channel GPS,-55° to +70°TABLE 1-1 EGPWC Part NumbersNOTE: X’s represent variable values defining a specific application and configuration software version (i.e., -230-230 for MK V/VII or -011 for MK VI/VIII/XXII original model or -026 for MK VI/VIII/XXII with improved CPU).MK V & MK VII EGPWC (left) and MK VI, MK VIII, MK XXII EGPWC (right)Figure 1-1 - Enhanced Ground Proximity Warning Computers1.3 REFERENCE DOCUMENTSThe following documents are identified as additional EGPWS references:MK V and MK VII:965-0976-603.........Product Specification for the EGPWS (MK V and MK VII)060-4404-000………Product Description for Runway Awareness and Advisory System (RAAS) prior to -230-230 060-4564-000………Product Description, Flight Safety Functions of the EGPWS993-0976-401.........Interface Control Document for the Mark V EGPWS993-1076-401.........Interface Control Document for the Mark VII EGPWS060-4199-125.........Installation Design Guide for the MK V EGPWS060-4199-225.........Installation Design Guide for the MK VII EGPWS060-4241-000.........MK V and MK VII EGPWS Pilot Guide060-4267-000.........EGPWS Terrain Database Airport Coverage List (MK V and MK VII)060-4353-000.........EGPWS Terrain Database Obstacle Coverage ChartMK VI, MK VIII, MK XXII:965-1176-601.........Product Specification for the MK VI and MK VIII EGPWS (original model)965-1180-601.........Product Specification for the MK VI and MK VIII EGPWS (with improved CPU)965-1590-601.........Product Specification for the MK XXII EGPWS (original model)965-1595-601.........Product Specification for the MK XXII EGPWS (with improved CPU)993-1176-401.........Interface Control Document for the Mark VI/VIII/XXII EGPWS (original model)993-1180-401.........Interface Control Document for the Mark VI/VIII/XXII EGPWS (with improved CPU)060-4314-125.........Installation Design Guide for the MK VI/VIII EGPWS (original model)060-4314-150………Installation Design Guide for the MK VI/VIII EGPWS (with improved CPU)060-4314-225.........Installation Design Guide for the MK XXII EGPWS (original model)060-4314-250………Installation Design Guide for the MK XXII EGPWS (with improved CPU)060-4314-000.........MK VI and MK VIII EGPWS Pilot Guide060-4314-200.........MK XXII EGPWS Pilot Guide060-4326-000.........EGPWS Terrain Database Airport Coverage List (MK VI and MK VIII)2 DESCRIPTION AND OPERATION2.1 GENERAL SYSTEM DESCRIPTIONThe purpose for the Enhanced Ground Proximity Warning System (EGPWS) is to help prevent accidents caused by Controlled Flight Into Terrain (CFIT), obstacles, or severe windshear. The Enhanced Ground Proximity Warning Computer (EGPWC) accepts a variety of aircraft sensors and system inputs and applies alerting algorithms to provide the flight crew with aural messages and visual annunciations when the boundaries of alerting envelopes are exceeded. A graphic depiction of terrain and obstacles within the range selected on an EFIS or Weather Radar display may be configured for enhanced situational awareness with respect to terrain and obstacles. Figure 2-1 provides an overall system block diagram.Figure 2-1: Enhanced Ground Proximity Warning SystemThe EGPWS is comprised of the following:•Aircraft sensors and systems providing input signals•The Enhanced Ground Proximity Warning Computer (EGPWC)•Flight deck audio systems (speaker and interphone)•Alert lamps and/or EFIS or EICAS displays (for alert and system status messages)•EFIS Navigation Display (ND), Multi-Function Display (MFD), or Weather Radar Indicator for display of terrain •Switching relay(s) when required for switching display inputs from weather display to terrain display•GPS antenna for direct connection to EGPWC with internal GPS sensors2.1.1 ENHANCED GROUND PROXIMITY WARNING COMPUTER (EGPWC)All EGPWS functions are processed by a single Line Replaceable Unit (LRU) called the Enhanced Ground Proximity Warning Computer (EGPWC).The MK V and MK VII EGPWC are digitally controlled computers housed in a 2 MCU ARINC 600-6 form factor chassis intended for Air Transport type aircraft. Installation configuration is defined by program pin strapping in the aircraft.The MK VI and MK VIII EGPWC are digitally controlled computers housed in a non-ARINC form factor chassis intended for Business and General Aviation and Regional Turboprop type aircraft. These models have fewer interface and functional options. The installation configuration is defined in a programmed Configuration Module installed in the aircraft.The MK XXII EGPWC is a digitally controlled computer housed in a non-ARINC form factor chassis intended for various rotorcraft. Similar to the MK VI and MK VIII EGPWC, this model has fewer interface and functional options. The installation configuration is defined in a programmed Configuration Module installed in the helicopter.The EGPWC receives information in AC, DC, discrete, and synchro analog formats, and RS-232, RS-422, ARINC 429 or ARINC 575 digital formats. Discrete signals can be either ground or +28V discretes. The EGPWC provides discrete, audio and ARINC 429 outputs for alerts and system status, and video (ARINC 453/708) for terrain display. The EGPWC is rack mounted and does not require any forced air cooling when operated within the normal operating temperature range given in the Table 1-1.2.2 OPERATION2.2.1 MODE 1 – EXCESSIVE DESCENT RATEMode 1 provides audio and visual alerts for excessive descent rates into terrain. When the EGPWS caution alert envelope is penetrated, the message “SINKRATE” is enunciated and EGPWS alert lights illuminate. Continuing the excessive descent rate into the EGPWS warning alert envelope results in a “PULL-UP” enunciation and EGPWS alert lights illuminated. Mode 1 is desensitized to eliminate unwanted (nuisance) alerts when the EGPWS determines that the aircraft is above a Glideslope beam. In some fixed-wing applications, Mode 1 is also desensitized when Steep Approach or Flap Override is active. In helicopter applications, Mode 1 is disabled when autorotation is detected.2.2.2 MODE 2A/2B - TERRAIN CLOSURE RATEMode 2 provides audio and visual alerts for dangerously high terrain closure rates. Two sub-modes, referred to as Mode 2A and 2B, are defined. Mode 2A is active when flaps are not in the landing position and the aircraft is not on an ILS approach within ± 2 dots of glideslope center. Mode 2B is active when the flaps are in the landing position or while on an ILS approach within ± 2 dots of glideslope deviation. When the caution alert envelope is penetrated, the message “TERRAIN, TERRAIN” is enunciated and EGPWS alert lights illuminate. Continuing the high terrain closure rate into the warning alert envelope results in a “PULL-UP” enunciation and EGPWS alert lights illuminated.2.2.3 MODE 3 - DESCENT AFTER TAKEOFFMode 3 provides audio and visual alerts for excessive altitude loss after takeoff, or after a go-around from below 245 feet above ground level (AGL), when flaps and gear are not in the landing configuration. Penetrating the Mode 3 alert envelope causes the voice message “DON’T SINK, DON’T SINK” and illumination of EGPWS alert lights.2.2.4 MODE 4A/4B/4C - UNSAFE TERRAIN CLEARANCEMode 4 provides audio and visual alerts for unsafe terrain clearance with respect to phase of flight, height above ground, and speed. Three sub-modes, referred to as Mode 4A, 4B, and 4C, are defined. Mode 4A is active during cruise and approach with landing gear up. Mode 4B is active during cruise and approach with landing gear down and flaps up. Mode 4C is active during takeoff when either gear or flaps are not in the landing configuration. The aural enunciations for Mode 4A are “TOO LOW TERRAIN” or “TOO LOW GEAR” depending on airspeed. Mode 4Bprovides “TOO LOW TERRAIN” or “TOO LOW FLAPS” depending on airspeed. Mode 4C provides “TOO LOW TERRAIN”. EGPWS alert lights are illuminated during these alerts.2.2.5 MODE 5 - DESCENT BELOW GLIDESLOPEMode 5 provides audio and visual alerts for excessive glideslope deviation when the aircraft descends below the glideslope beam on front-course ILS approaches. Two levels of alerting are provided. If the aircraft is below 1000 feet AGL and gets to or exceeds 1.3 dots glideslope deviation (fly-up), a ‘soft’ (reduced volume) “GLIDESLOPE” is enunciated. Exceeding 2 dots below 300 feet AGL provides a hard (full volume) “GLIDESLOPE” enunciation. EGPWS alert lights are illuminated during these alerts.2.2.6 MODE 6 - ADVISORY CALLOUTS (OPTIONAL)The EGPWC can be programmed to enunciate Mode 6 Advisory Callouts based on menu selectable options. Mode 6 includes Altitude Awareness, Minimums/Approaching Minimums, and Bank Angle type callouts as defined foreach EGPWS model (refer to an applicable Interface Control Document or Installation Design Guide). The menu selected Advisory Callouts are defined and enabled in the installation configuration. If Altitude Callouts are not enabled, only (DH based) “MINIMUMS” callouts will be provided. The MK XXII offers a tail strike advisory for helicopters.Only aural callouts are provided for Mode 6. EGPWS alert lights are NOT illuminated for Mode 6 callouts. The following table identifies all of the Mode 6 Callouts that are available and the applicability to each model.TABLE 2-1: MODE 6 CALLOUTSMODEL CALLOUT DESCRIPTIONV VI VII VIII XXII “DECISION HEIGHT“ At descent below minimums setting (DH) •# •# # “CHECK HEIGHT” At descent below minimums setting (DH) # # # # •“ALTITUDE-ALTITUDE” At descent below minimums setting (DH) with gear up # # # # •“MINIMUMS” At descent below minimums setting (DH) •# •# # “MINIMUM” At descent below minimums setting (DH) •# •# # “MINIMUMS-MINIMUMS” Atdescent below minimums setting (DH) •••••“DECIDE” At descent below minimums setting (DH) •# •# #“APPROACHING DECISION HEIGHT” At descent below minimums (DH altitude) setting plus100 feet•# •# #“APPROACHING MINIMUMS” At descent below minimums setting (DH altitude) plus80 feet•# •# #“PLUS HUNDRED” At descent below minimums setting (DH altitude) plus100 feet•# •# #“FIFTY ABOVE” At descent below minimums setting (DH altitude) plus50 feet•# •# # “RADIO ALTIMETER” At descent below 2500 feet •# •# # “TWENTY FIVE HUNDRED” At descent below 2500 feet •# •# # “ONE THOUSAND” At descent below 1000 feet ••••# “FIVE HUNDRED” At descent below 500 feet ••••#MODEL CALLOUT DESCRIPTIONV VI VII VIII XXII500 TONE Provides 2 second 960 Hz tone at descent below 500•# •# #feetSMART “FIVE HUNDRED” At descent below 500 feet (only) during non-precision•••••approach“FIVE HUNDRED” Above field callout within 5 nm of a runway in the# •# •#database“FIVE HUNDRED ABOVE” Above field callout within 5 nm of a runway in the# •# •#database“FOUR HUNDRED” At descent below 400 feet ••••# “THREE HUNDRED” At descent below 300 feet ••••# “TWO HUNDRED” At descent below 200 feet •••••“ONE HUNDRED SIXTY” At descent below 160 feet # # # # •“ONE HUNDRED FIFTY” At descent below 150 feet # # # # •“ONE HUNDRED FORTY” At descent below 140 feet # # # # •“ONE HUNDRED THIRTY” At descent below 130 feet # # # # •“ONE HUNDRED TWENTY” At descent below 120 feet # # # # •“ONE HUNDRED TEN” At descent below 110 feet # # # # •“ONE HUNDRED” At descent below 100 feet •••••100 TONE Provides 2 second 700 Hz tone at descent below 100•# •# #feet“EIGHTY” At descent below 80 feet •# •# •“SIXTY” At descent below 60 feet •# •# •“FIFTY” At descent below 50 feet •••••“FOURTY” At descent below 40 feet •••••“THIRTY FIVE” At descent below 35 feet •# •# #35 TONE Provides 1 second 1400 Hz tone at descent below 35•# •# #feet“THIRTY” At descent below 30 feet •••••“TWENTY” At descent below 20 feet •••••20 TONE Provides 1/2 second 2800 Hz tone at descent below•# •# #20 feet“FIFTEEN” At descent below 15 feet •# •# # “TEN“ At descent below 10 feet •••••“FIVE” At descent below 5 feet •# •# # # Not currently identified in any menu option for the model indicated.2.2.6.1 EXCESSIVE BANK ANGLE CALLOUTThe Bank Angle Callout feature provides callout enunciation for excessive bank angles based on altitude and bank angle limits defined by aircraft type. It is intended to enhance situational awareness during intentional or unintentional maneuvering, and for protection against wing or engine strikes when close to the runway.When the bank angle limit is reached, the aural callout “BANK ANGLE, BANK ANGLE” is given. Follow-on aural messages are only provided when the aircraft roll angle increases an additional 20% from the previous callout. Bank Angle Callouts are enabled by the installation configuration.2.2.6.2 TAIL STRIKE CALLOUTA tail strike alert function is provided by the MK XXII for applicable rotary wing aircraft based upon Radio Altitude, Pitch Attitude, Pitch Rate and Barometric Altitude Rate. The voice message “Tail Too Low “ is provided continuously while within the alert boundary. Unique alert boundaries are provided for applicable aircraft types.2.2.7 MODE 7 - WINDSHEAR DETECTION (OPTIONAL FOR MK V/VII ONLY)Mode 7 provides the flight crew with visual and aural alerts for windshear of sufficient magnitude to be potentially hazardous to the aircraft. The system is capable of detecting severe decreasing performance shears (i.e. increasing tailwind/decreasing headwind and/or downdraft) which present an immediate danger to the aircraft. The system is also capable of detecting severe increasing performance shears (increasing headwind/decreasing tailwind and/or up draft). While these shears may not present an immediate danger to the aircraft, these shears can indicate that the atmospheric instability is such that an encounter with a severe decreasing performance shear is likely.A detected increasing performance shear will result in an aural “CAUTION WINDSHEAR” enunciation and cockpit light annunciation when enabled. A detected decreasing performance shear will result in an aural siren followed by “WINDSHEAR, WINDSHEAR, WINDSHEAR” with a corresponding cockpit warning light annunciation.2.2.8 ENVELOPE MODULATION (NOT AVAILABLE IN MK VI/VIII -001)Envelope Modulation provides improved alert protection and expanded alerting margins at identified key locations throughout the world. Due to terrain features at or near certain specific airports, normal operations have resulted in nuisance or missed alerts at these locations in the past. With the introduction of accurate position information and a terrain and airport database, it is now possible to identify these areas and adjust the normal alerting process to compensate for the condition.Modes 4, 5, and 6 are expanded at certain locations to provide alerting protection consistent with normal approaches. Modes 1, 2, and 4 are desensitized at other locations to prevent nuisance alerts that result from unusual terrain or approach procedures. In all cases, very specific information is used to correlate the aircraft position and phase of flight prior to modulating the envelopes. This function is automatic and transparent to crew operation.2.2.9 TERRAIN CLEARANCE FLOOR AND RUNWAY FIELD CLEARANCE FLOORThe Terrain Clearance Floor (TCF) alerting function adds an additional element of protection to the standard Ground Proximity Warning System for fixed-wing aircraft. It creates an increasing terrain clearance envelope around the airport runway to provide CFIT protection against situations where Mode 4 provides limited or no protection. TCF alerts are based on current aircraft location, destination runway center point position, and Radio Altitude (altitude AGL). TCF is active during takeoff, cruise, and final approach. TCF complements the existing Mode 4 protection by providing an alert based on insufficient terrain clearance even when in landing configuration.The TCF function is enhanced in all fixed-wing models (beginning with release –210-210 for the MK V/VII) with the addition of a Runway Field Clearance Floor (RFCF) alerting function. RFCF is based on current aircraft location, destination runway center point position, and Geometric Altitude or altitude Above Sea Level (ASL) relative to the destination runway. RFCF provides short landing protection for runways that are significantly higher than the surrounding terrain.。
