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b737
飞机
航线
勤务
工作
系统故障
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钻研
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B737飞机航线勤务工作及滑油系统故障研究,b737,飞机,航线,勤务,工作,系统故障,研究,钻研
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Section 14 - Onboard Maintenance System (OMS) & Basic TroubleshootingOnboard Maintenance System (OMS)Functional Architecture:The Onboard Maintenance System (OMS) on the A380 is hosted in the Network Server System (NSS) and supplies maintenance functions for: The aircraft systems (Avionics World) The Avionics domain of the NSS (Open World)It is linked to the avionics systems through two Secure Communication Interfaces (SCI) which are secured gateways between the Avionics world and the Open World.The OMS includes maintenance software applications that support aircraft maintenance tasks. The maintenance operators can get access to this data through HumanMachine Interfaces (HMI). The OMS can also communicate with ground stations through datalinks.The OMS is designed to support line & hangar maintenance activities and engineering follow-up by providing the following functions: Failure detection/reporting Dispatch Repair Servicing Maintaining continued Airworthiness Managing aircraft configurationHuman Machine Interfaces (HMls) The maintenance applications are accessed and controlled through I-IMIs. These are as follows: Onboard Maintenance Terminal (0MT) CAPT & F/O Onboard Information Terminals (01 T) Portable Multipurpose Access Terminals (PMAT) Main and upper deck Forward Attendant Panels (FAP) PrinterOMS - FUNCTIONAL ARCHITECTUREOnboard Maintenance System (OMS) Applications System DescriptionThe OMS is divided into 3 sub-systems, which are hosted in the two Aircraft Network Server Units Operations (ANSI-JOPS) of the NSS Avionics domain. They record and exchange data through a maintenance shared database. The maintenance data is received through the SCIs and the Central Data Acquisition Module (CDAM).The three OMS sub-systems are:The Central Maintenance System (CMS), which identifies, centralizes and records system faults.The Data Loading & Configuration System (DLCS), which controls the data loading operations and aircraft configuration.The Aircraft Condition Monitoring System (ACMS), which supports preventive maintenance and in-depth investigation.The OMS also contains the following applications:Electronic Logbook for crew and maintenance personnel reportingPower Distribution Control System (PDCS), which controls and monitors circuit breaker status.Maintenance documentation (AirNv) OMS Post Flight ReportCIB = Circuit BreakersOMS - APPLICATIONSCMS Data Recording During a FlightDuring a flight, maintenance data received by the CMS are recorded in a time frame defined by several criteria. The CMS data recording is launched if:Three or more engines are running plus 180 secs (3 minutes) and,Calculated Air Speed (CAS) higher than 180 kts or a new flight number has been entered by the pilots. The CMS data recording is stopped when:Less than 3 engines are runningCAS lower than 80 kts for 150 secs (2.5 minutes).Onboard Maintenance Terminal (OMT)LocationThe Onboard Maintenance Terminal (0M T) is located at the rear the flight deck, behind the First Officers seat.FunctionThe OMT allows the operator to log on and get access to the Network Server System (NSS). If the operator logs on as a maintainer, he will gain access to the OMS home page.Troubleshooting OverviewTypes of FaultsThere are two types of basic faults as follows: BITE Faults None-BITE FaultsBite FaultsBITE faults are detected by the electronic systems and include the faults detected by the Engine Electronic Controller (EEC). The EEC sends fault messages to the CMS for the following: Channel A & B FADEC system faults EEC Internal faults Aircraft faults detected by the EEC Thrust Reverser faults detected by the EEC Thrust Reverser faults detected by the Electrical Thrust Reverser Actuation Controller (ETRAC). Engine Monitoring Unit (EMU) detected faults.The BITE fault message is displayed on the maintenance terminal and the Status, if applicable, is displayed on the ECAM.None-BITE FaultsNone-BITE faults are the faults detected by the flight crew, maintenance, or condition monitoring. The faults include observations such as high oil consumption and module performance shifts.There are no fault messages but the faults are reported in the tech log and can be reported by condition monitoring. The Status, if applicable, is displayed on the ECAM.BITE Fault DetectionThe following illustration defines the BITE fault detection used on the Trent 900 in the A380-800.Fault ClassificationIntroductionThere are a total of six fault classifications on the A380. The Flight Warning System manages Class 1 and Class 4 failures only. The other failures classes are managed by the Central Maintenance Function. The fault classifications are as follows:Class O FailuresFailure message where the operational effect of a detected failure is not known by the monitoring unit (class-less failure message).Class 1 FailuresAny detected failure generating a Flight Deck Effect (FDE) is covered by a class 1 failure message transmitted to theCMF. The FDE may be an ECAM warning, caution or advisory local warning flag on an instrument or an EFIS or ECAM displayThe FWS computes the alerts associated to Class 1 failures together with any abnormal procedure checklist. Class 2 Failures: not used anymoreClass 3 Failures:Any detected failure generating a Cabin Effect and with neither safety nor Airworthiness Authority regulation involvement (passenger comfort only).Class 4 FailuresAny failures which are categorised as Long Time Dispatch failures. Maintenance message (class 4) and LTD set flag sent to the FWS. Maintenance have 500 hours to rectify these faults.The warning for these faults is not sent immediately, but the FWS increments a timer during flight hours while EEC is sending its LTD set flag. When the timer saturates (200 hours) the FWS sets a warning. Dispatch allowed by the MMEL for the remaining period (300 hours). Once the warning is set, it can only be cleared by a specific clear flag sent by the EEC. This is sent when the fault confirmation test is carried out and it fails to detect the fault.Class 5 Failures:Any detected failures with neither Flight Deck Effect nor Cabin Effect and without safety involvement or time limitation. However, when combined with one or more other failures, can generate a FDE or Cabin Effect with potential aircraft delay.Class 6 Failures:Any detected failure with neither FDE nor Cabin Effect and without any safety or time limitation, but having an impact on aircraft performances (economical consequences). This page left intentionally blankOnboard Maintenance SystemGetting Access to OMS Home PageUsing the 0M T or the Capt. Or F/0 01 Ts you can get access to the OMS Home page.On the Open World Shell System page, select Login as Maintainer and the OMS Home page will come into view.OMS Home PageIntroductionThrough the OMS Home page, you can get access to all the functions of the maintenance applications as follows: Power Distribution Control (PDCS)If available select Power Distribution Control on the OMS Home page Or on the OMS Home page select Main Functions pull-down menu and select Power Distribution ControlPost Flight Report (PFR) and Fault Detail pageIf available select Post Flight Report on the OMS Home pageOr on the OMS Home page select the Context Home page pull-down menu and select Post Flight ReportTo get access to the Fault Detail page, select a fault case on the PFR and the Fault Detail page comes into viewSystem Report TestIf available select System Report/Test on the OMS Home pageOr on the OMS Home page select Main Functions pull-down menu and select CMS System Report/TestSystem MonitoringOn the OMS Home page select Main Functions pull-down menu and select CMS System MonitoringLoad UploadingIf available select Load Uploading on the OMS Home page Or on the OMS Home page select Main Functions pull-down menu and select DI-CS Load UploadingEquipment IdentificationIf available select Load Uploading on the OMS Home pageOr on the OMS Home page select Main Functions pull-down menu and select DI-CS Equipment IdentificationCMS EngineeringOn the OMS Home page select Advanced Functions pulldown menu and select CMS EngineeringClosing OMS session on OMTMake sure that there are no windows open relating to the maintenance application.In the Context Home page pull-down menu, select ExitDrop-Down MenusAt the top of the Home page there are a number of dropdown menus as follows:Main Functions Advanced FunctionsDocumentationUtilitiesOn the drop down menu for each, there are a number of further selections which can be selected as shown on the following pages.Main Functions contd:CMSSystem MonitoringSystem Report/TestDI-CSLoad UploadingEquipment IdentificationPDCSPower Distribution ControlAdvanced FunctionsDI-CSA/C ConfigurationDownloadingReference NameRepository ManagementSoftware Pin ProgUnistallationACMSCondition MonitoringData RecordingReal Time MonitoringRefuelDocumentation:AirnavMEL/CDLAdvanced Functions:CMSEngineeringExport BoxHistory ClearPrinter Manager Task ReminderUtilities:Maintenance HistoryPost Flight ReportThe Post Flight Report (PFR) shows the faults recorded during the last flight leg correlated to the Flight Deck Effects (FDEs).On the Time Limited tab of the PFR it shows the Class 4 faults, which have a time limit before they are required to be corrected. On this page there is a column giving the time remaining before the fault must be corrected.From the PFR, the fault message can be selected on the screen and the Fault Detail page for that fault will be shown. This gives the following:Logbook entry FDE(s)Fault messageFrom the fault message on the Fault Detail page, the Trouble Shooting Manual can be TSM Fault ProceduresAn example of a typical troubleshooting procedure is attached on the following pages. The procedure follows a set format which is as shown belowJob SetupFault ConfirmationFault IsolationClose-upTASK 73-21-00-810-845-AFailure of the Hydromechanical Unit Fuel Metering Valve Torque Motor on Channel B1.Job Set-up Information2.Fault ConfirmationSubtask 73-21-00-860-096-AA.Energize the FADEC of the engine that has a fault report.(1)On the ENG section of the panel 1255VM push the ENG FADEC GND PWR pushbutton switch, and the ON legend comes on. Subtask 73-21-00-710-085-AB.Do the steps that follow to find the status of the fault.NOTE: When you disconnect fuel tubes, air can get into the fuel system. Air in the fuel system can cause related maintenance messages to be shown when you next start the engine. This air will be automatically removed during continued engine operation. The next time you operate the engine the related messages should not show, unless they are caused differently.(1)Do the engine automatic start procedure AMM 710000860812 .(2)Let the engine become stable and operate at idle for 2 minutes.(3)stop the engine AMM 710000860814 .(4)On the OMT, get access to the Fault Detail page to find the status of the fault AMM 450000860801 .(5)If the status is CONFIRMED, go to the Para. Fault Isolation.(6)If the status is NOT CONFIRMED: Do the FADEC System Test on channel B AMM 732100740901 . If the test confirms the fault, go to the Para. Fault Isolation.NOTE: If a fault has occurred again and again without being confirmed, refer to the unconfirmed faults procedure (Ref. TSM 3.Fault IsolationSubtask 73-21-00-812-027-AA.If there is confirmation of the fault:(Ref. Fig. I-IMU to EEC Channel B Wiring Schematic SHEET 1) Do the electrical checks that follow between the EEC (4000KS) and the Hydromechanical Unit (HMU) (4000KC).(1) Get access to the EEC.(a) Open the fan cowl doors AMM 711300010801 .(2)At the EEC, disconnect the electrical harness connector 4000KS-J14.(3)On the electrical harness connector 4000KS-J14:(a)Do a check of the electrical resistance between the pins that follow AMM 715000200804 : EEC ( 4000KS* ) pin J14/11 and EEC (4000KS* ) pin J14/12 (65-157 Ohms).(b)Do a check of the insulation resistance between the pins that follow AMM 715000200803 : EEC ( 4000KS* ) pin J14/11 and ground (1 Megohm minimum).(4)If the resistance values are in the specified limits: Continue this procedure at step 3.B.(5)If the resistance values are out of the specified limits:(a)Replace the EEC (4000KS* ) AMM 732134000801 and AMM 732134400801 .(b)Do the test(s) given in the Para. Fault Confirmation.(c)If the fault continues: Continue this procedure at step 3.D. -3Subtask 73-21-00-812-028-AB.If the fault continues Do the electrical checks that follow at the I-IMU (4000KC).(1)At the HMU, disconnect the electrical connector 4000KC-B.(2)On the HMU electrical connector 4000KC-B:(a)Do a check of the electrical resistance between the pins that follow AMM 71500020Q?04 : HMU (4000102) pin B/14 and I-IMIJ (4000KC* ) pin 8/15 (65-157 Ohms).(b)Do a check of the insulation resistance between the pins that follow and ground AMM 715000200803 : I-IMIJ (A-OOQK-) pin B/14 and ground (1 Megohm minimum).(3)If the resistance values are in the specified limits: Continue this procedure at step 3.C.(4)If the resistance values are out of the specified limits:(a)Replace the I-IMIJ (4000KC* ) AMM 732152000801 and AMM 73215240001 .(b)Do the test(s) given in the Para. Fault Confirmation.(c)If the fault continues: Continue this procedure at step 3.E.Subtask 73-21-00-812-029-AC.If the fault continues:(1)Do a visual inspection of the electrical harness (4313KS) between the EEC and the HMU AMM 715000200801 .(2)Do a continuity check of the electrical harness between the pins that follow AMM 715000200802 : EEC ( ) pin J14/11 and I-IMU (4000KC* ) pin B/15 EEC (40QOKS* ) pin J14/12 and I-IMU (AQOOKQ*-) pin B/14 NOTE: Make sure the electrical connectors 4000KS-J14 and 4000KC-B are disconnected for the insulation resistance checks.(3)Do a check of the insulation resistance between the pins that follow and ground AMM 71QQ0200803 : EEC (4000KS* ) pin J14/11 and ground (1 Megohm minimum) EEC ( 4000KS* ) pin J14/12 and ground (1 Megohm minimum) EEC ( 4000KS* ) pin J14/11 and EEC (APQQKS*_) pin J14/12 (1 Megohm minimum).(a)If you find a problem: Repair or replace the electrical harness as necessary AMM 715161000801 and AMM 715161400801 .Do the test(s) given in the Para. Fault Confirmation.Subtask 73-21-00-811-085-AD.if the fault continues: Look at the steps you have completed during this procedure.(1) If you have not replaced the HMU:(a)Replace the HMIJ ) AMM 732152000801 and AMM 732152400801 .(b)Do the test(s) given in the Para. Fault Confirmation.Subtask 73-21-00-811-086-AE.If the fault continues: Look at the steps you have completed during this procedure.(1) If you have not replaced the EEC:(a)Replace the EEC ( ) AMM 73213400080.1 and AMM 7321340801 (b)Do the test(s) given in the Para. Fault Confirmation.Subtask 73-21-00-811-087-AF.If the fault continues: Look at the steps you have completed during this procedure.(1) If you have not replaced the electrical harness (4313KS) between the EEC and the I-IMLJ.(a)Replace the electrical harness AMM 715161000801 and AMM 715161400801 .(b)Do the test(s) given in the Para. Fault Confirmation.4. Close-upSubtask 73-21-00-942-045-AA. Put the aircraft back to its initial configuration.(1) Make sure that the work area is clean and clear of tools and other items.(a) Close the fan cowl doors AMM 711300410801 .This page left intentionally blankEnd of Section外文翻译资料译文部分第14节-机载维护系统(OMS)&基本故障排除机载维护系统（OMS）功能架构：A380机载维护系统(OMS) 安装在网络服务器系统(NSS)中，并为以下方面提供维护功能：飞机系统(航空电子领域)网络服务器系统的航空电子领域（开放的世界）它通过两个安全通信接口(SCI)连接到航空电子系统，安全通信接口是航空电子世界和开放世界之间的安全网关。机载维护系统包括支持飞机维护任务的维护软件应用程序。维护操作人员可以通过人机交互界面(HMI)访问这些数据。机载维护系统还可以通过数据链路与地面站通信。机载维护系统旨在通过提供以下功能来支持航线和机库的维护活动和工程跟踪：故障检测/报告派遣修理勤务保持持续适航管理飞机配置 人机交互界面(HML)维护应用程序通过人机交互界面进行访问和控制。这些应用如下：机载维修终端(OMT)机长及机上资料终端(0IT)便携式多功能接入终端（PMAT）驾驶舱主面板和上面板前护板(FAP)打印机机载维护系统(OMS)应用系统描述机载维护系统分为3个子系统，它们安装在网络服务器系统航空电子领域的两个飞机网络服务器组件-操作(ANSI-JOPS)中。它们通过维护共享数据库记录和交换数据。维护数据通过安全通信接口和中央数据采集模块(CDAM)接收。三个机载维护系统子系统是：中央维护系统(CMS)，负责识别、集中和记录系统故障。数据装载与配置系统(DLCS)，它控制数据装载操作和飞机配置。飞机状态监测系统(ACMs)，支持预防性维护和深度检查。图1 机载维护系统功能结构机载维护系统还包含以下应用：机组员和维修人员报告电子日志。配电控制系统(PDC)，它控制和监控断路器的状态。维修文件(AirNv)飞行过程中的中央维护系统数据记录在飞行过程中，中央维护系统接收的维护数据记录在由多个标准确定的时间范围内。启动中央维护系统数据记录的前提是：三个或更多的发动机在运行，外加180秒(3分钟)，和飞行员已输入超过180节或新航班号的计算空速(CAS)。当下列情况下停止中央维护系统数据记录：只有不到3个发动机在运转计算空速低于80节在150秒(2.5分钟) 内。图2 中央维护系统，飞行过程中的数据记录机载维护终端(OMT)位置机载维护终端（OMT）位于飞行面板的后面，正机长座位后面。功能机载维护终端允许操作员登录并访问网络服务器系统(NSS)。如果操作员以维护人员身份登录，他将访问机载维护系统主页。图1 机载维护终端显示屏 图4 机载维护终端使用故障排除概述故障类型有两种类型的基本故障，如下：自检故障非自检故障自检故障自检故障由电子系统检测，包括由发动机电子控制器(EEC)检测到的故障。发动机电子控制器向中央维护系统发送故障消息如下：全权限数字电子控制系统A，B通道故障发动机电子控制器内部故障发动机电子控制器发现的飞机故障发动机电子控制器检测到的反推故障由电子反推作动控制器(ETRAC)检测到的故障。发动机监控组件(EMU)检测到的故障。自检故障消息显示在维护终端上，如果适当的状态会显示在飞机电子中央监控上。非自检故障非自检故障是由机组人员、维修人员或状态监测人员检测到的故障.。故障包括高油耗和模块性能变化等观测。没有故障消息，但故障报告在技术日志中，和可以通过状态监视来报告。如果适用的话，该状态将显示在飞机电子中央监控上。图5 发动机故障类型自检故障检测下图定义了在A 380-800中Trent 900上使用的自检故障检测。图6 故障自检故障分类介绍A 380上共有六种故障类型。飞行警告系统只管理1级和4级故障。其他故障类由中央维护功能管理。故障分类如下：0级故障在监视单元不知道检测到的故障的操作效果的故障消息(“无等级”故障消息)。1级故障任何检测到的故障产生的驾驶舱效应（FDE）被覆盖到一个1级的故障消息发送中央维护功能。驾驶舱效应可能是飞机电子中央监控警告、警戒或咨询。在仪表或电子飞行仪表系统或飞机电子中央监控显示器上的本地警告标志飞行警告系统计算与一级故障相关的警报以及任何异常过程检查表。2级故障不能再使用3级故障任何检测到的故障都会产生驾驶室效应，并且既不涉及安全，也不涉及适航管理局的监管(仅限于乘客舒适)。4级故障任何被归类为长时间调度故障的故障。发送给飞行警告系统的维护消息(4级)和长时间调度故障的标志。维修有500个小时来纠正这些故障。对于这些故障的警告不是立即发送，但是在飞行期间当发动机电子控制器发送长时间调度故障“标志”飞行警告系统增加一个计时器。当计时器使充满（200小时）飞行警告系统的出现警告。主最低设备清单允许的剩余时间(300小时)的调度。一旦出现了警告，则只能由发动机电子控制器发送的特定“清除标志”清除。这是在进行故障确认测试时和它没有检测到故障发送的。5级故障任何检测到的故障，既没有飞行面板效应，也没有驾驶舱效应，也不涉及安全或时间限制。但是，当与一个或多个其他故障相结合时，可以生成飞行面板效应或驾驶舱效应可能导致飞机延误。6级故障任何检测到的故障，既没有飞行面板效应，也没有驾驶舱效应，也不涉及安全或时间限制，但对飞机性能有影响（经济后果）。机载维护系统访问机载维护系统主页使用机载维护终端或机长或副驾驶机的载信息终端，您可以访问机载维护系统主页。在开放世界壳牌系统页面上，选择登录名作为维护人员，机载维护系统主页将进入视图。机载维护系统主页介绍通过机载维护系统主页，您可以访问维护应用程序的所有功能，如下所示：图7 机载维护系统登录介面 电源分配控制(PDCS)如果可用，选择机载维护系统主页上的电源分配控制或在机载维护系统主页上选择“主要功能”下拉菜单并选择电源分配控制。飞行报告(PFR)和故障详细信息页面如果可用，选择机载维护系统主页上的飞行报告或在机载维护系统主页上选择目录主页下拉菜单并选择飞行报告若要访问故障详细信息页，请在飞行报告上选择故障案例，然后查看故障详细信息页系统报告测试如果可用，在机载维护系统主页上选择系统报告/测试或者在机载维护系统主页上选择主要功能下拉菜单并选择中央维护系统系统报告/测试系统监控在机载维护系统主页上选择主要功能下拉菜单并选择中央维护系统系统监控负载上传如果可用，选择加载上载到机载维护系统主页或在机载维护系统主页上选择主要功能下拉菜单并选择数据装载和配置系统负载上传设备鉴定如果可用，选择加载上载到机载维护系统主页或在机载维护系统主页上选择主要功能下拉菜单并选择数据装载和配置系统设备鉴定中央维护系统工程在机载维护系统主页上选择高级功能下拉菜单并选择中央维护系统工程在机载维护终端上结束机载维护系统会话确保没有打开与维护应用程序相关的窗口。在目录主页下拉菜单中，选择退出机载维护系统下拉菜单在主页的顶部有一些下拉菜单，如下所示：主要功能高级功能文件使用在每个下拉菜单上，还有许多其他的选择，如下面的页面所示。主要功能：中央维护系统 系统监控 系统报告/测试数据装载和配置系统 负载上传 设备鉴定电源分配控制 电源分配控制高级功能：中央维护系统 工程 历史操作高级功能目录：数据装载和配置系统 飞机配置 下载 参考名 仓库 管理 软件Pin Prog 卸载飞机状态监控系统 状态监控 数据记录 实时监控加油文件： Airnav 最低设备清单/缺件单使用： 出口箱 打印机管理器 任务提醒飞行报告飞行报告(PFR)显示了在最后一次飞行中记录的与驾驶舱效应(FDES)相关的故障。在飞行报告的时间限制列表选项卡上，它显示了4类故障，它们在需要更正之前有一个时限。在这个页面上有一个列，给出在错误必须纠正之前的剩余时间。从飞行报告中，可以在屏幕上选择故障消息，并显示该故障的故障详细信息页。这显示了以下：日志条目驾驶舱效应故障信息从故障详细信息页面的故障消息，可以访问故障排除手册，以纠正故障。表 1 飞行报告序号日期故障描述1/32003.1.31 14:02谨慎：右燃油箱的中心泵出囗压力低2/32003.1.31 14:25日志：在巡航出现1次方向舵配平警告警告：飞行控制方向舵配平出现1次故障3/32003.1.31 17:12指示旗：交输活门出现琥珀色的交输线排故手册故障程序下面的页面附有一个典型故障排除过程的示例。该过程遵循一个设置的格式，如下所示（任务 73-21-00-810-845-A）工件设置故障确认故障隔离结朿B通道液压机械装置燃油计量阀转矩电动机故障1. 任务设置信息表 2 参考信息参考名称71- 00-00-810-810-A未确认故障AMM 450000860801访问机载维护系统主页AMM 710000860812启动发动机的程序-自动启动AMM 710000860814关闭发动机的程序AMM 711300010801开启风扇整流罩AMM 711300410801关闭风扇整流罩AMM 715000200801发动机电线束和电缆的检查AMM 715000200802电线电缆的连续性检查AMM 715000200803线束、电缆和航线可更换件(LRUs)的绝缘电阻检查AMM 715000200804航线可更换件(LRUs)的电阻检测AMM 715161000801风扇区域电缆的拆除AMM 715161400801安装风扇区域电缆AMM 732100740801FADEC系统测试（EEC的自检）AMM 732134000801移除发动机电子控制器(EEC)AMM 732134400801安装发动机电子控制器(EEC)AMM 732152000801拆除液压机械计量装置(HMU)AMM 732152400801安装液压机械计量装置(HMU)参考文献HMU至EEC通道B布线示意图12. 故障确认分任务73-21-00-860-096-A给有故障报告的发动机的FADEC供电。（1）在面板1255 VM的发动机部分，按ENGFADEC GND PWR按钮开关，打开图例。分任务73-21-00-710-085-AB. 执行以下步骤以查找故障状态。注：当你断开燃油管，空气可以进入燃油系统。燃料系统中的空
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