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航空工程英语基础(中英文对照) [复制链接]

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发表于 2009-11-1 11:44:16 |显示全部楼层

航空工程英语基础(中英文对照)

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LESSON 1  THE B737 FUSELAGE机体
一、生词
飞机        Airplane        半硬壳式        Semi-monocoque        机身        Fuselage
起落架        Landing gear        动力装置        Power plant        支柱        Strut
分为        Divide into        包括        Contain        天线        Antenna
玻璃纤维        Fiberglass        蜂窝状物        Honeycomb        整流罩        Fairing
铰链        Hinge        压力密封隔板        Bulkhead        驾驶舱        flight compartment
进口        Entry        机上厨房        Galley        登机梯        Airstair
电子设备舱        Electronic equipment bay        检修口        Access door        旅客舱        Passenger cabin
货舱        Cargo        逃逸        Escape        舱口        Hatch
空间        Space        燃油箱        Fule bank        终止        Terminate
辅助动力装置        Auxiliary power unit        水平安定面        Horizontal stabilizer        桁架        Truss
排出        Exhaust        设计        Design        和…一样        The same as
伸长        stretch        延伸        Extension        脊鳍        Dorsal fin
增强        Strengthen        相对于        Relaviate  to         滑轨        Skid
结构        structure        修改        revise               
二、TEXT
(1)        the B737 is a low wing airplane. B737 has semi-monocoque fuselage and fully retractable landing gear. Two power plants are located under the wings on short struts.
波音737是一种下单翼飞机。它拥有半硬壳式机身和全收式起落架。两台发动机位于机翼下方短支架上。
(2)        The 737-300 fuselage is divided into four  sections: section 41 , section 43 , section 46 and section 48 .
波音737机体为为四部分:41、43、46和48.
(3)        Section 41 contains the radar antenna behind a fiberglass honeycomb fairing, hinged at the top. aft of the pressure bulkhead, above the floor, are the flight compartment and forward airstair and its door, and the electronic equipment bay .this section has two lower access doors.
41部分包括铰接在蜂窝状玻璃纤维雷达罩后面顶部的雷达天线、压力隔板后方及地板上方区域是驾驶舱和前登机梯及其门,还有电子设备舱。这部分有两个下检修口。
(4)        Section 43 contains the passenger cabin and the forward cargo compartment.
43部分包括客舱和前货舱。
(5)        Section 46 contain the center and aft portion of the passenger cabin ,two overwing escape hatches and aft entry and service doors. The space below the floor includes the wing center section (fule tank), air-conditioning bays, wheel well, hydraulic bay and aft cargo compartment. this section terminates at the aft pressure bulkhead.
46部分包括客舱中后部,两个逃生舱及入口和服务门。地板下的空间包括中央油箱、空调舱、轮舱、液压舱和后货舱。这部分终止于后压力隔板。
(6)        Section 48 contains the auxiliary power unit(APU) and horizontal stabilizer truss. Access to this section is through a door on the left side. Aft of which is the APU access door and APU exhaust.
48部分包括辅助动力装置和水平安定面桁架。可以通过左侧口盖接近。在它们的后面是APU检修口和APU排气口。
(7)        The 737-300 is the same basic design as the 737-200, with a body stretch of 104 inches, a wing tip extension of 14 inches, a horizontal tail extention of 36 inches, a larger dorsal fin and strengthened stabilizer.
737-300与737-200具有相同的基本设计,机体伸长了104英寸,翼尖延伸了14英寸,水平尾翼延伸了36英寸,还多了个大的脊鳍和增强的水平尾翼。
(8)        The 737-400, relative to the 737-300, has body stretch of 120 inches, tow additional overwing exit, tail skid, and strengthened landing gear.
737-400与737-300相比较,机身伸长了120英寸,多了两个逃生出口,尾部滑轨及加强了起落架。
(9)        The 737-500 uses the 737-300 basic structure with a 94 inches shorter body and a revised forward and aft fairing (wing to body).
737-500使用了737-300的基本结构,机身短了94英寸,并且修改了前后整流罩(机翼到机体)。

LESSON 2 THE PNEUMATICS SYSYTEM 增压系统
一、生词
目的        Purpose        压缩空气        compressure Air         压缩空气        pneumatic
环境        Environment        阶段,相位        Phase        得到        Obtain
发动机引气        Engine bleed        外部的        External        车        Cart
接头        Connector        整流罩        Cowl        热的        Thermal
防冰        Anti-icing        也,此外        Also        提供        provide
饮用水        Potable water        液压的        Hydraulic        启动器        Starter
在…之内        Within        正常的        Normal        取代        Substitute
满足        Meet        需要,要求        Need        上部、顶部        Top
图形        Figure        绝缘        Isolation        活门        Valve
管道        Duct        结合、连接        Join        交叉、跨接        crossover
管理、调整        govern        适当的        appropriate               
二、TEXT
(1)        the purpose of the pneumatic sysytem is to supply compressed air for a controlled temperature and pressure environment during all phases of flight and ground operation .air is obtained from engine bleeds. APU、or from an extermal ground cart through a connector located on the fuselage.
增压系统的作用是为飞行及地面所有阶段的温度和压力控制提供压缩空气。压缩空气的来源可以是发动机引气、APU、或通过机身上的连接头与地面气源车相连供气。
(2)        The pneumatic system controls the temperature and the pressure of engine bleed air source. The pneumatic system provides high temperature, high pressure air for the air conditioning .pressurization, wing and cowl thermal anti-icing .also, the pneumatic system provides pressure for the potable water system, hydraulic system and engine starters. The engine bleed air systems are located on the engine and within the support strut.
增压引气控制发动机引气的温度和压力。增压系统为空调、增压系统、机翼及整流罩热防冰系统提供高温、高压引气。同时,增压系统还给饮用水系统、液压系统和发动机起动系统提供压力。发动机引气系统位于支架内部发动机上。
(3)        The normal cabin air source is obtained from the 5th-stage of the engines at low –engine power, 9th-stage air automatically substitutes to meet user system needs.
正常情况下,客舱空气来自于发动机低能量的第5级,9级空气自动分配以满足用户系统的需要。
(4)        On the top of figure 2-1, the isolation valve separates the left and right halves of the system. On the left side of the isolation valve, the APU bleed air duct joins the left side crossover duct; on the right side ,the pneumatic ground service connector joins the right side crossover duct. From these ducts the user system are supplied with pressurized air ,governed by the appropriate control valves.
在图2-1的上方,隔离活门将左右系统分隔成独立的两部分。在隔离活门的左边,APU引气管道立连接着左交输管道;在右边,压缩空气地面接头连接右交输管道。用户系统可以从这些管道获得压缩空气,通过适当的控制活门进行控制。

LESSON 3 AIR CONDINTION空调系统
一、单词
空气调节        Air conditioning         环境        Ambient        机组        Crew
加热        heat        冷却        Cool        增压        pressurization
引出,放出        Bled        总管道        Manifold        分离        Seprate
独立的        indenpendent        冷却组件        Cooling pack        调节,管理        regulate
暖,热        Worm        减少        Reduce        期望        Desire
涡轮冷却器        Air cycle machine        整的        Integral        包括        Consist of
共同的        Common        轴        Shaft        离开        Leave
膨胀V        Expand        膨胀N        Expansion        下降        Drop
零下        Sub-zero        分配        Distribute        此外        In addition
配平空气管道        Trim air line        混合        Mix        室、容器        Chamber
加上,增加        Add        头顶上        Overhead        竖管        Raise
收集器        Collector        防护罩        Shroud        过滤器        Filter
排出口        discharge        再分配        Redistribute        二等分        halve
二、TEXT
(1)        the air conditioning system provides a conditioned air environment for the passengers and crew , heats the cargo compartment, cools the electronic equipment, and supplies air for the pressurization system.
空调系统为旅客和机组提供环境温度的控制,为客舱供热,为电子设备舱降温,还有为增压系统提供空气。
(2)        Air is bled from the pneumatic manifold and conditioned by 2 separate and independent cooling packs. Air flow into the packs is regulated by the pack valves.
空气从增压主管道和空调中通过2个隔离的,相互独立的冷却组件中被引入。空气流进组件中通过组件活门调节。
(3)        Air from the pneumatic manifold is too warm and must be cooled. The pupose of 2 packs is to reduce engine bleed air temperature to the desired temperature.
从增压主管道中来的空气太热,需要降温。两个组件的作用就是将发动机引气温度降低到需要的温度。
(4)        An air cycle machine is an integral unit of each cooling pack. The air cycle machine consists of a turbine wheel and a compressor wheel mounted on a common shaft. Air flowing through the air cycle machine drives the turbine, the turbine drives the compressor section. As the air leaves the turbine it expands greatly. This expansion can cause the temperature of the air to drop to sub-zero levels.
涡轮冷却器是构成每个冷却组件所必需的。它包括一个涡轮和一个压气机,安装在共同的轴上。气流通过涡轮冷却器驱动涡轮,涡轮驱动压气机部分。当空气离开涡轮后急剧膨胀。这种膨胀能够导致空气温度降到零度以下的程度。
(5)        In figure 3-1, we can see that the conditioned air from the right pack flows into the main distribution manifold, the conditioned air from the left pack flows into the main distribution manifold and into the flight compartment. In addition, a trim air line from the left mix chamber adds hot air to the flight compartment duct. The main distribution manifold supplies the passenger compartment overhead distribution system through tow sidewall risers.
在图3-1中,我们可以看出,调节空气从右组件流向主分配管道,还有调节空气从左组件流向主分配管道和进入驾驶舱。另外,从左混合舱出来的配平空气管道增加热空气给驾驶舱管道。主分配管道通过两个侧壁竖管供气给客舱顶部分配系统。
(6)        A 3-phase fan draws air from the collector shroud through filters and discharges into the main distribution manifold for redistribution.
一个三相风扇从收集器防护罩穿过过;滤器和排出口进入主分配管道,用以再分配。

LESSON 4 PRESSURIZATION INTRODUCTION增压系统简介
一、单词
组件        Pack        控制        Control        \座舱高度        Cabin altitude
外流阀        Outflow valve        保持        Maintain        尽可能的…        As as possible
目的地        destination        安全的        Safe        舒适的        Comfortable
曲线        Curve        对时间的        Against time        起飞        Takeoff
巡航        Curise        虚线        Dotted line        实线        Solid line
爬升        Ascend        下降        Descent        近        Near
环境        ambient        减小        decrease        变化率        rate
确定、决定        Determine        大气        Atmosphere        例子        Example
磅/英寸        Psi=pound per square inch        参照…        By referring        图表        Chart
描绘        Depict        与…的关系曲线        versus        称之为…        Is referred to as
制度        Sytstem        水银        mercury        毫巴        Millibar
相等的        identical        施加        exert        排出        exhaust
向机舱外        outbroud                               
二、TEXT
(1)        the air conditioning packs supply conditioned air into pressurization system. the pressurization system controls cabin altitude by regulating air flow from the fuselage, through the outflow valve. The pressurization system maintains cabin altitude as close to sea level as possible or at an altitude equal to the altitude of the flight destination, so the pressurization system provides a safe comfortable cabin altitude for the crew and passenger at all airplane altitude.
空调组件为增压系统提供调节空气。增压系统通过调节机身气流控制客舱高度,通过外流阀,增压系统保持客舱高度尽可能的接近海平面或等于飞行目的地高度,这样增压系统可为机组和旅客在整个飞行过程中提供一个安全舒适的客舱高度。
(2)        Figure 4-2 shows a curve of airplane and cabin altitude against time from take off through cruise to landing . airplane altitude is shown in dotted line. Cabin altitude is shown in solid line. The airplane starts its flight at an airport altitude near sea level, ascends, cruises, and descends to a landing airport near sea level.
图4-2显示为飞机和坐舱高度在起飞、巡航及着陆阶段的时间曲线。飞机高度显示为虚线,坐舱高度显示为实线。飞机以接近海平面的机场高度开始飞行、爬升、巡航、下降和接近海平面的机场着陆。
(3)        Cabin altitude starts at the take off altitude. As the airplane climb, the ambient pressure decreases; the higher the altitude, the lower the pressure. The altitude inside the airplane (cabin altitude)also climbs but at a lower rate than the airplane. The pressurization system provides the pressure differential between the cabin and ambient.
客趁高度开始于起飞高度。当飞机爬升时,环境压力减小,高度越高,压力越低。飞机内部高度(坐舱高度)也以一个低于飞机的速率爬升。增压系统提供客舱与外界环境之间的压力差。
(4)        The airplane altitude above sea level is determined by measuring the pressure of the ambient atmosphere. For example, see figure4-3, at 30,000 feet above sea level the ambient pressure would be 4.36 psi. the cabin altitude can be measured by adding the ambient pressure to the 7.80 psid maintained in side the airplane by the pressurization system: ambient pressure 4.36 psi at 30,000 ft.
Pressuree diffeential 7.80psid
                 12.16psi
by referring to the chart depicting ambient pressure versus altitude, if the ambient pressure is 12.16psi, the cabin altitude would be 5150 ft (see sigure 4-3).
飞机高度可通过测量环境大气的压力来测得。例如:图4-3,在高于海平面3万英尺的环境压力为4.36PSI。客舱高度可通过环境压力加7.8PSID来测得,7.8PSID由增压系统保持:
环境压力:4.36PSI   30000FT
压力差;7.8PSID
坐舱压力:4.36+7.8=12.16PSID
参照图表描述环境压力高度曲线,如果环境压力是12.16PSID,客舱 高度将是5150英尺(图4-3)
(5)        the cabin pressure is referred to as “psid” and indicates the differential pressure, in pounds per square inch , between inside and outside of the airplane. There are many systems for measuring pressure and “psi” is only one .airplane systems measure pressure in inches of mercury and millibars; these indications are identical to 14.7psi as a measurement of the pressure exerted by the atmosphere at sea level.
客舱压力被称为“PSID”并用“磅/英尺”指出压力差,在飞机内外,有许多系统可测量压力,“PSI”只是其中之一。飞机系统用英寸水银或毫巴来测量压力;这些指示等同于受到海平面大气压力14.7PSI。
(6)        The pressure control systems provide cabin differential pressure by controlling the outflow of air from the faselage. The pressure control system consists of an aft outflow valve, forward outflow valve, pressure controller, control panel, pressure sensing inputs, and monitoring indicators.
压力控制系统通过控制机外气流来提供客舱压力差。压力控制系统包括一个外流阀、前外流阀、压力控制器、控制面板、压力传感器和监视器。
(7)        The aft outflow valve allowing cabin air to exhaust overboard to maintain cabin pressure. The forward outflow valve receives a control signal from the aft outflow valve . when the aft outflow valve is closed, the forward outflow valve receives a signal to drive full closed.
后外流阀允许客舱空气排出到机外以保持客舱压力。前外流阀接收一个从后外流阀来的控制信号。当后外流阀被关闭时,前外流阀接收又个信号驱使完全关闭。

LESSON 5 FIRE DETECTION火警探测
一、单词
火警探测        Fire detection        在…周围        Around        组件        Pack
监控        Monitor        存在        Exist        泄漏        Leak
部件        Component        警告        Alarm        报警器        horn
过热        Overheat        铃声        Bell        规定        specify
发生        Occur        听觉        Aural        在…之下        beneath
面板        Panel        器件        device        与…相对应        Respond to
机翼        Wing        灭火器        Extinguish        盆        basin
厕所        Lavatory        瓶        Bottle        擦手纸斜槽        Tower chute
可选的        optional        角落        Corner               
特征        feature        轮子        wheel               
可用的        Available        放出        discharge               
位置        Location        完成        Accomplish               
元件        element        天花板        Ceiling               
二、TEXT
(1)        the fire detection systems monitor airplane components for overheat, fire or smoke condition. Engine and APU fire and overheat indication occurs on the P8 and P7 panels. Wing and body duct overheat warning occurs on the P5 and P7 panels. Lavatory smoke detection indication is an optional feature that is available. Indication can occur at the lavatory location and or on the P5 panel.
火警探测系统监控飞机组件的过热、失火或烟雾等情况。发动机和APU过热和失火指示出现在P8或P7板上。机翼和机身管道过热警告出现在P5或P7板上。厕所烟雾探测指示是一个可选装配件。指示能够出现在厕所位置或P5板上。
(2)        Engine fire and overheat detection is provided by detector elements located around the engine. The engine and APU fire detection accessory unit M279, located in the E/E bay determines if a fire or overheat condition exists. When detected indications occur in the flight deck an alarm bell is provided by the aural warning devices unit M315 for a fire condition. The two engine fire extinguisher bottles are located on the upper left aft corner of the main wheel well and are discharged from the flight deck.
发动机失火和过热信号探测由安装在发动机周围的探测元件提供。发动机和APU火警探测组件M279,安装在电子设备舱,用于判断是否有失火或过热情况发生。当在飞机蒙皮探测到火警信号时,音响警告设备M315将给出一个警告铃声。两台发动机灭火瓶安装在主轮舱左下方后角处,并从□□处释放。
(3)        The APU detectors sense fire conditions only. Monitoring of the sensors is accomplished by the M279. indications occur on the P28 panel in the wheel well and also in the flight deck. The APU fire bottle is located behind the aft pressure bulkhead and is discharged either from the flight deck or P28 panel.
APU探测器只感应火警信号。传感器的监控由M279完成。指示出现在P28板在主轮舱和FLIGHT DECK。 APU灭火瓶后压力隔板上,并通过P28板或FLIGH DECK释放。
(4)        Wheel well fire detection is provided by detector elements mounted on the wheel well ceiling. The detectors provide input to the M237 module located in the E/E bay. Indications occur on the P7 and P8 panels and an alarm bell is provided by the M315 module.
轮舱火警探测由安装在轮舱天花板上的探测元件来提供。探测器提供信号给安装在电子设备舱的M237组件。指示信号出现在P7和P8板上,警告铃声由M315组件提供。
(5)        The wing and body overheat detection system exists to monitor the pneumatic system for leaks . the detection system is divided into a left and right system. The detectors provide input to the M237 module. Overheat indication occurs on the P5 and P7 panels.
机翼和机身过热探测系统监控增压系统有无渗漏。探测系统分为左右两部分。探测器提供信号给M237组件。过热指示信号出现在P5和P7板上。
(6)        The lavatory smoke detector is located in each lavatory, the detector will provide a warning horn and indication at a specified smoke level .located in each lavatory, beneath the wash basin, is a fire extinguisher bottle which responds to high temperature in the tower chute.
厕所烟雾探测器安装在每个厕所里,探测器将在规定的烟雾层度发出警告信号。灭火瓶安装在每个厕所,洗手池下面,可以对擦手纸斜槽里的高温情况作出响应。


LESSON 6 OXYGEN SYSTEM氧气系统
一、单词
氧气        Oxygen        要求、命令        Acquire        单独的        independent
安装        Install        气态的        Gaseous        称为        designate
稀释器        Diluter        要求        Demand        化学上        Chemically
服务员        Attandent        气缸        Cylinder        旅客服务设备        Passengers service unit
面罩        Mask        切断        Shut off        数量        Quantity
压强计        Gage        即使        In a event of        排出        Vent
紧急情况        Emergence        锁定        Latch        释放        Release
作动筒        Actuator        机构        Mechanism        开动,启动        activate
自动地        automatically        人工地        manually               
二、TEXT
(1)        the purpose of the oxygen system is to provide oxygen for the flight crew and passengers when required. Two independent oxygen system are installed in B737. the flight crew oxygen system is a high pressure gaseous system for flight crew use only, this type of system is designated a “diluter demand” system . The passenger oxygen system is a chemically-generated oxygen system for use by passengers and cabin attendants. This type of system is designated a “continuous flow” system.
氧气系统用来为机组及旅客提供氧气。B737上安装有两套氧气系统。机组氧气系统是一个仅供机组使用的高压气态系统,这种系统被称为“稀释要求”系统。旅客氧气系统是一供旅客及乘务员使用个化学制氧系统。这种系统被称为“continuous flow”系统。
(2)        The flight crew oxygen system consists of an oxygen cylinder. Valves, indicating components, distribution tubing and oxygen mask/regulator. The crew oxygen system components are located in the forward cargo compartment and in the flight compartment.
机组氧气系统包括一个氧气瓶,阀门,指示组件,分配管道及氧气面罩/调节器。机组氧气系统组件安装在前客舱和驾驶舱内。
(3)        Oxygen flows through the pressure reducing regulator and shut off valve to the masks. Quantity (pressure) indication is provided by a gage in the flight compartment. In the event of an overpressure, the cylinder is vented to ambient through the overboard discharge. The cylinder is serviced after removal from the aircraft.
氧气通过减压调节器和关断活门流向氧气面罩。流量指示由驾驶舱内的压强计指示。一旦过压,气瓶将通过顶部释放开关进行释压。气瓶应从飞机上取下进行勤务。
(4)        The passenger oxygen system provides an emergency oxygen supply to the passengers and attendants, this system consists of passenger sevice units, control and indication. This service units contain the mask box, door latch release actuator, latching mechanism, chemical oxygen generator and oxygen mask.
旅客氧气系统为旅客及乘务员提供应急氧气,系统包括旅客服务设备,控制及指示器。这个服务设备包括氧气面罩盒、门锁释放作动筒,锁定机械装置、氧气发生器及氧气面罩。
(5)        The passenger oxygen system can be activated automatically by high cabin altitude (low cabin pressure) or manually from the flight compartment.
旅客氧气系统能够被较高的客舱高度自动启动,也能在驾驶舱人工启动。

LESSON 7 ICE AND RAIN PROTECTION防冰、防雨
一、单词
雨        Rain        保护        Protect        帮助        Aid
为…而提供        Is provided for        雨刷        Wiper        防雨剂        Repellent
叶片        Vane        卫生间        Toilet        排放        Drain
视线        Vision        皮托静压        Pitot static        探头        Probe
迎角叶片        Alpha vane        支柱管        Mast        堆积        Buildup
碰撞        Impact        强度        Strengthen        雾        Fog
导电的        conductive        涂层        coating        暴露        expose
气流        Airstream        形成        Formatting        结冰        Freeze
原因        Cause        出故障的        Faulty        损失        Loss
槽        Sink        嵌入        Embed        垫圈        gasket
装置        fitting        与…结合在一起        Are integrated with               

二、TEXT
(1)        the ice and rain protection system protects the airplane and aids the flight crew when operating under ice and rain conditions. Ice and rain protection is provided for:
1)        wing leading edge slats outboard of each engine.
2)        Flight compartment windows (heat, wiper, rain repellent).
3)        Pitot static and temperature probes.
4)        Alpha vanes.
5)        Toilet drains.
防冰、防雨系统用于保护飞机及帮助机组在雨雪天气下操作飞机。此系统为下列部件提供保护:
1)        发动机外前缘缝翼;
2)        驾驶舱玻璃窗(加热、雨刷、防雨剂);
3)        皮托静压管及总温探头;
4)        迎角叶片;
5)        厕所排水。
(2)        Wing leading slats use hot air from the pneumatic system. Flight compartment windows are electrically heated. The wipers and rain repellent are used for providing clear vision. The pitot static probes, alpha vanes, drain masts, and toilet drains use electric heaters.
前缘缝翼用增压系统的热引气加温。驾驶舱窗口用电加温。雨刷和防雨剂用来提供清晰视野。皮托静压探头、迎角叶片、排水管及厕所排水都是用电加温。
(3)        The wing anti-ice system prevents ice buildup on the wing leading edge slats, this system consists of air supply ducts, valves, terminal switches, controls and indications.
防冰系统可防止冰在缝翼前缘堆积,此系统包括供气管道、活门、终端开关、控制及指示器。
(4)        The window heat system improves the impact strength of the flight compartment windows and prevents fog and ice-buildup, this system consists of conductive coating in the window structure, heat control units, controls and indications.
窗口加热系统提高了驾驶舱窗口的撞击强度并防止雾和冰的堆积,此系统包括窗口结构上的导电涂层、加热控制组件、控制及指示器。
(5)        The pitot static probes, temperature probe and alpha vanes provide air data information to the various using system, they are located on the left and right sides of the forward fuselage. Since all the probes and vanes are exposed to the airstream, internal heating is provided to prevent ice formation. Freezing could cause faulty inputs or possible loss of all data.
皮托静压探头、总温探头和迎角叶片用来提供大气数据信息给不同的应用系统,他们位于前机身在右侧。因为所有的探头及叶片都暴露在气流里,需要加热以防止结冰。结冰可以导致所有数据的丢失或输入错误信息。
(6)        The drain anti-icing system prevents ice buildup on the drains from the toilets and lavatory sinks. The aft toilet drain heater is embedded in gasket between the drain tube and the drain outlet fitting. The lavatory sink drain heater are integrated with the drain mast. The power supply for the toilet drain heaters is 115 volts ac and for the lavatory sink drain is 115 volts ac or 28 volts ac.
排水防冰系统防止在卫生间及其水池的排水装置上积冰。后厕所加热器用垫片嵌入在排水管道与外流排水装置之间。厕所洗手池加热器与排水竖管连在一起。为厕所排水管加热用的是115V直流电,为厕所洗手池加热用的是115V直流或28V直流电。
LESSON 8 THE POTABLE WATER SYSTEM 饮用水系统
一、单词
饮用水        Potable water        浪废        Waste        由…组成        Be composed of
油箱        tank        数量        Quantity        制作        Construct
支架        bracket        3.785公升        U.S. gallon        4.546公升        Imperial gallon
园筒形的        Cylindrical        覆盖层        blanket        充注管道        Fill line
外泄管道        Overflow line        水量传感器        Quantity transmitter        容积        Capacity
簧片        Reed        二极管        Diode        浮子        Float
磁铁        Magnet        包围        Surround        标明        Label
关联的        associate        相应的        corresponding        空        emptiness
二、TEXT
(1)        the potable water system supplies potable water to the galleys and lavatories. The waste system is for storing and removing waste from the toilets. The water and waste system is composed of independent but related systems.
饮用水系统为机上厨房及卫生间提供饮用水。水系统是用于贮水及排放卫生间废水饮用水及废水系统是由相互独立并相互关联的系统。
(2)        The potable water system consists of a water tank, quantity indication, pressurization components, and distribution tubing. The water tank and pressurization components are located aft of the aft cargo compartment. The quantity indication is in the aft section of the passenger cabin.
饮用水系统由一个水箱、流量指示器、增压组件及分配管道组成。水箱及增压组件位于后货舱的后面,流里指示器位于客舱后部。
(3)        The water tank stores potable water for use by the passengers and crew.the tank is constructed of fiberglass and attached by struts and mounting brackets to the airplane structure. The 30 U.S. gallon tank is cylindrical. It is protected from freezing by a 3-pieces fiberglass blanket. On the upper section of the tank are connections for the air pressure line, fill line, overflow line, supply line, and a quantity transmitter, the fill and overflow valve is used to fill the tank to the capacity determined by a standpipe, this valve is operated a handle. A drain valve is located on the bottom of the tank.
水箱用以贮存供旅客及机组使用 的饮用水。水箱由玻璃纤维制成,并固定在飞机桁架上。30加仑的圆柱形水箱。用三个玻璃纤维垫片防止结冰。水箱上部连结着一个空气连接管道,充注管道,过流管道,供水管道及一个流量传感器,注水及过流阀       此阀门被一个手柄控制。一个排放活门被安装在水箱底部。
(4)        The quantity indication shows the amount of water in the tank. The quantity transmitter consists of 10 reed switches and 3 inside a tube. A float with 3 magnets surrounds the tube. In addition, the indicator consists of 5 lights the tank determines the position of the float. The magnets on the float close the associated reed switches. Using the push button on the quantity indicator, allows the corresponding quantity lights to illuminate if the tank is emptiness, the E light is illuminated, if the tank is full, all lights are illuminated.
流量指示器显示水箱水量。流量传感器包括10个簧片、3个管道。1个浮子和3个磁铁包围着管道。另外,指示器包括5个水位指示灯。浮子上的磁铁与弹簧开关相关联。按下水量指示器上的按钮,当水箱空了时,相关的指示灯E灯就会亮,若水箱是满的,所有的灯都会亮。

LESSON 9 FLIGHT DECK LIGHTING 飞行面板照明
一、单词
照明        Lighting        照明        Illumination        舒适        Comfort
最佳的        Optimum        效能        Performance        操作        Handing
主要的        Major        可变的        Available        强度        Strength
总体的        Integral        机长        Captain        副驾驶        First office
遮光板        Glareshield        发荧光的        Fluorescent        泛光灯        Floodlight
标记        Identify        顺时针方向的        Clockwise        增长        Increase
亮度        Brightness        白灼灯        Incandescent        自动驾驶仪        Autopilot
AFDS        Autopilot flight director system        暗淡        Dim        试验        Test
空间        Space        控制台        Control stand        与…类似        Similar to
推力手柄盘        Thrust lever quadrant        电路跳开关        Circuit breaker               
二、TEXT
(1)        the purpose of the lighting system is to provide the necessary illumination for passenger comfort, optimum flight crew work performance, service and cargo handling, and provide for lighting undremergency conditions.
灯光系统的作用是为旅客舒适、极佳的机组工作效能、服务及货舱操作,及在应急条件下提供灯光。
(2)        The major systems are :flight compartment lights, passenger compartment lights, exterior lights and emergency lights. In this lesson, we will introduce the flight deck lighting only.
主系统包括:驾驶舱灯光、客舱灯光、外部灯光及应急灯光。本文中,我们将只讲驾驶舱灯光。
(3)        Variable intensity controls for the integral instrument and main instrument panel lights are identified as PANEL and located on the lower portion of the captain’s and first officer’s panels. The captain’s variable intensity PANEL switch controls these lights on the captain’s main panel, the center panel and the glareshied. The first officer’s PANEL switch controls these lights on the first officer’s panel.
亮度调节面板作为调节亮度的整体及主要手,段位于机长及副驾面板的下方。机长的亮度调节面板开关控制着机长面板、中央面板及遮光板上的灯光。副驾驶面板开关控制副驾驶面板上的灯光。
(4)        White fluorescent floodlights are positioned under the glareshield to direct background lighting onto the main panels. One variable –intensity switch, which controls these lights, is on the lower portion of the captain’s main panel and identified as ACKGROUND, movement of this switch in a clockwise direction increases the brightness of the fluorescent lights.
白色的荧光屏泛光灯位于遮光板下方。一个亮度调节开关控制着这些灯,它是位于机长主面板下方标识为ACKGROUND的开关,顺时针转动开关增加荧光屏亮度。
(5)        White incandescent floodlights are positioned above the autopilot flight director sysem (afds)panel, one variable –intensity switch, which controls these lights, is on the lower portion of the captain’s main panel and identified as AFDS FLOOD. Clockwise movement of this switch increases brightness of the lights
白色荧光指示灯位于自动飞行指引系统面板上方,一个控制这些灯的亮度调节开关位于机长主面板的下方,并标识为AFDSFLOOD。顺时针转动开关可增加灯光亮度。
(6)        The flight compartment system indicator lights may be dimmed or tested by the use of a LIGHT switch located on the center instrument panel. Placing the switch in the test position illuminates the indicator lights, and placing the switch in the dim position dims them.
驾驶舱指示器系统的灯光可通过中央面板上的“灯光”开关来调暗或测试。将开关置于测试位照亮指示器灯光,将开关置于暗位来调暗灯光。
(7)        The control stand instrument panels are integrally lighted similar to those unit on the main instrument panels. In addition, there is a white flood light on the forward overhead panel which directs light downward onto the thrust lever quadrant on the control stand. Variable-intensity controls for these lights are on the control stand and identified as PANEL and FLOOD.
控制台面板整体灯光的控制与主面板灯光相似。另外,有一个白色的泛光灯在顶置面板上,它可直接为控制台上的推力手柄扇形盘提供照明,这些灯光的亮度调节钮在控制台上标识为“FLOOD”。
(8)        a variable intensity control for the integral instrument panel lights and for instrument lights on the overhead panels is located on the forward overhead panels and identified as PANEL.
(9)        In addition, there are two map lights mounted above each pilot’s seat, two circuit breaker panel floodlights on the sidewall by each pilot’s seat, two white dome lights on the circuit breaker panels behind the crew provide general flight compartment area illumination.


LESSON 10 737 ELECTRONIC EQUIPMENT BAY        737电子设备舱
一、单词
可以达到的        accessible        到达        reach        修改        modification
排故        Troubleshooting        简化        Simplify        可移动的        Removable
装配        Assembly        支架        Rack        搁板        Shelf
大气数据        Air data        计算机        Computer        自动油门        Auto throttle
数字式        Digital        失速        Stall        警告        Warning
温度        Temperature        控制器        Controller        设置        Location
飞行管理计算机        Flight management computer        惯性基准系统        Inertial reference system        模拟量        Analog
适配器        Adapter        发动机        Engine        振动        Vibration
信号        Signal        选择呼叫系统        Selective calling system        偏航阻尼器        Yaw damper
综合飞行系统附件组件        Integrated flight system accessory unit        旅客广播        Passenger address        放大器        Amplifier
遥控电子装置        Remote equipment unit        甚高频        Very hight frequency        通信        Communication
空中交通管制        Air traffic control        数字飞行数据采集装置        Digital flight data acquisition        测距机        Distance measuring equipment
静变流机        Static inverter        电瓶充电器        Battery charge        变压器        transformer
整流器        Rectifier        减速板        Speed break        襟翼        Flap
缝翼        Slat        电门        Switch        过热        Overheat
失火        Fire        探测器        detector        导航        navigation
继电器        relay                               
二、TEXT
(1)        electronic equipments are located in a compartment below the cabin floor aft or the nose gear. This electronic equipment compartment is accessible on the ground through a door in the lower fuselage. If necessary, the compartment can be reached in flight through a floor panel In the forward part of the passenger cabin. Modification and troubleshooting are simplified through use of easily removable shelf assemblies.
电子设备被安装在客舱地板下前轮舱的后面。电子设备组件可通过机身下方的检修口盖来接近。如果有必要,在飞行中,这些组件可通过客舱前端地板上的面板来接近。维修或排故通过用可更换件的装配很容易完成。
(2)        There are 3 electronic equipment racks in the electronic equipment bay. They are rack E1, E2 and rack E3.
电子设备舱中有三个电子设备架,分别是:E1,E2,E3.
(3)        Air data computer ,auto throttle computer, digital stall warning computer, auto –slat computer, cabin temperature controller, and pressure controller are located on rackE1, shelf1. flight management computer (FMC), inertial reference system relay, digital analog adapter and engine vibration signal conditional are located on rack E1, shelf2. SELCAL, flight control computer, yaw damper compute and IFSAU are located on rack E1, shelf3.
大气数据计算机、自动油门计算机、数字失速警告机算机、自动缝翼计算机、客舱温度计算机和压力控制器位于E1架上。飞行管理计算机、惯性基准系统继电器、数模适配器位于E2架上。选择呼叫系统、飞行控制计算机、偏航阻尼器及综合飞行系统附件组件位于E3架。
(4)        The electronic equipment rack E2 has four shelves. Shelf E2-1 contains P/A ampl, REU and VHF communication wquipments, shelf E2-2 contains ATC, DFDAU and DME. Shelf E2-3 contains symbol generator, shelf E2-4 contains radio altimeter, ground proximity warning equipment ,ADF(automatic direction finder) and marker beacon etc.
E2架有四层,第一层有旅客广播放大器、遥控电子组件及甚高频通讯;第二层包括ATC应答机、数字式飞行数据采集器及测距机;第三层包括SYMBOL发电机;第四层有雷达高度,地面接近警告设备,自动定向机及MAKER BEACON等。
(5)        The static inverter, battery charger, transformers, rectifiers, auto speed brake, flap and slat position switches, overheat and fire detector, navigation switches and a lot os relays are located on electronic equipment rack E3.
静变流机、电瓶充电器、变压器、整流器、自动减速板、襟翼机缝翼位置开关、过热及火警探测器、导航电门及许多继电器安装在E3电子设备架上。
LESSON 11 ELECTRICAL POWER 电源系统
一、单词:
电源        Electrical power        不同的        Various        电瓶        battery
发电机        Generator        地面保障设备        Ground support equipment        交流        Alternating current
驱动        Drive        插座        Receptacle        转换        Convertion
分布        Distribute        产生        Produce        主要是        Primarily
额定容量        Is rated at         千伏安        Kilovolt ampere        汇流条        Slip-ring
换向器        Commutator        电刷        Brush        励磁器        Exciter
完整的        Complete        整流器        Rectifier        磁极        Pole
磁场        Field        转 子        Armature        装有        Is supplied with
调节器        Regulator        引出        Develop        送入        Fed into
定子        Stator        恒速传动装置        Constant speed drive        附件齿轮箱        Accessory gearbox
关键的        critical        缺少        absence        变压器        transformer
备份的        backup                               
二、TEXT:
(1)        the electrical power is used for the control, operation, and indication of the various airplane systems on the ground and inflight. The electrical power is obtained from the battery, generator and ground support equipment. Is is controlled and monitored prior to distribution as 115 volt ac, 28 volt ac and 28 volt dc supply to using systems.
电源系统用于在飞行或地面飞机系统的控制、操作及指示。电源来源于电瓶、发电机及地面电源设备。它被控制并监控优先分配成115V交流、28V交流及28V直流提供给用户系统。
(2)        The alternating current power is supplied by two engine driven generators for normal infligt operation. A generator, driven by the auxiliary power unit, can supply all power for ground or flight operation。 power can be supplied on the ground through the external power (ac) receptacle. The dc power is supplied from the battery or conversion from the ac power.
正常飞行时,交流电由两台发动机驱动发电机提供。一台发电机由辅助动力装置驱动,能够在飞行操作中提供各种电源。飞机在地面时可通过地面电源插头由地面电源供电。直流电由电瓶或交流电转换而来。
(3)        The ac and dc power is distributed to the various system through the left and right load control centers in the flight compartment. The control and indication of the electrical system is from the P5 overhead panel in the flight compartment.
直流及交流电源在驾驶舱中通过左右LOAD控制中心被分配到不同系统中去。电源系统的指示及控制位于驾驶舱P5顶置面板上。
(4)        The generators driven by the engine produce the ac power required by the airplane systems primarily for flight operation. The ac generator is rated at 50 kilovolt –amperes, 120/208 volts, 400Hz . The unit is without slip-rings.commutator, or brushes on either the main generator or the exciter. A complete generator assembly consists of an exciter generator, a rotating rectifier and a main gererator.
发电机由发电机驱动产生飞行操作中各系统所需的交流电。交流发电机额定功率为50KV/A,120/208伏,400Hz,在每个主发电机或励磁器上没有汇流坏、换向器及电刷。一个完整的发电机组件上包括一个激励发电机,一个转子整流器及主发电机。
(5)        The exciter consists of a six – pole dc field and a rotating armature. The exciter field is supplied with dc power from the voltage regulator. This causes a 3-phase voltage to be developed in the exciter armature. The 3-phase voltage is rectified and fed into the ac generator rotating field. The rotating field generates the useful 115v output voltage in the ac stator.
励磁器上包括一个6柱直流磁场和一个转子电枢。激励磁场由电压调节器来的直流电源提供,使得在励磁电枢中引出3相电压。这3相电压被整流并注入交流发电机转子磁场,在交流定子电枢输出可用的115V电压。
(6)        The constant speed drive(CSD) is located on the left side of the engine, on the front of the accessory gearbox. The purpose of the CSD is to convert the variable speed of the engine to a constant speed for the driven generator to produce ac power at constant frequency.
恒速传动装置位于发动机的左侧,附件齿轮箱前面。恒速齿轮箱的作用是将发动机变化的速度转换成恒速,以使发电机产生恒频交流电。
(7)        The electrical power for the ground operation of all electrical loads on the airplane is supplied by an external 3-phase, 115vlot , 400Hertz alternating current system. The power is supplied through an external power receptacle. The ac external power receptacle is located on the right side of the airplane forward of the nose wheel well.
飞机在地面进行操作时,使用外部的3相115v,400Hz交流电源。外部电源通过一个外部电源插座连接飞机系统。外部交流电源插座位于飞机前轮舱右侧。
(8)        The battery is located in the electronic compartment, left side just forward of the E2 rack. The purpose of the battery is to provide dc power to critical airplane systems in absence of normal dc supply from the transformer rectifier. It is also used as a backup power for the ac system control and protection and for starting the APU.
电瓶安装于电子设备舱,E2架左侧。电瓶用来在无法通过转换整流器得到正常直流电时为飞机关键系统提供直流电。同时也作为直流系统控制、保护及APU启动的备用直流电源。
(9)        Three transformer rectifier units are located in the electronic compartment on E3 rack. The purpose of the 3 transformer rectifiers is to convert 115 vlot ac ,400Hz, 3-phase power to 28 vlot dc power for use by the airplane’s systems.
3个整流器组件位于电子设备舱E3架上。他们的作用是将115v,400Hz交流电转换成飞机系统使用的28v直流电。
(10)        The purpose of electrical power distribution system is to provide and control generated ac and dc power for use by the various airplane systems, the distribution system consists of 115 volt ac, 28 vlot ac and 28 vlot dc power obtained from generators and battery.
电源分配系统的作用是提供并控制飞行不同系统所使用的交流、直流电源,分配系统包括从发电机和电瓶来的115v交流电,28v交流电及28v直流电。
LESSON 12 FUEL 燃油
一、单词
燃油        Fuel        存贮        Store        运送        Deliver
细分        Subdivide        贮藏        Storage        加燃油        Fueling
油箱        Tank        通气装置        Vent        通气均压油箱        Vent surge tank
暂时的        Temporary        燃油密封的        Fueling tight        金属和金属        Metal to metal
装配        Fit        化合剂        Compound        密封剂        Sealing compound
紧固件        Fastener        接口        Joint        翼肋        Rib
缓冲挡板        Baffer        单向活门        Check valve        增压泵        Boost pump
离开        Away off        加油站        Fueling station        填充        Fill
部份的        Partially        完全地        Completely        另一方面        Alternately
入口        port        转移         Transfer        浮子        Float
过满        Overfill        防止…做…        Prevent M from doing        放油        Defueling
利用        Utilize        用泵抽        Boost pump        供油        Feed
各自的                交输        Crossfeed        可使用的        Usable
重量        Weight        容量        Capacitance        杆        Stick
芯片        Chip        微电子计算机        Microcomputer        液晶显示        Liquid crystal display
电阻电流        Resistive current        泄漏        Leakage        不能接受的        Unacceptable
错误        Error        代码        Code        刻度        Graduate
带        tape        高度        Height               
二、TEXT
(1)        the purpose of the fuel system is to store and deliver fuel to the engine and APU. The fuel system is subdivided into dotrage, fueling, distribution and indicating systems.
燃油系统用于贮存并传输燃油给发动机和APU。燃油系统细分为贮藏、供油、分配及指示系统。
(2)        There are 3 tanks for fuel storage and 2 vent surge tanks for temporary fuel storage. Tank No.1 is located in the left wing, tank No.2 is located in the right wing and center tank is located in the fuselage under the passenger cabin. The 2 vent surge tanks are located outboard of the main tanks. All fuel tanks are fuel tight. Close metal-to –metal fit of all parts forms the basic seal. Sealing compounds and sealed fasteners are used on all joints to complete the fluid tight seal. Two of the wing ribs contain a series of baffle check valves to prevent fuel flow away from the boost pumps.
燃油系统有3个贮油箱和2个用于临时贮油的油箱。1号油箱位于左机翼,2号油箱位于右机翼,中央油箱位于机身客舱下方。2个通气均压油箱位于两个主油箱的外侧。Close metal-to –metal fit of all parts forms the basic seal.所有的油箱都是密封的。所有的接头处都用密封剂和密封紧固件进行密封。两个翼肋处包括又个连续的缓冲隔板单向活门,防止燃油从增压泵中流出。
(3)        The fueling system provides a means of filling the fuel tanks on the airplane. Fueling can be accomplished by the use of a single pressure fueling station through which all tanks can be filled partially or completely. Alternately, the main tanks(No.1 and No.2) can be filled through the overwing ports. The center tank can be filled by transferring fuel from the main tanks using the fuel station.
燃油系统提供一种在飞机上给油箱注油的方式。供油可以通过一个单压力加油口来完成,通过它,可以为所有的油箱全部或部份的加油。另一方面,主油箱(1、2号)可以通过机翼上方口注油。中央油箱可以用加油站从主油箱中传输来过。
(4)        The components associated with the fueling system are the fueling station located under the right wing leading edge outboard of the engine, 3 float switches – one for each tank, prevent the tanks from being overfilled. The tank fueling float switches are located near the top of e        ach tank and sense full tank quantity. The tanks can be filled to any desired quantity, the float switches sense full tank condition and automatically stop the fueling. Power requirements are supplied by ground power, APU or the battery. Pressure fueling can also be done manually. Maximum fuel pressure is 55 psi.
构成燃油系统的组件有位于右翼前缘襟翼外侧的加油口,3个浮子开关-每油箱一个,用来防止油箱过满。浮子开关位于油箱顶部测量油量。油箱油量可按要求存贮,浮子开关测量油量并能自动停止加油。电源可由地面电源、APU或电瓶提供。压力加油也可人工操作。最大燃油压力为55psi。
(5)        The distribution system allows fuel to be supplied to the engines and APU. In addition, the system can be used for defueling the tanks and for fuel transfer between the tanks. The distribution system utilizes pumps, valves and truing for engine and APU feed. The fueling station is used for defueling and transfer operations which are only possible on the ground.
燃油分配系统可为发动机及APU供油。另外,分配系统可用于油箱放油及油箱之间的输油。分配系统利用泵、阀门及涡轮为发动机及APU供油。加油口只能在地面进行放油及输油操作。
(6)        Fuel is first supplied to both engines from the center tank and then from the respective tanks to engines. The crossfeed valve allows fuel from one tank to be supplied to both engine. Fuel to the APU is primarily supplied from tank No.1, but it can be supplied from any tank.
燃油 is first supplied to both engines from the center tank and then from the respective tanks to engines.交输活门允许燃油从一个油箱同时给两台发动机供油。为APU供油主要是用1号油箱,但也可从任一油箱供油。
(7)        The fuel quantity indicating units measure the weight of usable fuel in the tanks. Two types of quantity indicators are used, one is capacitance indication, another one is a manual measuring stick.
油量指示组件测量油箱中油的重量。一般使用两种油量指示,一个是容量指示,一种是人工用棒测量。
(8)        Digital fuel quantity indicators show the weight of fuel ing each tank. Each indicator consists of a single chip microcomputer system and a digital liquid crystal display(LCD). The microcomputer measures the capacitance and resistive current in the tank units. It monitors the leakage current and when is reaches an unacceptable level, an drror code o through 10 illuminates to assist in troubleshooting the system.
数字油量指示器显示每个油箱中的油量。每个指示器包括一个单芯片微型计算机系统和一个数字式液晶显示器。微型电子计算机测量油箱中的容量和电阻电流。它监控着泄漏电流,当泄漏达到一定程度时,会指示一个0到10的代码,以帮助进行系统排故。
(9)        The measuring sticks are graduated tape which can be pulled down for reading of fuel height.
测量棒是一个刻度尺,它能够放进油箱来读出燃油深度。


LESSON 13 HYDRAULIC POWER       
一、        单词
液压的        Hydraulic        动力,电源        Powr        反推装置        Reverser
共享        Share        责任、负责                液压传动的        Dydrallically
有要求的        On demond        起落架        Landing gear        前轮转弯        Nose wheel steering
副翼        aileron        动力控制组件        Power control unit        升降舵        Elevator
方向舵        Rudder        飞行扰流板        Flight spoiler        刹车        Brake
动力转换装置        Driven transfer unit        发动机传动泵        Engine driven pump        电动马达传动泵        Electric motor driven pump
关闭        Shutoff        截流阀        Shutoff valve        油箱        Reservoir
压力过滤器        Pressure filter        消除        Relief        润滑        Lubricate
热交换器        Exchanger        返回        Return        后缘        Trailing edge
前缘        Leading edge        交替的        Alternate        单独地        individually
龙骨        Keel beam        带保护罩的开关        Guarded switch        节       
二、TEXT
(1)        three separate and independent hydraulic system are provided to power the flight controls, landing gear, and thrust reversers. System A and system B are full-time operating system during flight that share rsesponsibility for all hydraulically powered components. The standby system is operated only on demand.
三个分隔独立的液压系统用以为飞行控制、起落架和反推装置提供动力。A系统和B系统在飞行中为全时操作系统,共同负责对所有受液压动力控制的组件进行控制。备用系统只在需要时工作。
(2)        System A draulic power operates the following systems:
Landing gear
Nose wheel steering
Left thrust reverser
Ailerons – power control unit and autopilot actuator
Elevators – power control unit and autopilot actuator.
Elevator feel
Rudder
Inboard flight spoilers 3 and 6
Cround spoilers.
Alternate brakes.
Power transfer unit.
   A系统为下列系统提供动力:
   起落架
   前轮转弯系统
   左反推装置
   副翼—动力控制组件及自动驾驶作动筒
   升降舵—动力控制组件及自动驾驶作动筒
   升降舵FEEL
   方向舵
   内侧飞行扰流板3#及6#
   地面扰流板
   备用刹车
   动力传输组件
(3)        System A pressure is provided by one engine driven pump(EDP) and one electric motor driven pump(EMDP). A 28v dc motor operated shutoff valve in the supply line between the reservoir and the engine driven pump is normally open . this valve is closed and stops the flow of hydraulic fluid to the engine when the fire handle is pulled.
A系统压力由一个发动机驱动泵和一个电动免马达驱动泵提供。一个28v直流免达操作位于油箱及发动机驱动泵之间传送管内的截流阀,正常情况下,它是打开的。当火警手柄拉上时,阀门关闭并停止压力流向发动机。
(4)        Normal system configuration is with both pumps operating to output fluid pressurized to 3000 psi through the pressure module to the using system. The pressure module contains pressure filter, low pressure switches, check valves and a pressure relief valve. Cooling and lubricating fluid from the pumps is filtered and routed through a heat exchanger in the number one fuel tank before entering the reservoir. Return fluid from the suing systems is filtered at the return module before entering the reservoir.
系统正常构造是通过操作泵输出3000PSI的压力,通过压力组件给用户系统。压力组件包括压力油滤,低压开关,单向活门和一个压力释放活门。
(5)        Hydraulic system B provides fluid under pressure of 3000 psi to portions of the flight control, landing gear, and thrust reverser systems. System B hydraulic power operates the following system:
Main wheel brakes
Right thrust reverser
Ailerons – power control unit and autopilot actuator.
Elevators – power control unit and autopilot actuator.
Elevator feel
Rudder
Outboard flight spoiler 2 and 7
Trailing edge flaps
Leading edge flaps and slats
Alternate landing gear retraction
Alternate nose wheel steering
   液压B系统提供小于3000PSI的压力给飞行控制、起落架及反推装置系统。液压B系统为下列系统提供压力:
   主轮刹车
   右反推装置
   副翼—动力控制组件及自动驾驶作动筒
   升降舵—动力控制组件及自动驾驶作动筒
   升降舵FEEL
   方向舵
   外侧飞行扰流板2#和7#
   后缘襟翼
   前缘襟翼和缝翼
   备用起落架收起
   备用前轮转弯
(6)        System Bhydraulic pressoure is provided by two hydraulic pumps, an EDP(engine driven pump)         and an EMDP(electric motor driven pump).the pumps are supplied with fluid from a reservoir pressurized with pneumatic air from the ECS(environmental control system). Output of the pumps is routed to a pressure module and from there to the using systems. Return fluid from the using system is routed through a return filter module then to the reservoir. Drain fluid from both pumps is routed through a heat exchanger before going to the reservoir.
   B系统压力油两个液压泵、一个发动机驱动泵和一个电动马达泵来提供。泵内装有从油箱来的液体,用环境控制系统的增压空气产生压力。泵内输出的压力被送往压力组件并从这儿传给用户系统。从用户系统返回的流体通过一个回油滤组件被送往油箱。泵中排出的流体通过一个热交换器后被送往油箱。
(7)        The standby system components are located in the main gear wheel well,on the keel beam and the aft bulkhead. The standby pump is operated when required to power the rudder, thrust reversers, or to extend the leading edge devices. The pump can be turned on by either of three guarded switches on the forward overhead panel(P5). In addition, the pump automatically switches on and provides standby pressure to the rudder whenever hydraulic system A or Bis lost, the flaps are not up, the airplane is either in the air or on the ground with wheel speed above 60 knots, and at least one flight control switch, system A or B, is ON.
备用系统组件位于主轮舱,压力隔板后方龙骨上方。当需要操作方向舵、反推装置或打开前缘设备时,备用泵开始工作。这个泵能够被头顶(P5)面板前方的三个带保护罩的开关中的任一个打开。另外,无论A系统或B系统哪一个失效时,这个泵将自动工作并为方向舵提供备用压力,襟翼不会打开,飞机无论在空中或地面轮速都将大于60节,并且至少有一个飞行控制开关,A系统或B系统是打开的。
(8)        When the standby pump is turned on, pressurized fluid is delivered to two motor-operated shutoff valves on the standby pressure module and to two thrust reverser shuttlee valves. The motor operated shutoff valves which control pressure to the leading edge devices and to the standby rudder actrator are individually controlled by switches on the forward overhead panel. The standby rudder shutoff valve is also opened when the standby hydraulic pump is automatically turned on.
当备用泵打开时,压力被送往备用压力组件的两个马达控制的截流阀和两个反推装置截流阀上。马达控制截流阀控制提供给前缘设备的压力并通过前顶置面板分别控制备用方向舵作动筒。当备用液压泵自动工作时,备用方向舵截流阀也同时打开。
LESSON 14 LANDING GEAR起落架
一、单词
主起落架        Main gear        前起落架        Nose gear        梁        Spar
防滑的        Antiskid        无效的        Inoperative        自动刹车        Autobrake
解除预位        Disarm        使动作        Actuate        借助于…        By means of
减压        Depressurize        电磁线圈        Solenoid        限制        Restrict
相应的        Respective        移动,变换        Transit        一致        Agree
充当        Serve as        形态        Configuration        在…情况下        In case of
故障        Malfunction        减震支柱        Shock strut        缓冲        Absorb
碰撞