航空英语阅读材料 - 图文

航空英语阅读材料

(飞机各主要系统概述)

ATA21 - Air Conditioning System（空调系统）

一 INTRODUCTION（介绍）

This chapter covers the air conditioning, ventilation and pressurization systems.（这一章包括了空调、通风和增压系统）The basic airflow through the pressurized part of the fuselage starts with the pneumatic system. （从引气系统开始基本的气流通过了机身的增压区域）Hot, high pressure air is supplied to two packs.（热的高压力的气体提供给PACK组件） The packs are responsible for basic temperature regulation.（PACK组件负责基本的温度调节）From the packs the air is distributed throughout the aircraft.（从PACK出来的空气被分配到飞机内）The pressurization system controls the airflow overboard to maintain the cabin pressurization within safe limits.（增压系统控制排往机外的气流以保持客舱压力在安全限制内） 二 BASIC AIR CONDITIONING SYSTEM INTRODUCTION（基本空气调节系统介绍）

The pneumatic system supplies air to each pack. （引气系统给PACK组件供气）The packs are responsible for BASIC temperature regulation. （PACK组件负责基本的温度调节）Temperature regulated pack discharge air is sent to the mixer unit.（调节好温度的空气从PACK组件出来，并供往混合组件）At the mixer unit, the air is mixed with air re-circulated from the main cabin.（在混合组件内与从客舱来的再循环气体混合） This reduces the overall bleed demand and saves fuel.（这样可以减少总的引气量并节省燃油）From the mixer, the air is distributed to the cockpit and the forward and aft cabin zones.（空气从混合组件供往驾驶舱、前客舱、后客舱）Some of the air from the pneumatic system is used for the OPTIMIZED temperature regulation system. （从引气体统来的另一部分气体用于优化温度调节系统）This hot air is mixed with the air from the mixer to adjust the temperature in each zone independently.（这部分热空气与从混合组件来的空气混合来单独的调节每个区域）The air is

distributed throughout the cabin and finally discharged overboard through the outflow valve to maintain pressurization.（空气分配到客舱，最终通过外流活门排往机外以维持增压）

三 PACK INTRODUCTION（空调组件介绍）

The Single Aisle family is equipped with two air conditioning packs located in the wing root area forward of the landing gear bay. （单通道系列的飞机在大翼根部起落架舱前部安装有两部空调组件）The packs supply dry air to the cabin for air conditioning, ventilation and pressurization.（空调组件提供干的空气用于空调、通风、增压）The main component of each pack assembly is the Air Cycle Machine.（每一个空调组件的主要部件是空气循环机）Hot air from the pneumatic system is supplied to the pack through the pack Flow Control Valve (FCV). （从引气系统来的热空气供到流量控制活门）The FCV adjusts the flow rate through the pack and is the pack shut-off valve.（流量控制活门调节通过空调组件的流量并且作为空调组件的关断活门）The pack temperature control system controls the pack outlet temperature and sets its maximum and minimum limits. （空调组件的温度控制系统控制出口温度、设定其最大和最小限制）The system includes two Pack Controllers (PCs). （系统包括两部PACK控制器）Each PC controls one pack and has two computers, one primary and one electrically independent secondary computer. （每个控制器控制一个空调组件，每个控制器都是双通道的：一个主通道和一个独立供电的次级通道）When the primary computer is operational, the system is fully functional. （主通道操作时系统有全部的功能）If the primary fails, some functions are lost as the secondary computer takes control.（主通道失效时，次级通道接替控制，但会时区一部分功能）During normal operation, the Zone Controller (ZC) sends the required pack outlet temperature to both PCs. （正常工作时，区域控制器给PACK控制器发送所需的PACK出口温度命令）To control the pack outlet temperature, the PC modulates the BYPASS VALVE and the RAM-AIR INLET doors. （PACK控制器通过调节旁通活门和冲压空气进口门来控制PACK出口的温度）For maximum cooling, the ram-air doors are fully open and the bypass valve is fully closed. （为了最大冷却冲压空气进口门全开，旁通活门全关）For maximum heating, the ram-air doors are nearly closed and the bypass valve is fully open. （为了最大制热冲压空气进口门全关，旁通活门全开） During takeoff and landing, the ram air inlet doors will be driven fully closed to stop the ingestion of foreign matter.（在起飞过程中，冲压空气进口门完全关闭以防止吸入外物）

四 ZONE TEMPERATURE REGULATION SYSTEM INTRODUCTION （区域温度调节系统介绍）

The packs supply the mixer unit. （PACK组件给混合组件供气）Three separate aircraft zones are supplied from the mixer unit: - cockpit,- forward cabin,- aft cabin.（从混合组件给不同的三个区域供气：驾驶舱、前客舱、后客舱）Two cabin recirculation fans are installed to reduce the bleed air demand and therefore save fuel. （两个循环风扇的安装可以减少供气量并节省燃油）These fans establish a recirculation flow of air from the cabin zones to the mixer unit. （从客舱到混合组件的空气通过循环风扇形成了一个循环系统）In normal operation, there are no ECAM indications associated with the cabin fans.（正常操作时，ECAM上没有相应风扇的指示）The ZC controls and monitors the temperature regulation system for the cabin zones. （区域控制器控制并监控客舱区域）On the overhead AIR COND panel, the flight crew selects the desired individual compartment temperature.（在头顶面板的空调面板上，机组可以选择希望得到的单独舱内的温度）The hot air system for cabin temperature control has a hot air valve and three trim air valves controlled by the ZC. （客舱温度控制的热空气系统有一个热空气活门和三个配平活门，都由区域控制器控制）The ZC compares the demand to the actual temperature in each zone.（区域控制器比较在每个区域的要求温度和实际温度）The ZC then sends the pack outlet temperature demand to both PCs to satisfy the coldest demand.（然后区域控制器给两个PACK控制器发送PACK出口温度的命令以满足最低温度的要求）For the zones, which require warmer temperature, the ZC signals the TRIM VALVES to open. （对于需要加热的区域，区域控制器命令配平空气活门打开）Hot air mixes with the pack discharge air and the temperature increases.（热空气和PACK出口的空气混合同时温度上升） In the case of any duct overheat, the hot air valve and the trim air valves will automatically close to isolate the system. （如果管道超温，热空气活门和配平活门自动关闭并隔离系统）The system can be reset when the overheat disappears.（过热消失的时候系统被重置） 五 Ventilation System（通风系统） 1 GENERAL（概述）

There are two ventilation systems on the Single Aisle (SA) family, avionics ventilation and lavatory and galley ventilation.（单通道系列的飞机包

含两套通风系统：电子设备通风和厕所厨房通风）The avionics ventilation system supplements the air conditioning system to supply cooling air to the avionics equipment.（电子设备冷却系统给电子设备提供冷却空气，作为空调系统的补充） This equipment includes the avionics compartment, the flight deck instruments and the circuit breaker panels.（这套系统包括电子设备舱、飞行舱设备、跳开关面板） 2 AVIONICS VENTILATION（电子设备通风）

A blower fan and an extraction fan circulate the air through the avionics equipment.（通过一个鼓风扇和一个抽风扇使电子设备的空气循环）Note: these fans operate continuously as long as the A/C electrical system is supplied. （注意：这两个风扇飞机一供电就持续工作）The Avionics Equipment Ventilation Computer (AEVC) controls the fans and the configuration of the skin valves in the avionics ventilation system based on flight/ground logic and fuselage skin temperature.（根据飞行或是地面逻辑和蒙皮温度，电子设备通风计算机控制电子设备通风系统的风扇和蒙皮活门的构型）

There are 3 configurations for the skin air inlet and outlet valves:（对于蒙皮进口和出口活门有三种构型）- open circuit: both valves open (on ground only),（仅仅在地面的开环构型：两个活门都开）- closed circuit: both valves closed (in flight or low outside air temperature on ground).（在飞行中或者在地面高温度时的闭环构型：两个活门都关） The air is cooled in the skin heater exchanger. （空气通过蒙皮热交换器冷却）- intermediate circuit: inlet closed, outlet partially open (smoke removal in flight or low ventilation airflow condition).（在低流量或者飞行中有烟雾时的中间构型：进口全关，出口半开）

3 LAVATORY AND GALLEY VENTILATION（厕所和厨房通风）

The lavatory and galley ventilation system is completely automatic.（厕所和厨房通风完全自动控制）Conditioned cabin air is supplied through the lavatory and galley areas and is removed from these areas by an extraction fan. （经过调节的客舱空气供到厨房厕所后，通过抽风扇排走）The fan pulls air through the ceiling into an extraction duct. （风扇通过天花板的抽风扇管路抽走空气）The air is then discharged overboard through the outflow valve.（然后空气通过外流活门排往机外）Note: the extraction fan runs continuously, provided electrical power is available.（注意：只要

有电，排风扇就持续运转）

六 Cargo Ventilation and Heating System（货舱通风和加热系统）

On the Airbus single aisle family, the forward and aft cargo compartments can have a ventilation system.（在空客单通道系列飞机里，前后货舱都有通风系统）In addition, a heating system may be installed in either or both compartments. （此外，在一个货舱或者两个货舱内都可以安装加热系统）Note that the heating system will only be installed along with a ventilation system.（注意，加热系统只能在通风系统的基础上安装） Air from the main cabin is drawn down into the cargo compartment by the extract fan or by differential pressure in flight.（空气空过抽风扇或者是在飞行中通过压差从客舱进入到货舱） After circulating through the compartment, the air is discharged overboard.（在货舱循环后，空气排往机外）The operation of the two isolation valves and the extract fan is controlled automatically by the cargo Ventilation Controller (VC). （两个隔离活门和抽风扇都由货舱通风控制器自动控制）One VC is able to control either or both compartments.（一个控制器可以控制一个或两个舱）For the heating of the cargo compartment, the pilots select the desired compartment temp and hot bleed air is mixed with the air coming from the main cabin to increase the temperature if necessary. （驾驶员可以选择想要的货舱温度，如果有必要，从客舱来的空气和热空气混合增加温度值）The supply of hot air is controlled by the Cargo Heating Controller. （热空气由货舱加温控制器控制）Each heated compartment has a dedicated Cargo Heating Controller. （每个货舱都有专门的加热控制器）Note that there is NO direct air conditioning supply to the cargo compartments. （注意，没有直接的空调供往货舱）The pilots cannot add \（驾驶员不能加冷空气给货舱） 七 Pressurization System（增压系统）

The pressurization system on the Single Aisle (SA) family normally operates automatically to adjust the cabin altitude and rate of climb to ensure maximum passenger comfort and safety.（单通道系列飞机的增压系统正常都是自动控制调节客舱高度和升降率以最大确保旅客的舒适性和安全性）The pressurized areas are:- the cockpit,- the avionics bay,- the cabin,- the cargo compartments.（增压区域包括：驾驶舱、电子舱、客舱、货舱）

The concept of the system is simple.（系统的概念很简单） Air is supplied from the air conditioning packs to the pressurized areas.（空气从空调的PACK组件供往增压区域）An outflow valve is used to regulate the amount of air allowed to escape from the pressurized areas.（一个外流活门用来控制逃离增压舱的空气）Automatic control of the outflow valve is provided by two Cabin Pressure Controllers (CPCs). （两部客舱增压控制器自动控制外流活门）Each CPC controls one electric motor on the outflow valve assembly.）每一部增压控制器在活门上都有自己的一套电马达） The CPC interface with other A/C computers to optimize the pressurization/depressurization schedule.（增压控制器与飞机的其他计算机连接来优化增压或者卸压的安排）There are two automatic pressurization systems. （有两套自动的增压系统）Each CPC and its electric motor make one system.（每一部增压控制器和其电马达构成了一套系统） Only one system operates at a time with the other system acting as backup in case of a failure. （同一时间只有一套系统工作，另一套系统备份，失效时接替工作）The system in command will alternate each flight.（在飞行中系统交替工作）A third motor is installed for manual operation of the outflow valve in case both automatic systems fail.（如果两个自动控制都失效了，还有第三套人工马达可以人工操作外流活门）To protect the fuselage against excessive cabin differential pressure, safety valves are installed on the rear pressure bulkhead. The safety valves also protect against negative differential pressure.（为了保护机身过大的压差，在增压舱的后隔板上安装有两个安全活门，安全活门可以保护过大的负压差）

ATA22 - Auto Flight System（自动飞行系统）

GENERAL（概述）

The Auto Flight System (AFS) is divided into four main parts:（自动飞行系统分为4个部分） - Flight Management (FM),（飞行管理） - Flight Guidance (FG),（飞行引导） - Flight Augmentation,（飞行增稳）

- Fault Isolation and Detection System (FIDS).（故障隔离和探测系统）

The first two functions are accomplished by the Flight Management and Guidance Computers (FMGCs).（前两个功能由飞行管理和引导计算机完成）The other two functions are accomplished by the Flight Augmentation Computers (FACs).（另外两个功能由飞行增稳计算机完成）The AFS calculates the position of the aircraft using several aircraft sensors.（自动飞行系统使用几个飞机的传感器计算飞机的位置）In addition, the system has the capability of storing flight plans in its memory, which are predetermined by the airline.（此外，自动飞行系统有在其内存中存储飞行计划的能力，该飞行计划由航空公司预先做好）A flight plan describes a complete flight from departure to arrival, it includes vertical information and all intermediate waypoints. （这个飞行计划描述了从离场到到场的一个完整的飞行）Knowing the position of the aircraft and the desired flight plan (chosen by the pilot), the AFS is able to compute the orders sent to the flight controls and engines so that the aircraft can follow the flight plan.（直到了飞机的位置和驾驶员预先选择的飞行计划，自动飞行系统可以计算出给飞控和发动机的命令值，保证飞机可以按飞行计划飞行） FLIGHT MANAGEMENT/FLIGHT GUIDANCE（飞行管理/飞行引导）

The FM part has several functions linked to the flight plan such as lateral and vertical guidance associated with performance computation.（飞行飞行管理的几个功能与飞行计划相关联，例如：与性能计算相关的横向和纵向引导） The FG part has 3 functions:（飞行引导有3个功能） - Autopilot (AP),（自动驾驶） - Flight Director (FD),（飞行指引） - Autothrust (A/THR).（自动油门）

The FMGC functions, FM and FG are controlled from the MCDUs and the Flight Control Unit (FCU).（飞行管理和引导计算机的功能：飞行管理和引导可以从多功能控制显示组件和飞行控制组件来控制）

Basically, the MCDUs provide the long term interface between the crew and the FMGCs (e.g. flight plan selection and modification) （基本上多功能控制显示组件在机组和飞行管理引导计算机之间提供长期的接口，例如飞行计划的选择和更改）while the FCU provides the short term interface (e.g. engagement of the autopilot, flight director and A/THR functions).（飞行控制组件提供短期的接口，例如:自动驾驶、飞行指引、自动油门的接通）

Besides the MCDUs and the FCU, the main displays presenting Flight Management and Guidance information are the EFIS displays.（而且，多功能控制显示组件和飞行控制组件的主要显示是电子飞行仪表系统上的显示，这些显示有飞行管理和引导的信息） AUTOPILOT/FLIGHT DIRECTOR（自动驾驶/飞行指引）

The main AP and FD functions are:（自动驾驶和飞行指引的功能有）

- stabilization of the aircraft around its center of gravity when the AP/FD system holds vertical speed or flight path angle and heading or track,（当自动驾驶飞行指引来保持垂直速度、飞行航向角度、方向或轨迹时飞机围绕重心的稳定性） - acquisition and holding of a flight path,（获得并保持飞行航线） - guidance of the aircraft at take off,（飞机起飞的指引） - automatic landing and go around.（自动着陆和复飞）

The AP function gives orders to control:（自动驾驶功能发出命令控制）

- the position of the control surfaces on the three axes (pitch, roll and yaw),（飞控舵面在三个方向的位置，俯仰、滚转、偏航） - the nose wheel steering.（前轮转弯）

The FD function generates optimum guidance orders used in manual controls.（飞行指引的功能是产生最合适的引导命令用于人工控制）The FD

is also used to monitor the AP when it is engaged.（当自动驾驶接通时，飞行指引也监控自动驾驶） The FD symbols are displayed on the PFDs.（飞行指引在主飞行显示器上显示） AUTOTHRUST（自动推力）

The A/THR system fulfills the following functions through the control of the thrust:（自动推力系统通过控制推力完成以下功能）

- speed or mach hold (either FMGCs computed or from throttle levers position),（根据FMGC的计算或者推力杆的位置保持速度和马赫数） - thrust hold (either FMGS computed or from throttle lever position),（根据飞行管理引导系统或者推力杆的位置保持推力） - thrust reduction during descent and during flare in final approach,（在下降和最终进近平飞时的减推力） - protection against insufficient speed linked to excessive angle of attack.（大攻角保护，以防止失速）

To fulfill the A/THR functions, the FMGCs communicate with the Full Authority Digital Engine Control (FADEC) via the FCU and the Engine Interface Units (EIUs).（为了实现自动推力功能，飞行管理引导计算机通过飞行控制组件和发动机接口组件与FADEC相联） FLIGHT AUGMENTATION（飞行增稳）

The flight augmentation part fulfills the following functions:（飞行增稳包含以下内容） - rudder trim,（方向舵配平） - yaw damper,（偏航阻尼）

- rudder travel limitation,（方向舵行程限制） - flight envelope protection,（飞行包线保护）

- FIDS.（故障隔离和探测系统）

For flight envelope protection, the FAC computes:（为了飞行包线保护，飞行增稳计算机计算如下参数） - the various speeds for aircraft operation (e.g. flaps limit speed),（飞机操作时的各种速度限制） - the excessive angle of attack and windshear detection,（大攻角保护和风切变探测）

- the low energy warning, indicating to the crew that the aircraft is quickly decelerating and that thrust will have to be increased to recover a positive flight path angle through pitch control.（低功率警告，给机组指示飞机正快速减速同时通过配平手轮修正飞行航向）

The FIDS function is only active in FAC 1.（仅有飞行增稳计算机1号有故障隔离和探测功能）FAC 1 is connected to the BITE of all the AFS computers and communicates to the Centralized Fault Display System (CFDS).（飞行增稳计算机1号与自动飞行计算机的BITE相连，并与CFDS系统通讯）

ATA 23 - Communications System（通讯系统）

GENERAL（概述）

The single aisle aircraft communication system has two sub-systems:（单通道飞机的通讯系统包含2个子系统） - radio communication,（无线电通讯） - on-board communication.（机上通讯）

The radio communication systems are used for communications to and from the aircraft.（无线电通讯系统用于飞机进出的通讯） The on-board internal communication system is divided into 4 functions:（机上通讯系统分为4个功能）

- service interphone (on ground only) for maintenance technician communication with cockpit or cabin thanks to several jack connectors around the A/C.（由于有围绕飞机的数个插孔，因此维护技术人员可以通过勤务内话与驾驶舱和客舱通讯）

- Flight interphone for cockpit internal communication and also with the ground mechanic,（飞行内话用于驾驶舱的通讯，也可以用于地面技术人员与驾驶舱的通讯）

- Passenger Address (PA) from the cockpit or from cabin crew stations for passenger announcements,（旅客地址系统用于从驾驶舱或者客舱的机组区域对旅客通知）

- cabin interphone for cabin crew or cabin crew/pilots communication.（客舱内话用于客舱之间或者客舱和驾驶舱的通讯） RADIO COMMUNICATION SYSTEM（无线电通讯系统）

The radio communications system lets the crew communicate with ground stations through VHF, VHF Data Radio (VDR), HF, High Frequency Data Radio (HFDR) and SATCOM if installed.（无线电通讯系统让机组与地面通过甚高频、甚高频数据的无线电、高频、高频数据的无线电、卫星进行通讯）

VHF1 and VHF2 used for flight crew voice communications（VHF1号和2号用于飞行员语音通讯）

VDR3 used for ACARS and as voice backup（VHF Data Radio，VHF3号的无线电数据用于ACARS和语音备份） HF used when A/C beyond VHF range（当超出VHF频段时，可以使用HF） ON-BOARD COMMUNICATIONS（机上通讯）

The on-board communication system is divided into 4 functions.（机上通讯分为四个功能） Flight interphone（飞行内话）

PA（passenger announcement旅客广播） Cabin interphone system（客舱内话） Service interphone（勤务内话）

ATA 24 - Electrical Power System（电源系统）

GENERAL（概述）

There are two identical engine driven generators called Integrated Drive Generators (IDGs). （有两个整体驱动发电机称为IDG）They are used as the main power source to supply the A/C electrical network.（他们作为飞机电网的主电源）The IDG basically contains, in a common housing, a generator and a Constant Speed Drive (CSD). （IDG基本组成：一个共有的客体、一个发电机、一个恒速驱动装置）The CSD gives a constant input speed to the generator, which is required for a constant output frequency.（由于发电机需要输出恒定的频率，恒速驱动装置给发电机一个恒速输入）

Each generator supplies 115V 400Hz AC to its own bus:- generator 1 supplies AC bus 1,

- generator 2 supplies AC bus 2. （每一个发电机给自己的汇流条提供115伏400赫兹的交流电，1号发电机给交流1号供电，2号发电机给交流2号供电）

This supply is known as split operation, which means that the AC power sources are never connected in parallel.（这种供电是分离供电，意味着交流电源绝不能并行供电）

Each AC bus supplies a Transformer Rectifier (TR):- AC bus 1 supplies TR 1,- AC bus 2 supplies TR 2.（每一个交流汇流条给一个变压整流器供电）

The TRs convert 115V AC into 28V DC to supply their associated DC buses, DC 1 and DC 2.（变压整流器将115伏的交流电转换成28伏的直流电供给相应的直流1号汇流条和直流2号汇流条）DC bus 1 then supplies the DC BAT bus.（直流1号汇流条给直流电瓶汇流条供电）The DC battery bus can charge the batteries or receive power from the batteries as a backup supply, if no other power sources are available.（直流电瓶汇流条可以给电瓶充电，作为备份供电同时可以从电瓶接受供电）The electrical system also includes two ESSential (ESS) Buses. （电源系统还包含两个重要汇流条）One is the AC ESS bus fed by AC bus 1 and the other is the DC ESS bus fed by DC bus 1. （一个交流重要汇流条由交流1号汇流条供电，另一个直流重要汇流条由直流汇流条1号供电）These buses are used to supply the most critical A/C systems.（这些汇流条组成了最基本的飞机电源系统）The entire electrical network can also be supplied by the APU generator.（整个飞机电网也可以通过APU的发电机供电）On the ground, the aircraft electrical network can be supplied by an external power source.（在地面飞机电网也可以用地面电源供电）Any one of the power sources can supply the entire electrical network. （任何一种电源都可以给整个的飞机电网供电）As no parallel connection is allowed on this A/C (split operation), we have to give priorities to the different power sources in supplying the bus bars.（在飞机上不允许并行供电，不通电源的供电优先顺序是）AC 1 and AC 2 buses are supplied in priority by their own side generator, then the external power, then the APU generator and then by the opposite generator.（交流汇流条1和2分别由相应侧的发电机供电，然后是地面电源，然后是APU发电机，最后是相反侧的发电机） ABNORMAL CONFIGURATION（非正常构型）

The electrical system has an ESS TR, which supplies the DC ESS Bus in abnormal or emergency configuration.（电源系统有一个重要变压整流器，在非正常或者应急构型时给直流重要汇流条供电）

In abnormal configuration (loss of TR1 or TR2) the ESS TR is supplied by the AC ESS Bus.（在非正常构型下，无论是失去变压整流器1还是2，重要的边压整流器都由交流重要汇流条供电）EMERGENCY CONFIGURATION（紧急构型）

The hydraulic power to drive the Emergency Generator (EMER GEN) is given by a Ram Air Turbine (RAT) via the blue hydraulic system.（冲压涡轮通过蓝液压系统驱动了一个应急发电机）RAT located in belly fairing, extends automatically when AC BUS 1 and 2 are lost.（冲压涡轮位于

机腹，当交流1号额2号都失去时自动放出）Then, the EMER GEN supplies the DC ESS through AC ESS directly TR. （然后通过重要的变压整流器，交流重要汇流条可以给直流重要汇流供电） BATTERY ONLY CONFIGURATION（仅有电瓶的构型）

In emergency configuration with emergency generator not available, BAT 1 supplies the AC ESS BUS via the static inverter and BAT 2 supplies the DC ESS BUS.（在紧急构型下如果应急发电机不可用，电瓶1号通过静变流机给交流重要汇流条供电，电瓶2号给直流重要汇流条供电）

ATA26 - Fire Protection System（防火系统）

The A320 family fire protection systems have:（A320系列的防火系统包括）

- fire detection and extinguishing systems for the engines and APU,（带火警探测和灭火的发动机APU系统） - smoke detection for the avionics equipment and compartment,（电子设备舱的烟雾探测系统）

- smoke detection and fire extinguishing for the cargo compartments and lavatories,（对于货舱和厕所的烟雾探测和灭火系统） - portable fire extinguishers for the flight compartment and the cabin.（驾驶舱和客舱的手提灭火瓶） ENGINE FIRE PROTECTION（发动机防火系统）

The engine fire protection is fulfilled by two sub-systems: the FIRE detection system and the FIRE extinguishing system.（发动机防火系统包含两个子系统：火警探测和灭火系统）The engines have individual fire detection systems.（每台发动机有独立的火警探测系统）Each system has two identical detection loops (A and B) mounted in parallel.（每个系统有并联的独立的两个探测环路A和B） Each loop is made of 3 detector elements. （每个环路有3个探测原件）Both loops are monitored by a Fire Detection Unit (FDU). （两个环路都由火警探测组件监控）The FDU sends FIRE

and FAULT signals to the Flight Warning Computer (FWC) for display on ECAM.（火警探测组件给飞行警告计算机传送火警和故障的信号用于ECAM的指示）

The guarded FIRE P/B switches give FIRE indication and the means to isolate affected systems. （带保护盖的火警手柄可以给出火警指示同样可以隔离受影响的系统）When the FIRE P/B is released out, fuel supply, hydraulic supply, electrical power and bleed supply are cut off. （当火警手柄释放时，燃油、液压、电源、引气都被切断）This also arms the extinguishing system.（这也是让灭火系统待命）Each engine is equipped with 2 fire bottles located in the pylon.（每个发动机在吊架内都装有两个灭火瓶）Each bottle is discharged by an associated AGENT P/B switch. （每个灭火瓶都有相应的灭火剂的按钮）The P/B switches are located on the overhead FIRE panel.（这个按钮位于头顶的火警面板上）The TEST buttons are used to test the respective fire detection and extinguishing system operation.（测试按钮可以测试各自的火警探测和灭火系统）The overhead FIRE panel handles both detection and extinguishing functions. （火警面板包含了探测和灭火功能）In addition to the indications on the FIRE panel, the ENG panel located on the pedestal is equipped with a red FIRE indicator light for each engine.（除了火警面板的指示之外，在中央操纵台的发动机面板上也有火警等用于指示每台发动机的火警） APU FIRE PROTECTION（APU防火）

The APU fire protection is fulfilled by two sub-systems: the FIRE detection system and the FIRE extinguishing system. （APU防火系统包含两个子系统：火警探测和灭火系统）The detection system has two identical detection loops (A and B) mounted in parallel. .（探测系统有并联的独立的两个探测环路A和B） Each loop has a single detector element. （每个环路有1个探测原件） Both loops are monitored by a FDU. （两个环路都由一个火警探测组件监控） The FDU sends FIRE and FAULT signals to the FWC for display on ECAM .（火警探测组件给飞行警告计算机传送火警和故障的信号用于ECAM的指示）The guarded FIRE P/B switches give a FIRE indication and the means to isolate affected systems. （带保护盖的火警手柄可以给出火警指示同样可以隔离受影响的系统） When the FIRE P/B is released out, fuel, electrical power and bleed supply are cut off and the APU is immediately shut down. （当火警手柄释放时，燃油、电源、引气都被切断）This also arms the extinguishing system. （这也是让灭火系统待命）For the APU, there is just one fire extinguisher bottle. （对于APU来讲只有一个灭火瓶）It is discharged by

ATA 29 - Hydraulic Power System

The aircraft has three independent hydraulic systems:- green,- yellow,- blue.（飞机有三个独立的液压系统：绿、黄、蓝）The three hydraulic systems supply hydraulic power at 3000 psi to the users:- flight controls,- landing gear,- brakes,- nose wheel steering,- cargo doors,- thrust reverser operation,- Constant Speed Motor / Generator (CSM/G).（三个液压系统提供3000PSI的压力给以下用户：飞控、起落架、刹车、前轮转弯、货舱门、反推、恒速马达发电机）Hydraulic fluid cannot be transferred from one system to another.（液压油不能从一个系统传输到另一个系统）A reservoir in each hydraulic system is pressurized with air to prevent cavitation.（每个系统都有一个用空气增压的油箱以防止空穴现象）The green and yellow hydraulic systems are each pressurized by an Engine Driven Pump (EDP) 1 and 2.（绿和黄系统分别由一个发动机驱动泵驱动）The yellow hydraulic system can also be pressurized by an electric pump.（黄系统也可以由电动泵增压）It is mainly used on ground for maintenance and cargo door operation.（它主要用于地面维护和操作货舱门）If no electric power is available, a hand pump in the yellow system can be used to operate the cargo doors.（如果没有电源时，黄系统还有一个手摇泵可以操作货舱门）A Power Transfer Unit (PTU) enables the green system to be pressurized by the yellow system and vice versa. （动力传输组件可以确保绿系统由黄系统增压，反之亦然）It transfers the hydraulic power but does not transfer the hydraulic fluid.（PTU只是传输的动力而不是液压油）Fire shut-off valves are located between the reservoirs and the EDPs.（火警关断活门位于油箱和发动机驱动泵之间）They isolate the systems in case of an engine fire.（当发动机火警时，他们隔离系统）The blue hydraulic system is pressurized by an electric pump.（蓝系统由电动泵增压）The electric pump is the main pump for the blue system.（电动泵就是蓝系统的主泵）It starts running at first engine start or it can be manually activated on ground for maintenance purpose.（蓝泵在一台发动机运行后自动工作，而且为了在地面维护的需要可以人工激活）Blue and yellow pumps are interchangeable.（蓝泵和黄电动泵可以互换）In an emergency, the blue system can be pressurized by the Ram Air Turbine (RAT).（紧急情况时，蓝系统可以由冲压涡轮增压）The RAT is deployed automatically or manually.（冲压涡轮可以自动或者人工放出） It pressurizes the blue hydraulic system at 2500 psi.（它只能增压系统到2500PSI） It can be retracted on ground only, following a specific maintenance procedure.（只有在地面按照特殊的维护程序，冲压涡轮才可以收回）

ATA30 - Ice and Rain Protection System（防冰防雨系统）

SYSTEM INTRODUCTION（系统介绍）

The ice and rain protection system enables unrestricted operation in icing conditions and heavy rain.（防冰防雨系统确保在结冰和大雨天气下不受限制的操作）For anti-icing, hot air or electrical heating protects critical areas of the aircraft.（为了防冰，热空气或者电加温可以保护飞机的临界面）The different subsystems of the ice and rain protection system are:（防冰防雨有以下不同的子系统）- wing ice protection,（机翼防冰）- engine air intake ice protection,（发动机进口防冰）- probe ice protection,（探头防冰）- windshield ice and rain protection,（风挡防冰防雨）- drain mast ice protection,（放泄桅杆防冰）- ice detection system (optional),（选装的结冰探测系统）- water and waste system ice protection.（水和废水防冰）

WING ICE PROTECTION（机翼防冰）

Hot air from the pneumatic system is supplied for the anti-icing of the three outboard leading edge slats (3, 4 and 5) of each wing. （从引气系统来的热空气供往每侧机翼前缘的三块缝翼进行防冰）Bleed air from the engines or the APU is supplied to each wing through a pressure regulating and shut off valve called Wing Anti-Ice (WAI) valve.（从发动机或者APU来的引气通过压力调节和关断活门供往每侧的机翼，这个活门叫机翼防冰活门）A single P/BSW on the overhead ANTI ICE panel controls WAI supply to both wings. （头顶防冰面板的一个电门控制两侧大翼的防冰活门）WAI must be manually selected by the crew and is available in flight only.（机翼防冰活门仅在飞行中可用，而且必须由机组人工选择）Whenever WAI is selected, the engine idle is increased and the Takeoff/Go Around (TOGA) limit (max thrust) is decreased by the Full Authority Digital Engine Control (FADEC).（每次机翼防冰活门选择的时候，FADEC都会增加发动机最小慢车的限制值并减小最大推力的限制值） This signal is sent to the FADEC through the Engine Interface Unit (EIU).（这个信号通过发动机接口组件送往FADEC）For testing purposes, WAI can be selected on the ground but will be automatically limited to 30 seconds operation to prevent damage to the wing leading edge.（为了测试需要，在地面机翼防冰活门选择后仅能自动接通30秒，这样可以防止损伤机翼前缘）

ENGINE AIR INTAKE ICE PROTECTION（发动机防冰）

Each engine air intake is protected from ice by an independent air bleed supply from the High Pressure (HP) compressor of that engine.（每台发动机进气口防冰都由该发动机单独的高压引气提供）The air is supplied through the engine air intake anti-ice valve.（通过发动机防冰活门引气进入发动机唇口）Engine anti-ice is manually selected by the crew and is available in flight or on the ground with the engine running. （发动机防冰必须由机组人工来选择，在空中和地面只要发动机运行都可用）After circulating around the inlet, the air is ducted overboard.（在唇口循环后，空气通过管路排往机外）Note: in the event of an electrical power supply failure, this valve will automatically open when the engine is running.（注意：如果电源失效，当发动机运行时该活门自动打开）Whenever engine anti-ice is selected, the engine idle is increased and the TOGA limit (max thrust) is decreased by the FADEC. （每次发动机防冰活门选择的时候，FADEC都会增加发动机最小慢车的限制值并减小最大推力的限制值）The FADEC also turns on continuous ignition. （FADEC同时会连续点火）This signal is sent to the FADEC through the EIU. （这个信号通过发动机接口组件送往FADEC）

PROBE ICE PROTECTION（探头防冰）

Ice protection of the Angle Of Attack (AOA) sensors, pitot probes, static ports, and Total Air Temperature (TAT) probes is achieved by electrical heating.（探头包括迎角探头、空速管、静压口、总温探头，都是电加温的）In order to give reliable information to the air data systems, the air data probes are heated automatically when at least one engine is running. （为了将可靠的信息给大气数据系统，在至少一台发动机启动后探头自动加温）The probes are arranged in three channels related to the three air data systems: CAPT, F/O and STBY (Air Data/Inertial Reference Unit (ADIRU) 1, 2, 3). （这些探头分为三组对应与三组大气数据，分别是机长、副驾驶和备用）The heating system for each channel is controlled and monitored by a Probe Heat Computer (PHC) 1, 2, 3.（每一组通道的控制和监控分别由探头加温计算机1号2号3号完成）The PROBE/WINDOW HEAT P/BSW (normally in the AUTO position) may be used to select the probe heating ON with the engines shut down.（探头和窗户加温电门正常在自动位，在发动机关车后可以选择到位）

WINDOWS ANTI-ICING AND DEFOGGING（窗户防冰和除霜）

The front windshields and side windows are heated automatically when at least one engine is running. （当至少一台发动机运行时，前风挡和侧窗会自动加温）The heating system for each side is controlled and monitored by a Window Heat Computer (WHC) 1, 2.（每一侧的加热系统分别由窗户加温计算机1和2控制和监控）The PROBE/WINDOW HEAT P/BSW (normally in the AUTO position) may be used to select the window heating ON with the engines shut down. （探头和窗户加温电门正常在自动位，在发动机关车后可以选择到位）The windows are protected against overheat by sensors and flight/ground logic.（通过温度传感器和空地逻辑保护窗户的过热） The sensors turn off the heat when the temperature reaches the limit and the windows are heated at a lower power on the ground than in flight.（当窗户温度到达限制值时传感器关断加热，同时在地面窗户加热在低功率位）

DRAIN MAST ICE PROTECTION（放泄桅杆防冰）

When the electrical system is powered, the waste water drain masts are also electrically heated. （只要有电，废水的放泄桅杆就会电加热）Two Control Units located in the cargo compartments control the heating of the forward and aft drain masts.（在货舱内的2个控制组件控制控制前后放泄桅杆的加热）

ATA 31 - Indicating/Recording System（指示记录系统）

一. ELECTRONIC INSTRUMENT SYSTEM（电子仪表系统）

The Electronic Instrument System (EIS) has six display units.（电子仪表系统有六个显示器）

The EIS is divided into two subsystems:（电子仪表系统有两个子系统）- the ECAM （Electronic Centralized Aircraft Monitoring）system which uses the two displays in the center to give information on the A/C systems,（电子中央飞机监控系统在中间给出飞机系统的信息）- the EFIS （Electronic Flight Instrument System）for which each pilot has two displays.(电子飞行仪表系统，每一个驾驶员有两个显示器)

二. ELECTRONIC INSTRUMENT SYSTEM – ECAM（电子中央飞机监控系统）

For the ECAM displays, the System Data Acquisition Concentrators (SDACs) receive data from the A/C systems and send it to the Display Management Computers (DMCs).（对于ECAM显示：系统数据采集器从飞机系统接收数据，送往显示管理计算机）The DMCs process the data and generate the images to be displayed.（显示管理计算机处理数据并且产生图形用于指示）

Under normal circumstances:（正常条件下）- DMC 1 supplies the upper ECAM display,（DMC1号用于上ECAM显示）- DMC 2 supplies the lower ECAM display,（DMC2号用于下ECAM显示）- DMC 3 is available as a backup.（DMC3号作为备份）The Flight Warning Computers (FWCs), heart of the ECAM system, receive data from:（飞行警告计算机是电子中央飞机监控系统的核心，从以下地方获得数据）- the A/C systems to generate red warnings,（从飞机系统接收数据产生红色警告）- the SDACs to generate amber cautions.（从SDAC接收数据产生琥珀色告诫）The FWCs then supply:（飞行警告计算机把数据提供给）- the DMCs for the display of alert messages,（给DMC显示警告信息）- the attention getters,（给需要注意的地方）

- the loudspeakers with aural alerts and synthetic voice messages.（给扬声器用于声音警告和合成语音警告） 三 ECAM CONTROL AND INDICATING（ECAM的控制和指示）

The EWD is divided into two main parts:（发动机警告页面分成两个部分）- the upper area is used to display the main engine parameters, the Fuel On Board (FOB) and the slat/flap position,（上部区域用来显示发动机参数、机载燃油、襟翼和缝翼位置）- the lower area is used for warning, caution and memo messages.（下部区域用来显示警告、告诫和备忘信息）The SD is divided into two areas:（系统显示页面分成两个区域）- the upper part is used to display the various system pages, diagrams of the A/C systems,（上部分用来显示各种系统页面、飞机系统的简图）- the lower part is used to display permanent data.（下部分显示永久参数）

Below the ECAM displays, on the center pedestal, there is the ECAM control panel.（在ECAM显示器下方，中央操纵台上有ECAM控制面板）The two control knobs on the LH side are used to adjust the brightness of the two ECAM screens and to turn them off.（控制面板左侧有两个旋

钮用于调节两个屏幕的亮度并且可以关断显示器）The P/Bs on the RH side are mainly used to:（在右侧的按钮主要用于）- display any of the system pages or the STATUS page,（显示任一系统页面或者状态页面）- clear or recall a warning or caution message.（清除或者召回告诫信息）An A/C STATUS page may be also displayed on the SD to give an operational status of the A/C.（一个状态页面可以给操作者显示飞机的状态）When things are not normal the STATUS page displays:（当有不正常的事件，状态页面会显示：）- operational data on the LH side,（在左侧显示操作数据）- INOPerative SYStem on the RH side.（右侧显示失效系统）In front of each pilot, there are two attention getters, a red MASTER WARNing and an amber MASTER CAUTion.（在驾驶员前面有各有一个红色的主警告和一个琥珀色的主告诫灯）

As a further means of getting the attention, there is a loudspeaker on each side of the cockpit for aural alerts and synthetic voice messages.（另外每一侧还有一个扬声器用于声音警告和合成语音警告）

四 ELECTRONIC INSTRUMENT SYSTEM – EFIS（电子仪表系统）

For the EFIS displays, data from the Air Data and Inertial Reference System (ADIRS) plus navigation data from the Flight Management and Guidance System (FMGS) is fed directly to the DMCs.（对于电子仪表系统，从大气数据和贯导系统来的数据、导航的数据直接送给显示管理计算机）The DMCs then process the data and generate the images to display.（然后显示管理计算机处理数据产生图形用于指示）Under normal circumstances:（正常条件下）- DMC 1 supplies the CAPT EFIS displays,（DMC1号用于机长侧的EFIS显示）- DMC 2 supplies the F/O EFIS displays,（DMC2号用于副驾侧的EFIS显示）- DMC 3 is available as a backup.（DMC3号用于备份） 五 EFIS CONTROL AND INDICATING（EFIS的控制和指示）

Flight parameters are displayed on the PFDs while navigation data is displayed on the NDs.（飞行参数显示在主飞行显示器上，导航数据显示在导航显示器上）Outboard of the PFDs, there are control knobs to adjust the brightness of the associated PFD and ND, and to turn the displays off.（PFD的外侧有控制旋钮可以调节相应PFD和ND的亮度并可以关闭显示器） 六 CLOCK（时钟）

A single electrical clock gives the Universal Time Coordinated (UTC) and date as time references for the crew and all peripheral systems.（单一的脉冲时钟给出协调世界时和日期，给机组和所有的周边系统）The other functions available for crew are Elapsed Time (ET) and chronometer. （另一个功能可以给机组提供消耗时机和精确计时）The clock can be synchronized with satellite GPS time.（时钟可以和GPS时间同步）The time is also displayed at the bottom of the SD.（时间也会显示在系统页面的底部） 七 CENTRALIZED FAULT DISPLAY SYSTEM（集中故障显示系统）

The Centralized Fault Display Interface Unit (CFDIU) centralizes and memorizes all information concerning A/C system failures.（集中故障显示接口组件集中并记忆所有的飞机系统的失效信息）Reading or printing of the failure information is done in the cockpit with any MCDU or the printer.（在驾驶舱通过多功能控制和显示组件可以读出失效信息，并且可以通过打印机打印信息）Most A/C system computers have a BITE.（大部分飞机系统计算机都有内建的测试模块） The BITE permanently monitors the system operation. （内建的测试模块永久的监控飞机系统的操作）When a failure is detected, it is stored in the BITE memory and is transmitted to the CFDIU.（当探测到失效时，储存在BITE的记忆里并传送给集中故障接口组件）

The ECAM also monitors the A/C systems. （ECAM也监控飞机系统）The warning information is delivered to the CFDIU.（警告信息也会传送给CFDIU）The failure information is available in various reports.（通过各种报告可以获得失效信息）

The reading of the failure information is made from two different MCDU menus depending on if the A/C is in flight or on ground.（根据飞机在地面或者在空中，通过MCDU可以读到两种不同的菜单）The SYSTEM REPORT/TEST function is available on ground only. （系统报告和测试功能仅在地面可用）It enables a dialogue between the CFDIU and a system computer.（它提供CFDIU和飞机系统计算机之间的对话）The SYSTEM REPORT/TEST menu page presents the list of all the systems connected to the CFDIU, in ATA chapter order.（系统测试报告菜单按ATA章节编排并连接到CFDIU）The maintenance Post Flight Report (PFR) can only be printed on ground. （航后报告仅在地面可以打印）It summarizes and displays the list of the ECAM warning messages and the fault messages that occurred during the last flight, with the associated time, flight

phase and ATA reference.（按相应的时间、飞行阶段、ATA参考号，航后报告总结了上一个航段的ECAM的警告清单和故障信息清单）It helps the maintenance crew to make a correlation for easier troubleshooting.（它可以帮助维护人员确定相互关系并轻松排故） 八 DIGITAL FLIGHT DATA RECORDING （数字飞行数据记录）

On the classic system, the Flight Data Interface Unit (FDIU) is the heart of the Digital Flight Data Recording System (DFDRS). （在基本型系统里飞行数据接口组件是数字飞行数据系统的核心）To fulfill the mandatory requirements of crash recording, the FDIU acquires and formats various critical flight parameters and system data before supplying the Solid State Flight Data Recorder (SSFDR).（为了完成失事记录要求，FDIU获得并编排飞行参数和系统数据再提供给固态飞行数据记录仪）The linear accelerometer measures the acceleration of the A/C in all three axes.（线性加速度计测量飞机三个方向的加速度）The SDAC digitizes the analog signal of the linear accelerometer and sends it to the FDIU.（SDAC将模拟信号转换成数字信号传送给FDIU）The operation of the SSFDR is automatic.（固态飞行数据记录仪自动操作）On the overhead panel, there is a GrouND ConTroL P/B located on the ReCorDeR panel. （在头顶面板上，在记录面板上有地面控制的按钮）This P/B lets the SSFDR be supplied when the A/C is on ground for preflight checks before engine start or for test and maintenance purposes.（在地面，这个按钮允许SSFDR供电 以便在启动发动机之前进行准备检查或者用于维护测试） 九 AIRCRAFT INTEGRATED DATA SYSTEM（飞机综合数据系统）

The main functions of the Aircraft Integrated Data System (AIDS) are to monitor engine condition, APU condition and A/C performance, and to provide trouble shooting assistance.（飞机综合数据系统的功能是监控发动机状况、APU状况和飞机性能并且提供排故帮助）The Data Management Unit (DMU) is the heart of the AIDS. （飞机综合数据系统的核心是数据管理组件）It fulfils the following functions:（它具有以下功能）- collection, processing and recording of various A/C parameters, including the mandatory parameters given by the FDIU. （收集处理记录各种飞机参数，包括FDIU给的命令性参数）The recording is made in an internal memory of the DMU,（这记录在DMU的内存里）- generate various reports according to defined conditions. （产生多种报告并界定条件）These reports are stored in a non-volatile memory of the DMU.（这

些存储在DMU不会丢失的存储器里）The printer is used to print reports generated by the DMU.（打印机也可以打印DMU生成的报告）

ATA 32 - Landing Gear（起落架）

LANDING GEAR（起落架）

The A320 aircraft family has a LH and RH dual wheel Main Landing Gear (MLG) and a dual wheel Nose Landing Gear (NLG).（A320系列飞机有左右两个带双轮的主起落架，和一个带双轮的前起落架）The MLG retracts inboard into the MLG wheel well and the NLG retracts forward into the NLG wheel well. （主起落架向内侧收进主轮舱，前起落架向前收进前起落架舱）The Landing Gears (L/Gs) are hydraulically operated and electrically controlled.（起落架系统是电控液压做动的） Each L/G has hydraulically and mechanically operated doors.（每个起落架都有液压和机械操作的舱门） Each L/G has a shock absorber. LANDING GEAR DOORS（起落架门）

Doors are hydraulically operated and electrically controlled.（门是电控液压做动的）The mechanically operated doors are linked to the L/G struts and moves with the gear.（随动门连接到起落架支柱上随起落架一起移动） WHEELS AND BRAKES（轮和刹车）

The wheels of the MLG have:（主起落架的轮包括）- carbon brakes,（碳的刹车）- brake fans (optional),（可选装的刹车风扇）- Tire Pressure Indicating System (TPIS) sensor (optional)（可选装的轮胎压力指示系统）- gear jacking pad for wheel change.（为了换轮的起落架顶头）The NLG has:（前起落架包括）- a Nose Wheel Steering (N/WS) system,（一个前轮转弯系统）- a jacking pad for wheel change,（一个为了换轮的顶头）- a TPIS sensor (optional).（一个可以选装的轮胎压力指示系统） LANDING GEAR EXTENSION AND RETRACTION（起落架的收放）

The L/G extension and retraction is controlled from the L/G control lever located in the cockpit.（在驾驶舱的起落架控制手柄可以控制起落架的收放）The gear up and down sequence is controlled by two computers called Landing Gear Control and Interface Unit (LGCIU) 1 and 2.（起落架的收放顺序由起落架控制和接口组件控制） Only one LGCIU is in command while the other LGCIU is in standby.（仅有一部起落架控制和接口组件在命令位，另一部在待命位） With any up selection the LGCIU in command will change and control a complete gear cycle.（当选择收上位时，命令通道进行转换同时控制一个完整的循环）The gear up and down position and the door close and open position are monitored by proximity detectors.（起落架上下的位置和门开关的位置由接近传感器监控）In case of failure of a LGCIU or a proximity detector, the other LGCIU will be in command.（如果LGCIU或者传感器失效，另一部计算机将接替工作）An interlock mechanism prevents unsafe retraction by locking the control lever in the down position when any shock absorber is not extended.（当起落架减震器处于压缩位置时，一个内部的机械锁锁定手柄在放下位以防止不安全的收上操作）The Nose Wheel (N/W) is automatically centered when the shock absorber is extended.（当减震器完全伸长时，前轮自动定中）The L/G is powered by the green hydraulic system. （前起落架由绿系统供压）At high air speed a safety valve cuts hydraulic supply to the L/G system（安全活门在高速时切断液压）In case of failure, the gear can be extended mechanically from the cockpit by means of a free fall extension handle.（如果失效，在驾驶舱的重力释放起落架手柄可以用于重力放下起落架） During free fall extension, a cut-out valve will close to cut the L/G hydraulic supply.（在重力放起落架时，切断活门切断液压系统的供压） BRAKING（刹车）

There are two braking modes:（有两种刹车模式）- normal braking,（正常刹车）- alternate braking.（备用刹车）-parking brake （停留刹车）The normal braking system is powered by the green hydraulic system.（正常刹车由绿系统供压）The alternate brake system and the parking brake are powered by the yellow hydraulic system and backed up by a brake accumulator.（备用刹车和停留刹车由黄系统供压，储压器作为备份）All braking functions are controlled by the Braking/Steering Control Unit (BSCU).（所有的刹车功能都由刹车转弯控制组件控制）These functions are:（这些功能有）- normal and alternate braking,（正常和备用刹车）- Anti-Skid (A/SKID) control,（防滞控制）- auto braking,（自动刹车）- brake temperature indication.（刹车温度指示）In manual normal braking, electrical braking orders are sent by the brake pedals to the

BSCU. （在人工正常刹车时，刹车的电信号传送给刹车转弯控制组件）The BSCU energizes the normal brake selector valve allowing green pressure to supply the brakes trough the automatic selector and normal servo valves.（刹车转弯控制组件打开正常刹车选择活门，允许绿系统压力通过自动选择器和正常伺服活门供往刹车）Depending on manual braking orders and A/SKID regulation, the BSCU regulates the pressure delivered to each brake through the normal servo valves.（依靠人工刹车的命令和防滞的调节，BSCU调节供到每个正常刹车伺服活门的压力）Wheel rotating speed from the tachometer, aircraft speed data and braking pressure are supplied to the BSCU for braking and A/SKID computation.（从轮速传感器来的轮速信号，飞机速度数据和刹车压力都提供给BSCU用于刹车和防滞的计算）Before landing, the crew can select one of the auto brake modes MAXimum, MEDium or LOw, to obtain the optimal deceleration rate compatible with the length of the runway.（在着陆之前，机组可以根据跑道的长度，选择一个自动刹车模式的减速率：最大、中、低，）Before take-off, MAXimum mode must be selected in case of an aborted take-off.（在起飞前为了防止中断起飞，选择最大的减速率）Braking starts when the ground spoilers deploy.（在地面扰流板伸出时，刹车开始）Depending on the deceleration rate and the A/SKID regulation, the BSCU regulates the pressure delivered to each brake trough the normal servo valves.（依靠减速率和防滞的调节，BSCU调节供往每个正常刹车伺服活门的压力）When the aircraft deceleration reaches a given value, the DECELerate green light on the L/G panel comes on.（当飞机减速到既定参数时，在起落架控制面板上的绿色减速灯会良）In order to stop the MLG wheels rotation before entry into the L/G bay, a programmed brake pressure is sent to the normal brakes during gear retraction.（在起落架收上后为了阻止主起落架轮自转动，一个刹车的压力会送往正常刹车）The alternate braking mode is automatically obtained in case of green pressure loss, or if a failure occurs on the normal brake system during operation.（当绿系统压力丢失或者操作中正常刹车失效时，备用刹车模式自动生效）The alternate braking circuit is pressurized through the automatic selector by isolating the normal brake system.（通过自动选择器隔离正常刹车系统之后，备用刹车被增压）Orders are entered by the pedals and transmitted through an auxiliary low pressure control system to the dual valve which regulates the yellow braking pressure.（命令通过脚蹬和一套辅助低压系统控制备用刹车系统的双活门来调节黄系统的刹车压力）The BSCU ensures the A/SKID regulation by controlling the alternate servo valves.（刹车转弯控制组件通过控制备用刹车伺服活门来确保防滞功能）Braking pressure is read on the triple pressure indicator.（在三针指示器上可以读出备用刹车压力）

The A/SKID regulation is deactivated, either electrically by setting OFF the A/SKID & N/W STeeRinG switch, BSCU failure or hydraulic low pressure (brakes being supplied by the brake accumulator only).（当刹车转弯防滞电门选择到关闭位，或者刹车转弯控制组件失效，或者是液压低压只由储压器供压时，防滞的功能失效）The pilot must refer to the triple pressure indicator to limit brake pressure in order to avoid locking a wheel.（此时，驾驶员必须参考三针指示限制刹车的压力以防止刹死机轮）With the accumulator pressure only, a maximum of 7 full brake pedal applications can be performed.（当仅有刹车储压器的压力时，最多可以用脚蹬完成7次完整的刹车）The parking brake system is supplied either by the yellow hydraulic pressure or by the brake accumulator.（停留刹车的压力可以由黄系统或者是刹车储压器提供）When the parking brake is activated, all other braking modes become inoperative.（当停留刹车激活时，所有的刹车模式都被抑制）With the parking brake handle in ON position, the parking brake control valve is open and the yellow pressure goes through the parking brake control valve, reaching the dual shuttle valve.（当停留刹车手柄设置到开位，停留刹车控制活门开，黄系统刹车压力到达双关断活门） The BSCU will deactivate the other braking modes.（刹车转弯控制组件将抑制其他刹车模式）The dual shuttle valve moves, allowing yellow pressure to the brakes through the alternate servo valves.（双活门做动，允许黄系统刹车压力到达备用刹车伺服活门）The pressure delivered to the LH and RH brakes as well as the brake accumulator pressure are indicated on the triple pressure indicator.（在三针指示表上的压力指示分为左侧和右侧） STEERING（转弯）

The steering system uses the green hydraulic system to operate a steering actuating cylinder, which changes the direction of the NLG wheels. （转弯系统使用绿系统压力来操作转弯做动器，来改变转弯的方向）The N/W doors must be closed in order for the hydraulic system to apply pressure to the steering actuating cylinder.（为了液压系统的压力能狗提供给转弯做动器，前起落架的舱门必须处于关闭状态）The steering system is controlled by the BSCU, which receives order from:（转弯系统由刹车转弯控制组件控制，接收以下信号）- the steering hand wheels (orders added algebraically),（代数叠加的转弯手轮信号）- the rudder pedals,（方向舵脚蹬的信号）- the autopilot.（自动驾驶的信号）The BSCU transforms the orders into N/WS angle. That angle has the following limits:（刹车转弯控制组件改变转弯的角度，并且有如下限制）- Ruder pedals: max 6 degrees,（方向舵最大6度）- Hand wheels: max 75 degrees.（手轮最大75度）The steering system receives hydraulic pressure in the following

conditions:（满足以下条件时转弯系统才接收液压动力）- A/SKID & N/W STeeRinG switch in ON,（转弯防滞电门打开位）- towing control lever in normal position,（拖行控制手柄在正常位）- at least one ENG MASTER switch ON,（至少一台发动机主店门在开位）- aircraft is on ground.（飞机在地面）

ATA 33 - Lights System（灯光系统）

GENERAL（概述）

The lighting system includes:（灯光系统包括）- cockpit lighting,（驾驶舱灯光）- cabin lighting and signs,（客舱灯光和信号）- emergency lighting,（应急灯光）- cargo and service compartment lighting,（货舱和勤务舱灯光）- exterior lighting.（外部灯光） COCKPIT LIGHTS SYSTEM（驾驶舱灯光系统）

The cockpit lighting system include:（驾驶舱灯光包括）- panel and instrument lighting,（面板和仪表灯）- general cockpit lighting (dome light),（一般照明灯光，顶灯）- ambient lighting.（环境照明灯光） CABIN LIGHTS（客舱灯光）

Various cabin light and sign systems are controlled, tested, and monitored by the Cabin Intercommunication Data System (CIDS). （各种客舱灯光和信号系统由客舱内部通讯数据系统负责控制监控和测试）The CIDS, composed of two Directors, is linked to the Forward Attendant Panel (FAP) and to the Programming and Test panel (PTP) for control and monitoring of the cabin light functions.（客舱内部通讯数据系统由两部主管的计算机组成，连接到前服务员面板和编程测试面板用于监控和控制客舱灯光功能）The director communicates through Decoder Encoder Units (DEUs) with the cabin, passenger and crew systems. （主管计算机通过解码译码器与客舱、旅客、机组系统相连）The PTP is used to program and test the CIDS and the related light systems.（编程测试面板可以用来编程并测试客舱内部通讯数据系统和相应的灯光系统）The CIDS controls the cabin lights through the FAP and monitors the cabin lights through the PTP.（客舱内部通讯数据系统通过前服务员面板控制客舱灯光，通过

编程测试面板监控客舱灯光）The CIDS also controls:（客舱内部通讯数据系统还可以控制）- the passenger lighted signs,（旅客信号灯）- the passenger reading lights,（旅客阅读灯）- the passenger calls.（旅客呼叫） EMERGENCY LIGHTS（应急灯光）

The cabin emergency lights are lamps located on the cabin ceiling panels.（客舱应急灯位于客舱天花板）In order to provide sufficient lighting of the aisle, exits and emergency exits, lights are installed on the left aisle seats and near the passenger doors and wing exits.（为了给过道、出口、应急出口提供足够的照明，灯安装在通道左侧的座椅上、旅客门的的附近和翼上出口）The exterior emergency lights come on automatically whenever the escape slide is deployed. （只要紧急滑梯释放，外部应急灯光自动打开）The lights are supplied from the cabin emergency power supply units.（这些灯光由客舱应急电源提供组件供电）The emergency - lighting system can be controlled by the control switch EMER EXIT LT installed on the overhead cockpit control panel.（安装在驾驶舱头顶面板的应急出口灯电门可以控制应急灯光）The red LIGHT EMER (EMERGENCY LIGHT) pushbutton on the FAP has the same function as the cockpit EMER EXIT LT switch in the ON position.（在前服务员面板的应急灯光电门与驾驶舱应急出口灯电门功能相同）Emergency lights in the cabin include EMERGENCY EXIT signs, Ceiling EMERGENCY lights, ESCAPE PATH lighting, The emergency lights are supplied by several Emergency Power Supply Units (EPSUs).（客舱应急灯包括：应急出口信号、天花板的应急灯、逃离通道灯，这些应急灯都由几个应急电源提供组件供电）

Housed in the fuselage, there are 4 exterior emergency lights. （在机身上有四个应急出口灯）These lights are automatically activated when an overwing emergency exit door is opened in the armed configuration.（当翼上应急出口在待命位被打开时，这些灯自动打开）The lights come on all along the escape route leading to the aft wing slide.（这些灯沿着撤离的路径延伸到机翼后方的滑梯） Each escape slide has integrated lighting strips.（每个滑梯都由一个完整的灯光条） EXTERIOR LIGHTS（外部灯光）

The exterior lighting system include:（外部灯光包括）- taxi, turn off lights,（滑行转弯灯）- navigation, strobe, beacon, wing lights,（导航灯、闪

光灯、防撞灯、大翼照明灯）- take off and landing lights.（起飞和着陆灯）

ATA 34-NAVIGATION（导航）

The navigation systems will be broken down into 4 main groups. （导航系统分成4个主要部分）They will be presented in 3 modules:（他们又被分成3个模块）

- Air Data/Inertial Reference System (ADIRS) and standby instruments,（大气数据和惯性基准系统以及其备用仪表） - dependent position determining systems and landing aids,（受依赖的的位置决定系统和辅助着陆系统） - independent position determining systems.（独立的位置决定系统）

There are several subsystems within each group.（每一个部分又分成几个子系统） The first group includes:（第一个部分包括）

- Air Data Inertial Reference Units (ADIRUs),（大气数据和惯性基准组件）

- Digital Distance and Radio Magnetic Indicator (DDRMI),（数字显示式的距离和无线电磁航向指示器） The second group (dependent position determining systems) includes:（第二部分包括） - GPS,（全球定位系统）

- ATC/Traffic Alert and Collision Avoidance System (TCAS),（Air Traffic Control，Traffic Alert and Collision Avoidance System，空中交通控制，交通警告和防撞系统）

- DME,（Distance Measuring Equipment，测距设备）

- ADF,（Automatic Direction Finder，自动测向仪） - VOR.（VHF Omnidirectional Range，甚高频全向信标） The third group (landing aids) includes:（第三部分包括） - ILS,（Instrument Landing System，仪表着陆系统） - marker receivers.（信标接收）

The fourth group (independent position determining systems) includes:（第四部分包括）

- Enhanced Ground Proximity Warning System (EGPWS),（Enhanced Ground Proximity Warning System，增强型的近地警告系统） - RAs,（Radio Altimeter，无线电高度）

- Weather Radar (WXR) and Predictive Windshear (PWS).（Weather Radar，Predictive Windshear System气象雷达和预警告的风切变探测系统）

ATA 35 – Oxygen（氧气）

GENERAL（概述）

The oxygen system supplies crew and passengers with oxygen in case of cabin depressurization.（如果客舱系统释压，氧气系统可以给机组和旅客提供氧气）The oxygen system has three different subsystems:（氧气系统有3个不同的子系统）- cockpit Crew Oxygen System: the oxygen is supplied from a high pressure oxygen cylinder to quick donning masks in the cockpit,（驾驶舱机组氧气系统：氧气从高压氧气瓶提供给驾驶舱的氧气面罩）- passenger Oxygen System: the passenger and cabin attendant oxygen system is supplied by chemical oxygen generator units,（旅客氧气系统：旅客和服务员氧气系统由化学氧气发生器供氧）- portable Oxygen System: it has a high pressure portable cylinders with

continuous flow type masks and smoke hoods.（手提氧气系统：带有连续流动型面罩的高压氧气瓶，防烟面罩） COCKPIT CREW OXYGEN SYSTEM（驾驶舱机组氧气系统）

The cockpit crew oxygen system supplies oxygen to the flight crew, in case of a sudden decrease in cabin pressurization or if there are smoke or dangerous gases in the cockpit.（如果发生突然的客舱释压或者发生烟雾或者有有害气体时，驾驶舱氧气系统给飞行机组提供氧气）The cockpit crew oxygen system has a high-pressure oxygen cylinder that can be isolated for maintenance by an ON/OFF valve. （驾驶舱机组氧气系统有一个高压氧气瓶，上面有开关用于隔离系统）A pressure regulator reduces the high pressure to a supply low pressure to the masks via a supply valve.（一个压力调节器减小压力后通过一个提供活门将氧气供往低压系统）The supply valve can be switched off from the cockpit for maintenance action as well as in ground configuration.（在地面构型时为了维护的需要，供氧活门可以在驾驶舱关断）The system is protected if an overpressure occurs in a high or low-pressure circuit.（在高压部分和低压部分都有超压保护） The overpressure is vented overboard.（过压的氧气直接通机外） The oxygen pressure condition is indicated on the DOOR/OXY page of the ECAM system.（在ECAM的门/氧气页面有氧气压力的指示）The pilots oxygen masks are located in a storage box on both side consoles.（在驾驶舱两侧的台子上安装有氧气面罩储存盒，氧气面罩就在里面）A mask-mounted regulator supplies a mixture of air and oxygen or pure oxygen, or gives emergency pressure control.（氧气面罩的调节器提供混合供氧或者纯氧或者在紧急情况下的压力供氧）With the regulator set to NORMAL, the user breathes a mixture of cabin air and oxygen up to the cabin altitude at which the regulator supplies 100% oxygen.（当调节器设置到正常位置时，机组呼吸混合的氧气，随客舱高度的增加纯度上升直到100％纯氧）The user can select 100%, in that case the regulator supplies pure oxygen at all cabin altitudes.（如果选择100％，在任何客舱高度调节器都提供纯氧）Depending on the situation, the user can use the emergency rotating knob and receive a maximum of oxygen or with the button pressed the oxygen system can be tested.（根据情况，机组可以使用紧急选装按钮接受最大的供氧，同时按压这个按钮可以测试氧气系统）A microphone is installed in the mask.（氧气面罩内安装有麦克风）The TEST AND RESET control enables the oxygen flow to be tested as well as to reset the oxygen system.（测试和重置按钮可以测试氧气的气流或者重置氧气系统） CABIN OXYGEN SYSTEM（客舱氧气系统）

The fixed oxygen system in the cabin supplies oxygen to passengers and cabin crew in case of cabin depressurization.（如果客舱释压，客舱固定氧气系统给旅客和客舱乘务组提供氧气）It has containers with two to four masks and a chemical oxygen generator.（它包括2－4个氧气面罩和一个化学氧气发生器） The oxygen containers are located above the passenger seats, in the lavatories, in each galley and at each cabin attendant station.（氧气装置位于旅客座椅的上方、厕所、每一个厨房和每一个坐乘务务员的地方）In case of cabin depressurization the container doors open automatically and the oxygen masks drop out.（如果发生释压，氧气装置的门自动打开，氧气面罩脱落）The container doors can also be opened from the cockpit or manually with a special tool located in the cabin crew workstation.（氧气装置的门也可以从驾驶舱控制打开，同时在乘务员工作站下方有特殊工具可以人工打开该门）By pulling the mask the oxygen generator is activated and produces pure oxygen to the masks for a limit time.（用力向下拉面罩可以激活氧气发生器，在有限的时间内可以给面罩提供纯氧） PORTABLE OXYGEN SYSTEM（手提氧气系统）

Smoke hoods are located in the cockpit.（驾驶舱有防烟面罩）Portable oxygen bottles and smoke hoods are located in the cabin.（客舱有手提氧气瓶和防烟面罩）

ATA 36 - Pneumatic System（引气系统）

SYSTEM INTRODUCTION（系统介绍）

The Airbus single aisle family pneumatic system supplies High Pressure (HP) air for:（空客单通道系列飞机的引气系统给如下系统提供高压起源）- air conditioning,（空调）- wing ice protection,（机翼防冰）- water pressurization,（水增压）- hydraulic reservoir pressurization,（液压油箱增压）- engine starting.（发动机启动）High Pressure air can be supplied from three sources:（高压空气有以下三个来源）- the engine bleed system,（发动机引气系统）- the APU,（辅助动力装置）- a HP ground power unit.（地面高压气源组件）The pneumatic system operates pneumatically and is monitored by 2 Bleed Monitoring Computers (BMC 1 & 2).（引气系统操作引气，由引气监控计算机BMC1号和2号监控）There is one BMC for each engine bleed system.（每台发动机一部引气监控计算机监控）Both BMCs exchange data. If one BMC fails, the other BMC takes over

most of its monitoring functions.（两部引气监控计算机交输数据，如果一台失效可以代替大部分监控功能） ENGINE BLEED（发动机引气）

The engine bleed air is pressure and temperature regulated prior to supplying the pneumatic system.（在提供到引气系统之前，发动机引气要经过压力和温度的调节） Air is bled from two engine High Pressure Compressor (HPC) stages, the Intermediate Pressure (IP) stage and the HP stage.（引气从发动机高压压气机的中间级和高压级引出）The HP bleed is only used when the engines are at low power.（发动机低功率时使用高压级引气）Once the IP bleed is sufficient, the HP valve closes.（一旦中间级引气足够，高压活门关闭）All the engine bleed air is supplied to the pneumatic system through the main engine BLEED valve (or Pressure Regulating Valve (PRV)) which acts as a shut off and overall system pressure regulating valve.（所有发动机的引气都通过引气压力调节活门供往引气系统）Each BMC monitors system pressure and will shut down the engine bleed in case of excessive pressure.（引气监控计算机监控系统压力，如果超压将关断发动机引气） In addition, an Overpressure Valve (OPV) is installed downstream from the bleed valve to protect the system in case of overpressure.（此外，在引气压力调节活门的下游安装有超压活门，如果发生超压可以保护系统）The hot bleed air goes through an air-to-air heat exchanger called the precooler.（热的引气将通过预冷器，该预冷器是一个空气冷却空气的热交换器） Fan discharge air modulated by the Fan Air Valve (FAV), blows across the pre-cooler to maintain the temperature within limits.（通过风扇空气活门调节风扇来的空气，流向预冷器以维持温度在限制值之内）The left and right bleed systems are connected by a crossbleed duct. （一个交输管道连接左右引气系统）A cross bleed valve enables their interconnection or isolation.（一个交输引气活门用于连接或者隔离） APU BLEED（APU引气）

The APU can also be used for bleed air supply. （APU也可以提供引气）This is usually done on the ground for air conditioning and for engine start.（通常在地面时用于空调系统和启动发动机）However, APU BLEED air could also be used in flight, depending on altitude.（根据高度情况，APU引气也可以在飞行中使用）The APU bleed supply is connected to the left side of the crossbleed duct.（APU引气交输管路的左侧）

HP ground power（地面高压气源）

On the ground, a HP ground power unit can be connected to the left side pneumatic system.（在地面，地面高压气源可以连接到左侧引气系统）The right side may be supplied by opening the crossbleed valve.（通过打开交输引气活门，供气也可以到右侧） LEAK DETECTION（渗漏探测）

Leak detection loops are installed along the hot air supply ducts of the pneumatic system.（沿着引气系统的供气管路，安装有渗漏探测的环路） The loops are made of multiple sensing elements connected in series.（环路由多根传感原件并联而成）The leak detection loops are connected to the BMCs. （渗漏探测的环路连接到引气监控计算机）If a leak is detected, a signal is sent to the BMC 1 or 2 which automatically isolates the affected area by closing the crossbleed valve and shutting off the engine bleed on the affected side.（如果探测到渗漏，引气监控计算机通过关闭交输引气活门和发动机引气活门来自动隔离受影响的区域）The leak detection system is organized into three loops.（引气渗漏探测系统由三组环路组成）Here are the loops and the protected areas:（以下是环路和受保护的区域）- pylon: from the precooler to the wing leading edge,（从预冷器到机翼前缘的吊架区域）- wing: wing leading edge including the wing air inlet supply, and belly fairing (cross bleed duct, pack supply ducts and APU forward supply duct).（机翼：机翼前缘包括空气进口和机腹整流罩，交输引气管、空调供气管、APU前供气管）- APU: APU aft supply duct from APU firewall to wheel well area.（从APU防火墙到主轮舱的APU供气管）

ATA 38 - Water and Waste（水和废水）

SYSTEM INTRODUCTION（系统介绍）

The water and waste system has:（水和废水系统包括）- a potable water system,（饮用水系统）- a waste water system,（废水系统）- a toilet system.（厕所系统）

POTABLE WATER SYSTEM （饮用水系统）

The potable water system supplies water from the water tank through a distribution system to the users.（饮用水系统从水箱开始通过分配系统供往用户）The users are the water faucets in the galleys and lavatories and the vacuum toilet units.（用户包括厕所和厨房的水龙头、真空马桶组件）A water heater is installed under the wash basin in each toilet unit to supply hot water to the water tap.（在每个厕所洗手池的下方都有水加热器，可以给水龙头供热水）The potable water system is pressurized by the bleed air system.（饮用水系统由引气系统增压）Manual shut off valves are installed to isolate any galley or lavatory.（每一个厕所和厨房都装有水关断活门用于隔离厨房和厕所）The potable water system can be serviced with or without electrical power available.（无论有电还是没电，饮用水系统都可以完成勤务工作） WASTE WATER SYSTEM（废水系统）

The waste water drain system collects the waste water from the lavatory washbasins and the galley sinks.（废水系统收集排放厕所洗手池和厨房的废水）The waste water is discarded outside through the drain valve (air stop valve) and the heated drain mast.（通过一个空气止动的放水活门和一个加热的排放桅杆，废水排向机外）Air stop valves avoid constant cabin depressurization by opening only when a certain amount of water is collected.（空气止动活门避免客舱持续的泄压，它只由收集到一定量的水后才会打开） VACUUM TOILET SYSTEM（真空厕所系统）

During toilet flushing, the waste from the toilet bowl is sent under the effect of cabin differential pressure to the under floor waste holding tank.（在厕所冲洗的时候，依靠客舱内外的压差，废物排到地板下方的废水收集箱）Waste holding tank servicing is done from the toilet servicing panel.（在厕所勤务面板上可以完成废水收集箱的勤务工作）On ground and in flight below 16,000 ft, a vacuum generator is used to generate the necessary delta pressure.（在地面或者高度低于16000英尺时，真空泵提供必要的压差）The overall toilet system operation, monitoring and fault indication are controlled by the Vacuum System Controller (VSC).（整个厕所系统的操作、监控、和故障指示都由真空系统控制器完成）When the flush switch is pressed, the Flush Control Unit (FCU) initiates the flush sequence.（当冲洗电门按压后，冲洗控制器控制冲洗的先后顺序）The rinse valve and the flush valve open in sequence, controlled by the FCU, to evacuate the waste material.（由冲洗控制器控制的漂洗和冲洗活门按顺

序打开，带走废弃物）At the same time the FCU sends a signal to the VSC which will operate the vacuum generator.（同时冲洗控制器给真空系统控制器信号操作真空泵）The vacuum generator makes the necessary differential pressure between the cabin and the waste holding tank to move the waste from the toilet bowl.（真空马达确保客舱与废水箱之间的必要压差，以至于将废物从马桶排到废水收集箱）Above 16,000 feet the VSC will stop the vacuum generator.（在16000英尺以上，真空系统控制器停止真空泵的工作）The VSC controls and monitors the vacuum toilet system and it is connected to the Centralized Fault Display System (CFDS).（真空系统控制器控制并监控真空厕所系统的工作，同时与集中故障显示系统相连接）

ATA 49 – APU（辅助动力装置）

一 GENERAL（概述）

The Auxiliary Power Unit (APU) is a constant-speed gas turbine engine installed in the unpressurized tail cone.（APU是一个恒速涡轮燃气发动机，安装在飞机的尾部）The APU is a self contained unit which enables the A/C to be independent of external pneumatic and electrical power sources.（APU是一个可以独立供电源和气源的组件）The APU is designed to operate throughout the entire flight envelope.（APU设计成在全部飞行包线内都可以使用）Electrical power is available whenever the APU operates, but bleed air is shut off above FL250.（只要APU工作就可以提供电源，在25000英尺以下可以使用气源）The APU is able to supply:（APU可以提供）- electrical power for the A/C systems,(给飞机电网供电)- bleed air for engine starting and air conditioning on the ground,（在地面可以提供引气用于发动机启动和空调）- bleed air for air conditioning/pressurization and wing anti-ice in flight.（在飞行中可以提供引气用于空调和增压以及大翼防冰） 二 ENGINE DESCRIPTION（发动机的描述）

The APU is a constant speed, single-shaft gas turbine engine that delivers mechanical shaft power to drive an accessory gearbox and a load compressor.（APU是一个恒速、单转子燃气涡轮发动机，它通过机械轴驱动附件齿轮箱和负载压气机）The APU generator is driven by the gearbox and the load compressor supplies pneumatic power for starting, air conditioning, etc.（APU发电机由附件齿轮箱驱动，负载压气机给启动、空调

等提供气源）The APU operation is controlled and monitored by the Electronic Control Box (ECB).（APU的控制和监控都由电子控制盒完成）The ECB has full authority over the following APU functions:（电子控制盒有权管理以下功能） - starting,（启动） - acceleration,（加速） - speed governing,（速度调节） - indication,（指示）

- fault monitoring,（故障监控）

- interface with A/C systems.（与飞机其他系统的接口）

The APU is capable of unattended operation; therefore, the ECB automatically shuts down the APU in case of a FAULT to protect the APU.（APU可以无人操作，因此当APU故障时电子控制盒自动关断APU）Based on regulations, in-flight protective shutdowns may be inhibited, except for critical FAULTs.（按规则，在飞行中关断保护可能被抑制，但严重故障除外） 三 CONTROL AND INDICATING（控制和指示）

The controls used to operate the APU are:（用以下部件操作APU）

- the APU MASTER SWitch and START P/BSW, on the APU control panel.（在APU控制面板上的主电门和启动电门） - the APU fire controls, on the FIRE panel.（在火警面板上的APU火警手柄）

In case of an APU FIRE warning on the ground, a loud horn will sound in the nose wheel well to tell ground personnel. （在地面如果APU火警，在前起落架舱的报警器发出响亮的声音提醒地面的人员）Associated with the horn, a red APU FIRE light will come on, on the external power

control panel on the lower fuselage.（与报警器关联的，在前机身的外部外部电源控制面板上出现红色的火警灯）

The APU has an air intake flap. The intake flap is open when the APU MASTER SWitch is selected ON and closes when the MASTER SWitch is selected OFF.（APU有一个空气进口风门，当主电门打开时风门打开，主电门关闭时风门关闭）

ATA70 - Power Plant CFM56

INTRODUCTION（简介）

The CFM56-5B engine is a dual-rotor, variable stator, high bypass ratio turbo fan power plant. （CFM56-5B发动机是双转子、可调静子叶片、高涵道比涡扇发动机）The CFM56-5B powers the complete single aisle family of aircraft. （CFM56-5B发动机为整个单通道系列飞机提供动力）CFM56-5B engines are available in several thrust ratings.（CFM56-5B发动机有几种可用的额定推力）

All the engines are basically the same.（基本上，所有的的发动机都一样 ）A programming plug on the Electronic Control Unit (ECU) changes the available thrust.（ECU上的程序塞可以改变可用推力） INSTALLATION（安装）

The power plant installation includes the engine, the engine inlet, the exhaust, the fan cowls and the reverser assemblies.（动力装置的安装包括发动机、进气、排气、风扇整流罩和反推组件） The pylon connects the engine to the wing structure.（吊架将发动机连接到机翼结构上） The engine is attached to the pylon by forward and aft mounts.（发动机通过前后安装节与吊架相连） MODULAR CONCEPT（单元体理念）

The CFM56-5B is designed using a modular concept. （CFM56-5B采用单元体理念设计）For easy maintenance and quicker return-to-service, the engine is made of 4 primary modules:（为便于维护和快速返回使用，发动机由四个主单元体组成：）

- fan and Low Pressure (LP) compressor,风扇和低压压气机

- High Pressure (HP) compressor, combustion chamber and HP turbine,高压压气机、燃烧室和高压涡轮 - LP turbine and Turbine Rear Frame (TRF),低压涡轮和涡轮后框架 - transfer and accessory gearboxes.传动和附件齿轮箱

The Low Pressure (LP) rotor has the forward fan, the booster compressor and the LP shaft, all driven by the LP turbine. （低压转子有前风扇、低压压气机和低压轴，它们都由低压涡轮驱动）The speed of the LP rotor is indicated on ECAM as N1.（低压转子转速在EACM上以N1表示） The forward fan supplies most of the engine thrust. （发动机的大部分推力由前风扇提供）The air produced by the fan is known as secondary airflow or bypass airflow. （风扇产生的气流就是我们所知的二股气流或外涵道气流）The 4-stage booster compressor supplies air to the engine core. （四级低压压气机为核心机供气）This is primary airflow. （这是主气流）The fan and LP compressor are supported by the fan frame which is also the location for the forward engine mount.（风扇和低压压气机由风扇框架支撑，她也是发动机前安装节的位置）

The 4-stage LP turbine drives the forward fan and the booster compressor.（四级低压涡轮驱动前风扇和低压压气机） It is supported by the TRF which is also the location for the rear engine mount.（低压涡轮由涡轮后框架支撑，她也是发动机后安装节的位置）

The LP rotor is supported by roller and ball bearings which are lubricated and cooled.（低压转子由滚珠和滚棒轴承支撑，轴承有润滑和冷却） The High Pressure (HP) rotor is made up of a 9-stage HP compressor driven by a single-stage HP turbine. （高压转子由九级高压压气机和九级高压涡轮组成，压气机由涡轮驱动）The speed of the HP rotor is indicated on the ECAM as N2.（高压转子转速在EACM上以N2表示） The HP compressor is also the source of customer bleed air.高压压气机也是用户引气的来源

The HP rotor is supported by roller and ball bearings, which are lubricated and cooled. （高压转子由滚珠和滚棒轴承支撑，轴承有润滑和冷却）

The annular combustion chamber is located between the HP compressor and HP turbine.（环形燃烧室位于高压压气机和高压涡轮之间） It is equipped with ports for 20 fuel nozzles and 2 igniter plugs.（燃烧室装有20 个燃油喷嘴和两个点火点嘴）

The accessory gearbox is located at the bottom of the fan case and is driven by the HP rotor through the transfer gearbox.（附件齿轮箱位于风扇机匣底部，由高压转子通过传动齿轮箱驱动）

The fuel pumps, oil pumps, hydraulic pump, Integrated Drive Generator and FADEC alternator are all driven by the gearbox.（燃油泵、滑油泵、液压泵、IDG和FADEC发电机都由齿轮箱驱动）

During engine starting, the starter rotates the HP compressor through the gearboxes.（启动期间，启动机通过齿轮箱驱动高压转子旋转） FADEC全功能数字式发动机电子控制器

In order to increase engine reliability and efficiency, the Full Authority Digital Engine Control (FADEC) gives the full range of engine control to achieve steady state and transient engine performances when operated in combination with aircraft subsystems.（为了增加发动机的可靠性和效率，在和飞机子系统共同工作时，由FADEC提供全程控制以获得稳态和过渡态的性能）

Each engine is controlled by an ECU, a dual channel computer located on the engine fan case. （每台发动机都由ECU控制，它是位于风扇机匣的双通道计算机）The ECU controls the engine during start and all operations. （ECU控制发动机的启动和所有工作）The ECU manages engine thrust and protects against overspeed and overtemperature by controlling the engine sub-systems. （通过控制发动机的子系统，ECU管理发动机推力并防止超速和超温）The ECU also monitors all engine subsystems and sensors for failure. （ECU也监控所有发动机的子系统和传感器的失效）When the engine is running, power for FADEC operation is supplied by a dual-output FADEC alternator driven by the gearbox.（发动机运转时，FADEC工作的电源是由齿轮箱驱动的双输出FADEC发电机提供）

The FADEC system has a dual channel ECU and the following peripherals:（FADEC系统由一个双通道ECU和以下周边设备组成）

- hydromechanical unit,液压机械装置

- dedicated FADEC alternator,专用FADEC发电机 - compressor control systems,压气机控制系统 - clearance control systems,间隙控制系统

- start system (starter shutoff valve, ignition exciters),启动系统（启动控制活门、点火激励器） - thrust reverser system,反推系统

- oil/fuel temperature control system,滑油/燃油温度控制系统 - fuel return valve,燃油回油活门 - engine sensors,发动机传感器 - electrical harnesses.导线

EIU/EVMU发动机接口组件/发动机振动监控组件

The ECU interfaces with various aircraft systems.（ECU与很多飞机系统有接口） Essential communication with the ECU (thrust lever position, air data, etc.) is direct to and from the applicable systems and controls. 与ECU的重要通讯（推力杆位置、大气数据等）直接送到或来自于相关的系统和控制Non-essential communication (autothrust, Centralized Fault and Display Unit (CFDS), etc) is routed through the Engine Interface Unit (EIU) of each engine. 非重要通讯（自动推力、CFDS等）通过EIU送到每台发动机The EIUs interface with various aircraft circuits and systems. （EIU与很多飞机电路和系统有接口）The data is then transmitted in a single stream to each ECU channel.（然后，数据送到每个ECU通道）

Engine vibration monitoring is accomplished by the Engine Vibration Monitoring Unit (EVMU). 由EVMU完成发动机振动监控工作The EVMU collects vibration data from both engines. （EVMU收集两台发动机的振动数据）The vibration information is displayed on the ECAM and is also available through the CFDS for troubleshooting.（振动信息显示在ECAM上，也可以通过CFDS用于排故） THRUST REVERSER SYSTEM反推系统

The flight crew manually selects reverse by lifting the latching levers on the throttle control levers.（机组通过提起油门杆上的锁手柄可以人工选择反推）The reverse thrust command is sent to the ECU and the Engine Interface Unit (EIU)..（反推指令送到ECU和EIU） The signal from the ECU to the directional valve is fed to an inhibition relay controlled by the Engine Interface Unit (EIU) according to throttle control lever position.（根据油门杆位置，从ECU送到方向控制活门的信号送到由EIU控制的抑制继电器）

According to commands from the ECU and the EIU, a Hydraulic Control Unit (HCU) supplies hydraulic power to operate the thrust reverser. （根据ECU和EIU的指令，HCU供应液压压力用于操作反推）The thrust reverser uses 4 hydraulically actuated pivoting blocker doors to redirect the engine fan airflow.（反推使用4个液压做动的阻流门将风扇气流反向） Reverse thrust is only available on the ground.（反推只能在地面使用）

附：常用航空英语词汇

vacuum cleaner suspend curved surface conversely restriction cross section of an airfoil angle of attack piston lift and drag coefficients hydraulic reinforce volume plane surface solid object dimension length width thickness triangle base altitude radius diameter circumference cylinder sphere 真空吸尘器 悬挂 弯曲表面 相反地 限定,节流 翼型剖面 攻角,迎角 活塞 升力和阻力 液压的 加强 体积 平面 实体 维,尺寸 长度 宽度 厚 三角形 底边 高度 半径 直径 圆周 圆柱 球体 breach ingnition spark crankshaft vector resultant centrifugal force centripetal force adhesive severe literally air transportation emphasize concentrate predictable conspequence gross weight certificate specification rough air shift stall characteristics bagage compartment loading chart fixed ballast lever moment 裂口 点火火花 曲轴 矢量,飞机航向 合成的 离心力 向心力 粘附的 严重的 完全地,字面上地 航空运输 强调 集中 可预测的后果 总重 证书 规范 颠簸不稳的气流 移动 失速特性 行李舱 装载图表 固定压舱物 杠杆 力矩 rod eliminate airframe angle notation perpendicular decimal fire extinguisher oxygen bottle hydraulic accumulator occupant mass gravitational inertia cruising speed friction ounce exert slat deploy lateral longitudinal decal pulley engage the spoiler mixer consume rig aisle hinge point 杆,棒 除去,消去 机体,结构 角 标志,记数法 垂直的 十进制 灭火器 氧气瓶 液压蓄压器 乘员 质量 万有引力的 惯性 巡航速度 摩擦 盎司=1/12磅 施加,产生 缝翼 展开,放出 横向的 纵向的 标记,图形 滑轮 接合,啮合 扰流板混合器 消耗 装配 通道 铰接点 fire propeller spinner alternator battery logical rearward category envelope prohibit constitute adverse beacon ballast temporary aileron spoiler flap transmitter loop terminater pedal autoland adjustment crank coordination pedal push rod fin spar ball peen hammer grind 防火墙 螺旋桨毂盖 交流发电机 电瓶 合乎逻辑的 在后面的 种类,类别 包线 禁止 构成 相反的 信标 压舱物 暂时的,临时的 副翼 扰流板 襟翼 传感器 回路,环路 终止,端接 脚蹬 自动着陆 调节手柄 协调 脚蹬推杆 安定面 梁 圆头锤 磨

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