航空工程英语基础（中英文对照）

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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        Inpact        冲撞        Shock        振动        Vibration
滑行        Taxi        整流罩        Fairing        机构        Mechanism
保证        Assure        阻力杆        Drag brace        扭力臂        Torsion link
圆筒        Cylinder        轴颈销钉        Trunnion pin        稳定性        Stability
牵引        tow        环        Lug        横向螺栓        crossbolt
牵引杆        tow bar        碰撞        Bump        注入        Charge
氮气        Nitrogen        折迭        Fold        环        collar
转弯力矩        Turning moment        手轮        Handwheel        脚蹬        pedal
二、TEXT
(1)        the landing gear consists of two main gear and a nose gear. The main gear are located inboard of each engine, aft of the rear wing spar. The nose gear is located below the aft bulkhead of the flight compartment. Braking is provided by four brake assemblies, one mounted on each main gear wheel. Landing gear control and indication components located in the flight compartment include: the landing gear selector lever and indication lights, manual extension handles, parking brake lever and indicator, nose gear steering control wheel, antiskid control switch and inoperative indicator, and the autobrake control switch and disarm indicator.
起落架包括两个主起落架和一个前起落架。主起落架位于每台发动机内侧，翼尾梁后部。前起落架位于驾驶舱后压力隔板下方。刹车系统由四个刹车组件组成，一个安装在每个主起落架舱。起落架控制及指示组件安装在驾驶舱，包括：起落架选择手柄和指示灯，人工释放手柄，停留刹车手柄及指示器，前轮控制器，防滑控制开关及无效指示器，及自动刹车控制及解除预位控制。
(2)        The landing gear is hydraulically actuated to extend and retract by means of a landing gear selector lever located on the center instrument panel (P2-2).when the selector lever is placed in the UP position, all three gear retract. Each main gear retracts into the fuselage. The nose gear retracts into the nose wheel well. When the selector lever is placed in the DOWN position, all three gear extend. The OFF position is the normal cruise mode and all landing gear are locked up and depressurized. A solenoid lock system restricts the selector lever to the UP position when the airplane is on the ground .
起落架借助于位于中央控制面板P2-2的起落架选择手柄通过液压作动进行起落架收放操作。当起落架控制手柄置于“UP”位时，三个起落架收起。各主起落架收起到机身内；前起落架收起到前轮舱。当控制手柄置于“DOWN”位时，三个起落架放下。置于“OFF”位为正常巡航模式，起落架锁好并释压。当飞机在地面时，一个电磁锁系统限定控制手柄在“UP”位。
(3)        Six lights located above the landing gear selector lever provide indication and warning for the landing gear. A green light is illuminated when the respective gear is down and locked .the red light is illuminated when the landing gear is in transit or the landing gear lever and the landing gear do not agree. The red lights also serve as warning lights when the airplane is in a possible landing configuration and the gear is not down and locked.
六个位于起落架手柄上方的指示灯用来起落架指示及警告。当起落架移动或起落架手柄和起落架不一致时绿灯亮。红灯亮用作当飞机可能在降落状态而起落架没有放下并锁好时，用作警告。
(4)        Three red manual extension handles are located on the floor of the flight compartment. Just aft of the first officer’s station, for manual extension of the landing gear in case of hydraulic malfunction in hydraulic system “A”. the manual extension handles are independently operated for each gear. The landing gear selector lever should be in the OFF position for manual extension.
三个红色的人工放下手柄位于驾驶舱地板上，正位于副驾位置，用来在液压“A”系统发生故障的情况下，人工放下起落架。三个人工释放手柄独立控制每个起落架。人工放下起落架时，起落架选择手柄将被放在OFF位。
(5)        The main gear provides the support for the aft section of the fuselage. It uses a shock strut to absorb impact on landing，And shocks and vibration while taxiing . each main gear is hydraulically actuated to retract inboard into the fuselage. Doors and wheel well seals provide fairing with the gear retracted. Lock mechanisms and sensors assure that the main gear is down and locked or up and locked.
主起落架支撑机身和部。通过一个减震支柱来减弱与地面的撞击，及滑行时的冲撞和振动。各主起落架都是通过液压作动向内侧收起到机身内部。可通过舱门及轮舱密封性来判断起落架收起是否失效。上锁机构和传感器确保主起落架放下锁好或收起锁好。
(6)        The nose gear, located below the aft bulkhead of the control cabin, provides the support for the forward section of the fuselage. The nose gear includes a drag brace, shock strut, torsion links, a hydrauic nose gear actuator and a hydraulic lock actuator. The shock strut consists of inner and outer cylinders. The upper part of the outer cylinderis “Y” shaped with arms extended to the sidewalls of the wheel well. Trunnion pins connect the gear to airplane structure. The “Y” arms and pins provide lateral stability. The gear rotates about the trunnion pins during extension and retraction. A tow lug and crossbolt are installed for attaching a tow bar to the nose gear.
前起落架，位于驾驶舱后压力隔板的下方，为机身前段提供支撑。前起落架包括一个阻力杆、减震支柱、扭力臂、一个液压前起作动筒和一个液压锁作动筒。减震支柱包括内、外作动筒。外部作动筒的上部是一个“Y”形的有一伸向轮舱侧壁的杆。轴向销钉连接着机轮与机身。“Y”形杆和销钉可提供稳定性。轮子在收放时以轴向销钉为轴旋转。牵引环和横向螺栓安装在前起落架上用来连接牵引杆。
(7)        Shocks and bumps during taxi, take off and landing are absorbed by the shock strut which contains oil and is charged with compressed air or nitrogen. Longitudinal stability is provided by a hinged drag brace which folds upward and aft during gear retraction。for steering, the shock strut inner cylinder turns within the outer cylinder. Torsion links connected at the upper end to a steering collar and at the lower end to the shock strut inner cylinder transmit a turning moment supplied by hydraulically actuated steering cylinders. The steering is controlled by the handwheel on the pilots sidewall or by the rudder pedals. The handwheel can turn the nose wheel 78 from center and the rudder pedals at full deflection can turn the nose wheel 7 from center.
飞机在滑行、起飞及降落时的震动和撞击可通过包含滑油和注入压缩空气或氮气的减震支柱减弱消除。纵向稳定性可通过铰接的阻力杆在起练架收起时折合在上方及后方。作动时，减震支柱里面的圆柱体在外圆柱体里面转动。扭力臂。
LESSON 15 FLIGHT CONTROLS
一、单词
飞行        Flight         操纵        Control         机动动作        maneuver
水平的        Lateral        纵向的        longitudinal        垂直的        Vertical
轴        Axes        增加        Increase        升力        Lift
起飞        Takeoff        着陆        Landing        阻力        Drag
地面        Ground        被分成        Are divided into        集团        Group
主要的        Primary        次要的        Secondary        方法、手段        Means
驾驶盘        Control wheel        配平        Trim        位置        Position
导致        Cause        转 动        Rotate        姿.态        Attitude
角度        Angular        量； 值        Amount        操纵面        Control surface
建立        Establish        大小、尺寸        Magnitude        达到        Reach
再成流线型        Refair        全部的        Total        对…起作用        Act on
平衡        Balance        保持        remain        稳定的        Stable
坡度        bank        角度        Angle        降低        Lose
命令        Command        驾驶舱        Flight deck        操纵台        Control stand
传感器        Sensor        反馈        Feedback        信号        Signal
自动驾驶仪        Autopilot        转动鼓轮        bus  Drum        驾驶盘操纵        Control wheel steering
换能器        transducer        副翼操纵力限制        Aileron force limiter        考虑        Consider
升力中心        Center lift        重心        Center gravity        反向力        Counter force
横滚        Roll        俯仰（率）        Pitch rate        驾驶杆        Control column
扭力管        Torque tube        调整片        Tab        扇形盘        quadrant
操纵杆        Control rod         曲柄        Crank        供给、容许        admit
二、TEXT
(1)        the flight controls provide maneuvering control about the lateral, longitudinal, and vertical axes. They also provide increased lift for take off and landing as well as increased aerodynamic drag both in flight and on ground. Flight controls are divided into two major groups: primary and secondary. The primary flight controls consist of the ailerons, elevators, and rudder. The secondary flight controls consist of the spoilers, trailing edge flaps, leading edge devices, and the stabilizer. We will introduce the primary flight controls in this lesson.
飞行控制系统提供水平、纵向及垂直方向上的机动控制。它们同时也为飞机在地面起飞时提供升力及从空中降落时提供空气阻力。飞控系统分为两个主要部分：主飞控系统及次飞控系统。主飞行控制系统包含副翼、升降舵及方向舵。次飞控系统包含扰流板、后缘襟翼、前缘襟翼及水平安定面。本课主要讲述主飞控系统。
(2)        The aileron control system provides the means of rotating the airplane about the longitudinal axis. The aileron control system is actuated by rotation of either the captain’s or first officer’s aileron control wheel. The autopilot system also provides a control input. These inputs control a hydraulic powered system which drives the ailerons. Moving the ailerons out of their trimmed position causes the airplane to ratote and change attitude. The angular amount of control surface moved establishes the “rate-of –change”. When the desired magnitude of attitude change has been reached, the control surfaces are refaired, total forces acting on the airplane are balanced and the airplane remains stable in a bank angle. Since the airplane is in a bank, the wing loses some of its lift, so up elevator command is used by the pilot or by the autopilot.
副翼控制系统提供飞机纵向转动的方式。副翼控制系统通过转动机长或副驾位的副翼控制轮作动。自动驾驶系统也可提供控制输入。这些输入控制驱动副翼的液压动力系统。转动副翼离开配平位置，致使飞机转动并改变姿态。控制面角度的移动形成“变化率”。当姿态变化达到希望的量值时，控制面再成流线型，作用在飞机上的合力达到平衡，同时飞机在一个角度上保持稳定。因飞机有一定的角度，机翼升力降低，所以驾驶员或自动驾驶系统会给出升降舵上升的命令。
(3)         The ailerons are located on the outboard trailing edge of each wing. Other aileron components are located in 3 main areas:
l        Flight deck
The control wheels are located in the forward portion of the flight deck. The aileron trim switch is located on the control stand.
l        Wheel well area
The aileron power control units(PCU, convert a pilot or autopilot mechanical driven input to a hydraulic power driven mechanical output to drive the aileron) are located on the forward wall of the main wheel well. The autopilot aileron actuators are located on the forward wall of the main wheel well. The aileron position sensor provides two feedback postion signal from the aileron system to the A/P system.
l        Lower nose compartment
The control drum and bus drum are connected to the control wheel, located in the lower nose compartment. The roll CWS force transducer is connected between the bus drum and the control drum, the output of the force transducer provides signals to the autopilot. The aileron force limiter limits control wheel movement during A/P operation, the control wheel rotation is limited to 17°with flaps up and 25°with flaps down.
副翼位于每个机翼前缘外侧，其它副翼组件位于3个主要区域：
l        驾驶舱
控制轮位于驾驶舱前部。副翼配平开关位于控制台上。
l        轮舱区域
副翼动力控制组件（PCU，转变驾驶员或自动驾驶系统机械驱动的输入为液压驱动机械输出，用以驱动副翼）位于主轮舱前壁。自动驾驶副翼作动筒主轮舱前壁。副翼位置传感器从副翼系统提供两个位置反馈信号给自动驾驶系统。
l        机头下方
控制鼓及转动鼓轮连接到控制轮上，位于机头下方。横滚驾驶盘操纵反向换能器连接在转 动鼓轮与控制鼓之间，力量转换器的输出为自动驾驶提供信号。副翼操纵力限制器限制控制轮在自动驾驶仪操作时移动。控制轮的转动被限制在襟翼上升17°及襟翼下降25°之间。
(4)        To understand elevator poeration consider the airplane balanced about the center of lift (CL). The center of gravity (CG) is shown forward of the center of lift. The stabilizer provides a counter force to the CG. The stabilizer may be trimmed to changer the force as required to maintain balance.
The elevators are used to change the pitch attitude. Moving the elevators out of their faired position causes the airplane to change the pitch attitude about the lateral axis. The amount of elevator movement establishes the airplane pitch rate. When the desired attitude is reached, the elevators are faired and the air-plane maintains the new pitch attitude.
升降舵操作要考虑飞机相对于升力中心的平衡。重力中心一般在升力中心的前面。安定面提供一个反向力给重力中心。安定面也可以在需要时通过配平改变力量以保持平衡。
升降舵用来改变飞机俯仰姿态。移动升降舵离开它们的流线型位置，使得飞机改变水平轴上的俯仰姿态。升降舵的移动量形成俯仰率。当达到希望的姿态时，升降舵再成流线型，飞机保持新的俯仰姿态。
(5)        Two control columns provide pitch control of the airplane . each control column extends through the floor into the lower nose compartment. A torque tube connects the control columns together. The control columns allow the pilots to control the airplane about the lateral axis.
两个驾驶杆提供飞机俯仰控制。每个控制杆通过地板沿伸到前舱。一个扭个管将驾驶杆连在一起。驾驶杆允许驾驶员沿水平轴控制飞机。
(6)        Control about the vertical axis is provided by the rudder. Control is provided by a single rudder without tab. The rudder is pedal operated by the captain or the first officer. Pedal movement rotates the forward quadrants, which are cable connected to the aft quadrant. Rotation of the aft quadrant moves a control rod connected to a torque tube. Rotation of the torque tube moves a crank connected to the rudder power control unit linkage. This admits hydraulic fluid to the actuating cylinder, which moves the rudder.
飞机垂直方向上的控制由方向舵提供。通过一个单独的不含调整片的方向舵提供控制。方向舵由机长或副驾驶的脚蹬控制。随着脚蹬的移动，使得前扇形盘转动，前扇形盘由线缆连接到后扇形盘。后扇形盘的转动带动一个连接着一个扭力管的操纵杆。扭力管的转动带动了连接着方向舵动力控制组件的曲柄移动，它提供液压压力给员筒型作动筒，作的筒作的使得方向舵移动。
LESSON 16 POWER PLANT (1)
一、单词
动力装置        Power plant        推力        thrust        帮助        aid
反推装置        Thrust reverser        驱动        drive        齿轮箱        gearbox
高函道比        High bypass rate        涡轮风扇        turbofan        装配        fitting
相同的                轴流        axes        转子        rotor
定子叶片        State vane        压缩机        compressure        经由        Via
轴        shaft        涡轮        turbine        机械地        mechanically
独立的        independent        相互        Each other        气流        Airstream
燃烧        combusion        环形的                提高        increase
排气        Discharger air        能够        Is capable of        大约        approximately
主要的        major        组件        module        核心        core
附件齿轮箱        Accessory gearbox        维护        maintenance        助推器        booster
轴承支座        Bearing support        入口        inlet        支架        frame
喷嘴        nozzle        防护罩        shroud        转换        transfer
继续        continue        加速        accelerate        引导        direct
结果        result        交付        deliver        用泵抽        pump
截流阀        Shutoff valve        起动手柄        Start lever        警告        waring
头顶上方的        overhead        照亮        illuminate        暗淡的        dim
热交换器        Heat exchange        过滤器        filter        失败        failure
堵塞        blockage        主发动机控制器        Main engine control        离开        leave
转入        Is ported to         机械        mechanism        和…一起        In conjunction with
转/分        Revolution per minute        测量        meter        发射机        transmitter
测量        measure        指示器        indicator        回油        scavenge
旁通活门        Bypass valve                               
二、TEXT
(1)        the power plant on the 737-300/400/500 provides the thrust required for flight and also supplies power to in stopping the airplane (thrust reversers ), provides bleed air for air conditioning, pressurization, anti-icing , and drives a gearbox used for electrical power and hydraulic power. The 737 airplane are powered by two wing-mounted CFM 56-3 high bypass-ratio turbofan engine, the engine buildup is identical for left or right engines.
B737-300/400/500上的动力装置提供飞机飞行所需的推力及飞机停止时的反推力，同时为空调、增压系统及防冰系统提供引气，并驱动一个电源及液压系统使用的齿轮箱。B737飞机的动力来自于安装于机翼上的两台CFM56-3型高函道比的涡扇发动机，左右发动机的结构是相同的。
(2)        The engine is an axial flow turbofan with two rotors and variable stator vanes. The single-stage fan and three –stage low pressure compressor(LPC) are driven, via the low –speed(N1) shaft, by a four-stage low pressure turbine(LPT), the nine stage high pressure compressor(HPC) is driven, via the high speed(N2) shaft, by a single stage high pressure turbine(HPT). The two rotors are mechanically independent of each other. Air entering the engine is divided into a primary(inner) and a secondary (outer) airstream. After the primary airstream has been compressed by the LPC and HPC , combustin of fuel in the annular combustion chamber increases the HPC discharge air velocity to drive the high and low pressure turbines. The engine is capable of producing approximately 18,500 to 23,500 pounds of thrust at sea level static condition.
发动机是一个有两个转子和不同的定子叶片的轴流式涡轮风扇发动机。单级风扇和三级低压压气机被驱动，经由N1低速轴，通过一个四级低压涡轮。九级高压压气机被驱动，经由N2高速轴，通过一个单级高压涡轮。两个转子是彼此独立的机械结构。进入发动机的空气被分成主（内）次（外）两个气流。当主气流被低压压气机和高压压气机压缩后，环形燃烧室内的燃油开始燃烧，增加了高压压气机的排气速度以驱动高、低压涡轮。发动机能够产生在海平面条件下大约18，500到23，500磅的推力。
(3)        The engine consist of 4 major modules; fan, core, low pressure turbine and accessory gearbox. The fan major module consists of 4 maintenance modules, they are fan and booster, No.1 and No.2 bearing support, inlet gearbox. No.3 bearing and fan frame. The core major module consist of 8 maintenance modules, they are high pressure compressor (HPC) rotor, HPC front stator, HPC rear stator, combustion outer case, combustion chamber, high pressure turbine (HPT) nozzle, HPT rotor, HPT shroud and 1st – stage LPT nozzle. The low pressure turbine module consisis of 3 maintenance modules, they are low pressure turbine, low pressure turbine shaft and turbine frame. The accessory drive module consists of 2 maintenance modules, they are the transfer gear box and the accessory gearbox.
发动机包含四个组要组件：风扇、主体、低压涡轮及附件齿轮箱。风扇又包含四个主要的维护部件，它们是：风扇和助推器、1#、2#轴承支架，入口齿轮箱、3#轴承及风扇骨架。发动机主体主要组件包括8个维护组件，它们是高压压气机转子、高压压气机前定子、高压压气机后端定子、燃烧室外壳、燃烧室、高压涡轮喷嘴、高压涡轮转子、高压涡轮保护罩及第一级高压涡轮喷嘴。低压涡轮组件包括3个维护组件，它们是低压涡轮、低压涡轮轴及涡轮支架。附件驱动组件包括2个维护组件，它们是传动齿轮箱和附件齿轮箱。
(4)        The fan and booster provide two separate air stream, the primary airflow passes through the inner portion of the fan rotor, then continues through the booster, the core engine and the LPT, exiting through the core exhaust nozzle. The secondary airflow passes through the fan outer portion and exits through the fan discharge duct(fan air ). The fan is located on the front of the engine, the main function of the fan is to accelerate the air directed to the engine secondary airflow nozzle. This results in producing approximately 78% of the total engine thrust.
风扇及助推器提供两个隔离的气流，主气流通过风扇转子内部，接着穿过助推器、发动机主体及低压压气机，从排放喷嘴核心排出。次级气流通过风扇外部从风扇排气管道喷出。风扇安装于发动机前端，其主要功能是给气流加速引导气流到发动机次级气流喷嘴。这样产生的动力占发动机总推力的78%。
(5)        Fuel is delivered to the fuel nozzles at pressure and flow-rate required to obtain the desired engine thrust. Fuel is pumped from the fuel tank and enters through the engine fuel shutoff valve. The engine fuel shutoff valve is controlled by the engine start lever and the engine fire warning switch. When the engine fuel shutoff valve is closed ,the FUEL VALVE CLOSED light located on the forward overhead panel illuminates dim.
燃油根据发动机推力的需求在压力作用下流到燃油喷嘴。燃油在油箱中用泵抽出并流过燃油关断活门。发动机燃油关断活门由发动机起动手柄和发动机火警开关控制。当发动机燃油关断活门关闭时，位于前顶置面板上的“FUEL VALVE CLOSED”灯燃亮。
(6)        Fuel passes from the first stage of the engine driven fuel pump through a fuel/oil heat exchanger to a filter. Provisions are made to bypass the filter in the event of failure or blockage. The second stage of the fuel pump provides high pressure fuel to the main engine control(MEC). As the fuel leaves the second stage fuel pump, it passes through another filter where a portion of the fuel is ported to a servo fuel heater before entering the MEC. The servo fuel heater uses engine oil to heat the servo fuel to prevent icing of control mechanisms control(PMC) uses power lever angle, fan inlet pressure and temperature, N1 rpm and N2 rpm to meter the correct amount of fuel to the combustor. A fuel-flow transmitter measures the rate of fuel flow from the MEC and provide a signal to the fuel flow indicator.
燃油从第一级发动机驱动燃油泵中通过燃油/滑油热交换器到一个油滤。当油滤万一失效或堵塞时将被旁通。燃油泵的第二级提供高压燃油给主发动机控制器。当燃油离开燃油泵第二级,流到另一个油滤，在那里，一部份燃油在进入主发动机控制器前前转到一个伺服燃油加热器。这个伺服燃油加热器用发动机滑油加热伺服燃油以防止控制机械内部主发动机控制器结冰。主发动机控制器与电源管理控制器相连，用动力杆角度、风扇入口压力及温度、N1转速和N2转速来测量燃烧室燃油量。燃油流量传感器从主发动机控制器测量燃油流率并为燃油流量指示器提供信号。
(7)        The oil system is pressurized by the engine driven oil pump. The oil leaves the oil pump, where sensors for oil pressure and the LOW OIL PRESSURE switch are located, passes through an oil filter and continues to the engine bearing and gearbox, the oil is returned to the oil tank by means of engine driven scavenge pump. From the scavenge pumps the oil passes through a scavenge filter. Bypass valve is mounted to prevent filter from blocking. scavenge oil temperature is sensed as the oil returns to the scavenge pump. The oil then passes through the servo fuel heater and fuel/oil heat exchanger where it is cooled by fuel before returning to the oil tank.
滑油系统通过发动机驱动的滑油泵增压。滑油离开装有滑油压力传感器及“LOW OIL PRESSURE”开关的滑油泵，流向一个滑油油滤并流到发动机轴承及齿轮箱。滑油通过发动机驱动的回油泵回到滑油箱。从回油泵返回的滑油流经一个油滤，旁通活门用来防止油滤堵塞。当滑油回到回油泵时，通过一个传感器来感受回油滑油温度，然后，滑油通过伺服燃油加热器及燃油/滑油热交换器，在这，滑油在回到滑油箱之前被燃油冷却。
LESSON 17 PPOWER PLANT （2）
一、单词
起动        Start        点火        Ignition        扭矩        Torque
转动        Rotate        加速        Accelerate        慢车        Idle
起动器        Starter        一套电路        Circuitry        高压压气机        High pressure compressor
外壳        Case        位置        Position        完成        Accomplish
级        Stage        空气涡流发动机        Turbine-air motor        把…转换        Convert into
能量        Energy        足够的        Sufficient        地面源        Ground source
交叉引气        Crossbleed        另一个        Another        与…有关        Related to
火花        Spark        混合物        Mixture        起飞        Take off
着落        Landing        有害的        Adverse        天气        Weather
情况        Condition        要求        Require        点火        Ignite
励磁器        Exciter        三维的        triaxial        屏蔽        Shield
引线        lead        入口整流罩        Inlet cowl        预冷器        Percooler
限制        Limit        温度        Temperature        总管道        manifold
相反        revers        方向        Director        套筒        sleeve
遥控器        Remote        展开        Deploy        在…之前        Prior to
展开        Deployment        阻流门        Blocker door        排列        Arrange
连接在…上        Is attached to         螺栓        Bolt        阻力连杆        Drag link
装置        Fitting        移动        Translate        强迫        Forcing
级联的        Cascade        部分、段        Segment        形成        Form
参数        Parameter        仪表        Instrument        发光二极管        Light emitting diode
百分比        Percent        排气温度        Exhaust gas temperature        超出        Exceed
红线        Redline        重量        Weight        总的        Total
消耗        Consume        顺序        Sequence         复位        Reset
振动        Vibration        最大的        maximum               
二、TEXT
(1)        the engine starting system provides air, fuel, ignition and torque for rotating the engine to an rpm at which the engine can accelerate to idle rpm. The system consists of the starters, start valves, start bleed valves, pneumatic ducting, control and power circuitry, start levers and start selector switches. The start valve and starter are located on the forward side of the engine accessory gearbox, the start bleed valve is located on the left side of the HPC case at the 11 o’clock position, the start levers, start selector switches and start valve open light are in the flight compartment. Engine starting is accomplished by supplying air from the pneumatic system through the start valve to the starter.
发动机起动系统提供引气、燃油、点火及扭矩，以使发动机转动并加速到慢车所需的转速。系统包括起动器、起动活门、起动引起活门、增压管道、控制及电源线路，起动手柄及起动选择开关。起动活门及起动器安装于发动机附件齿轮箱，起动引气活门安装于高压压气机左侧11点钟位置，起动手柄、起动选择开关及起动活门打开指示灯位于驾驶舱。发动机起动过程通过发动机增压系统提供空气经过起动活门给起动器来完成。
(2)        The engine starter is a single-stage, axial flow, turbine-air motor, the starter converts compressed air pressure into rotational mechanical energy sufficient to accelerate the engine to starting speed. Pressurized air and electrical power are required for starter operation. The engine may be started with air from the APU(we will introduce APU in the next lesson), from a ground source, or by using engine crossbleed. Another important system related to engine operation is the ignition system. The purpose of the ignition system is to produce a high current electrical spark to ignite the fuel /air mixture in the engine combustion chamber during starting and to provide continuons ignition during takeoff, landing and operation in adverse weather conditions. The ignition system consists of the ignition power supply, engine ignition control, 2 ignition exciters, 2 spark igniters and 2 triaxial shielded ignition leads.
发动机起动器是一个单级、轴流式空气涡轮发动机，起动器将压缩空气的压力转换为足够的转动机械能以加速发动机的转速。起动操作时需要增压空气及电源。发动机可以用APU来的引气、地面气源或发动机交输引气起动（我们将在下一课介绍APU）。另一个与发动机起动有关的重要系统是点火系统。点火系统的作用是在起动过程中产生高压电火花点燃发动机燃烧室中的燃油/空气的混合气，并在起飞、降落阶段及恶劣天气下提供持续的点火。点火系统包括点火电源、发动机点火控制、2个点火励磁器、2个火花点火器及2个三相点火屏蔽线。
(3)        Bleed air is extracted from the high pressure compressor for the following system:
        Air-conditioning
        Cabin pressurizatin
Wing and engine inlet cowl anti-icing
Hydraulic tank pressurization
Potable water tank pressurization
Fan air is used as cooling air for the precooler to limit the temperature of the bleed air in the pneumatic manifold. Fan air is also used for cooling the generator and thrust reverser.
   引气从高压压气机中释放给列镣系统：
   空调系统
   客舱增压系统
   机翼及发动机入口整流罩防冰
   液压油箱增压
   饮用水箱增压
风扇空气做为预冷器中的冷却空气用以限制增压总管中的引气温度。风扇空气也可用于冷却发电机和反推装置。
(4)        The thrust reverser system reversers the direction of the fan exhaust during landing and provides additional brakeing of the airplane. The reverser sleeve is part of the engine cowling . the actuating system is on the reverser. The control and indicatin system are located remote from the engine. The reverser can only be deployed on the ground with hydraulic pressure available. Prior to deployment the engine thrust lever must be at idle position.
In figure17-1,10blocker doors are arranged around the forward section of the thrust reverser sleeve. The forward section of the blocker door is attached to the sleeve with two bolts, the blocker door drag link attaches the blocker door to the inner duct. The ddrag link attaches to the blocker door with a link attachment fittin and to the inner duct with a bolt. As the sleeve translate aft, the blocker doors rotate into a blocking position, due to sleeve movement and the door’s attachment to the inner duct. When extended, the blocker doors block the fan exhaust, forcing air in the reverse direction through the cascade segments. When retracted, the doors form part of the outer duct for fan exhaust air.
   反推装置系统将降落阶段风扇排放的气流反向并辅助飞机刹车。反推器的外壳是发动机整流罩的要部分。作动系统在反推器上。控制及指示系统从发动机遥控。反推器只能够在地面液压系统有效时打开。在打开之前，发动机反推装置必须是在慢车位。
在图17-1里，10个阻流门围绕着反推装置外壳前部排列。阻流门前段用两个螺栓与外壳相连，阻流门阻力连杆将阻流门连接在内部管道上。阻力连杆用一个连接装置连接到阻流门并用一个螺栓连接到内部管道上。当外壳移动后部，阻流门转到阻流位，由于外壳转动，并且门连接在内部管道。当扩展时，阻流门阻止风扇排气，迫使空气反向通过级联段。当收回时，阻流门将作为风扇向外排气的外部管道的一部份。
(5)        The engine and hydraulic parameters are displayed on two engine instrument panel(ELS)using light emitting diodes(LED).
Engine displays and controls on the center panel consist of the following :
·N1 displays—— indicate fan speed in percent rpm.
·N2 displays —indicate high pressure compressor speed in percent rpm .
·Exhaust gas temperature(EGT)displays
1.        indicate temperature of exhaust gas in °C.
2.        a red light above each N1,N2,and EGT display illuminates if that engine exceed its redline.
·Fuel flow displays
Indicate fuel flow in weight of fuel per hour and also total fuel consumed per engine.
The FUEL FLOW/FUEL USED switch is used to change display from FUEL FLOW to FUEL USED, after 10 seconds the FUEL USED display reverts to FUEL FLOW.
·The FUEL USED RESET display a sequence:fuel used since last trset or
power— up, then 000, and finally fuel flow.
·Engine oil pressure displays —display engine oil pressure in psi.
·Engine oil temperature displays— display engine oil temperature in°C.
·Engine oil quantity displays —display oil quantity of engine in percent of full.
·Engine vibration displays —display engine maximum vibration.
·Hydraulic pressure displays —display hydraulic systems pressure in psi.
·Hydraulic quantity displays —display hydraulic system quantity in % of full.
发动机及液压参数用发光二极管显示在两个发动机指示面板上。
发动机在中央面板上显示及控制包括以下内容：
·N1显示—用转速百分比指示风扇转速
·N2显示—用转速百分比指示高压压气机转速。
·排气温度指示
1.        用°C指示排气温度。
2.        如果发动机超出红线，N1，N2上方的红灯及发动机排气温度指示灯亮。
·燃油流量指示
用每台发动机每小时总的消耗重量指示燃油量。
FUEL FLOW/FUEL USED开关用于改变FUEL FLOW/FUEL USED的显示模式，10秒后FUEL USED显示恢复到FUEL FLOW。
·FUEL USED RESET—显示一个顺序：上次重置后上电后的燃油使用，然后是000，最终燃油流量。
·发动机滑油压力指示—用PSI指示发动机滑油压力。
·发动机滑油温度指示—用°C指示发动机滑油温度。
·发动机滑油量指示—用百分比显示发动机滑油量。
·发动机振动值指示—显示发动机最大振动值。
·液压指示—用PSI显示液压系统压力。
·液压油量显示—用百分比显示液压油量。
LESSON 18  AUSILLARY POWER UNIT (1)
一、单词
电的        Electrical        完全地        Completely        封入        Enclose
钛        Titanium        入口        Inlet        入口        Entrance
分开        Split        通路        Path        孔、洞        Hole
喷射管        Jet pipe        组件        Pack        容易地        Readily
容易接近地        Accessible        检查        Inspection        拆卸        removal
简单的        Simple        吊车        Hoist        电缆        Cable
离心的        Centrifugal        径向的        radial        流入、内流        Inflow
电磁线圈        Solenoid        放置        Place        超控        Override
调节        Regulate        最初的        initial        污染        contamination
施加        apply        测量        Meter        接近        Near
恒定的        Constant        速度        Speed        安全的        Safe
插头        Plug        电路        Circuit        点火激励器        Ignition exciter
密封的        hermetically        密封        Seal        金属        Metal
安装        Install        连接        interface        程序化的        Sequencing
通电        Energize        保证        Ensure        起燃        Initiate
最低        Minimum        润滑        lubricate        形成        Build up
表压        Psig        释放        De-energize        保持…状态        Remain
引导        Conduct        噪音        Noise        消音器        Muffler
因而        Thus        园柱体        Cylindrical        绝缘纸        Felt
衬垫        Liner        集油盘        Drip pan        间隔        Gap
二、TEXT
(1)        the auxiliary power unit (APU) is used for providing:
1)        compressed air for engine starting.
2)        Compressed air to the air conditining system on the ground or in flight.
3)        Electrical power to the airplane electrical system on the ground or in -flight ,(we will discuss APU electrical power in the next lesson).
辅助动力装置APU被用于提供以下：
1) 为发动机起动提供压缩空气
2) 在地面或飞行中为空调系统提供压缩空气
3) 在地面或飞行中为飞机电源系统提供电源
(2)        The APU engine is located in the aft end of the fuselage, behind the pressure bulkhead and below the horizontal stabilizer. The APU engine is completely enclosed in a titanium shroud. The air inlet door is located on the right side of the aft fuselage for air entrance. The airflow is split into two paths, one for the engine and the second for the accessories cooling. The cooling air exhaust overboard through a hole in lower shroud. The exhaust ducting is cooled by four air inlets around the jet pipe. Fuel is supplied through a shrouded line from fuel tank. Bleed air from the APU is supplied to the pneumatic system through a bleed valve, the bleed air can be used to perate either of the two air —conditioning packs or for main engine starting. The APU is readily accessible for inspection, maintenance or removal through a large door in the fuselage directly below it . removal is accomplished by lowering the assembly with a simple hoist and cable system.
The APU is a singe shaft gas turbine engine with a two stage centrifugal compressor, a single combustion chamber and one radial inflow turbine. The accessories group, driven by the gear box , is at the front of the unit.
APU发动机安装于机身尾部、压力隔板后面及水平安定面下方。APU发动机被完全地封进一个钛防护罩中。空气进口安装于机身后部右侧。进入APU的空气被分成两个通路，一个供给发动机，另一个供给容易接近的冷却器。冷却空气通过保护罩下方的一个孔排放出去。排气管道被四个围绕喷射管道的进口空气冷却。燃油从燃油箱通过一个带保护的管道提供。从APU出来的引气通过一个引气阀门被提供到增压系统，引气可以被用来控制两个空调组件中的任一个，也可用于发动机起动。APU通过它正下方机身的一个大的口盖很容易接近，并通过它进行检查、维护或拆装工作。通过组件下方用一个简单的吊架和线缆系统完成拆卸。
APU是一个单轴气动涡轮发动机，它有一个两级离心压气机，一个单燃烧室和一个径向内流式涡轮。由齿轮箱驱动的附件组位于组件前面。
(3)        The APU fuel system consist of a fuel valve, control unit, solenoid valve, f ilter, heater and control valve. The fuel valve allows fuel supply from the tank to the APU engine. This valve operation is controlled by the APU switch on P5 panel, is it opened by placing the APU switch to the ON postion and closed by the switch placed to the OFF position. The valve can be operated manually without power by the override handle. The control unit regulates the fuel flow to the combustion chamber, during starting and normal operation. The solenoid valve allows fuel flow to the combustion chamber after the initial rotation of the APU. The two fuel filters are used to prevent contamination of the pump and fuel control unit. The fuel heater is used to prevent ice from blocking the fuel filter.
APU燃油系统包括一个燃油活门、控制组件、电磁活门油滤、加热器及控制活门。燃油活门允许燃油从燃油箱提供给APU发动机。此活门是通过P5板上的APU开关操作的，当APU开关置于ON位时打开，置于OFF位时关闭。此开关在没有电源情况下可通过超控手柄进行人工操作。控制组件用来在起动及正常操作期间调节流进燃烧室的燃油量。电磁开关允许燃油当APU初始转动后流向燃烧室。两个油滤用来防止污染泵及燃油控制组件。燃油加热器用来防止燃油结冰堵塞燃油油滤。
(4)        The fuel from the tank is delivered to the fuel control unit through the fuel valve. The fuel control unit supplies and regulates the fuel to the combustion chamber. The regulated fuel flow controls the acceleration of the APU engine during the starting operation. When a load is applied to the APU, the fuel control unit meters the fuel flow to maintain a near constant speed and a safe operating temperature of the unit.
燃油箱中的燃油通过燃油活门被送到燃油控制组件。燃油控制组件对进入燃烧室的燃油进行调节。调节燃油量可对APU发动机起动时的加速进行控制。当一个负载被加到APU上时，燃油控制组件测量燃油量以保持一个相近的恒定速度及组件的安全温度。
(5)        The APU ignition and starting system provides the means of rotating the APU engine to starting speed and for igniting the fuel-air mixture in the combustion chamber. This system consists of a start switch, starter, start relay, ignition exciter, igniter plug, and control circuit. The starter provides initial power for rotatin the APU engine compressor, tubine, and engine –driven accessories to a speed high enough to obtain good airflow for combustion. The ignition exciter provides the high voltage required to produce the spark at the ignitor plug, the ignition exciter electrical components are enclosed in a hermetically sealed metal container. The igniter plug is installed on the forward side of the combustion chamber, it is used to provide the high energy spark for igniting the fuel/air mixture.
APU点火及起动系统提供APU发动机起动速度时的转动及点燃燃烧室中的油气混合物。这系统包括一个起动开关、起动器、起动继电器、点火励磁器、点火器插头及控制电路。起动器为APU发动机压气机、涡轮及发动机驱动附件到足够高的速度以得到燃烧所需的气流转动提供初始动力。点火励磁器为在点火器插头上产生火花提供高压电能，点火励磁器电子组件被封入一个密封地金属容器内。点火插头被安装在燃烧室的前面，被用来提供点燃油气混合物的高能花火。
(6)        The start system interfaces with the sequencing oil pressure switch, speed switch, APU control unit and APU switch. During APU start, the starter is energized and APU rotates. The ignition exciter is energized by the action of the sequencing oil pressure switch(this switch ensures that combustion cannot be initiated during an APU start until a minimum lubricating oil pressure has been buildup during APU start, with increasing oil pressure, this switch closes at 4 psig oil pressure and provides 28 volt dc power to the fuel solenoid valve and the ignition exciter). The starter and ignition circuits are de-energized by the action of the speed switch during APU engine acceleration. During normal engine operation, the exciter remains de-energized.
起动系统连接着程序化的滑油压力开关、速度开关、APU控制组件及APU开关。APU起动期间，起动器被接通，APU转动。点火励磁器通过程序化的滑油压力开关（此开关确保在APU起动到建立最小的滑油润滑压力期间不会燃烧。在APU起动期间，随着滑油压力增加，当滑油压力达到4PSIG时，开关关闭，并且提供28伏直流电给燃油电磁活门及点火励磁器）动作被接通。起动器及点火线圈在APU发动机加速期间通过速度开关被释放。在发动机正常操作期间，励磁器保持断开。
(7)        The APU exhaust conducts the engine exhaust gas overboard and reduces the noise level of the high velocity gas flow. The exhaust duct consists of a heat shield and a muffler. The muffler is inside the heat shield. A felt metal liner is installed on the inside surface of the muffler for noise reduction. At the forward end ,the heat shield has a drip pan and is supported by the engine shroud. There si a gap between the muffler and the APU engine exhaust. At the aft end ,the exhaust duct is supported by the aft fairing .
APU排放口引导发动机排出气体到外面并降低高速气流的噪音。排放管道包括一个加热保护罩和一个消音器。消音器安装于加热保护罩内部。一个绝缘金属垫片消音器内表面上，用来降低噪音。在加热器前端有一个集油盘并被发动机保护罩支持。在消音器与APU发动机排气口之间有一个间隙。排气管道后端由后整流罩支撑。
LESSON 19 AUXILIARY POWER UNIT （2）
一、单词
首先        Primarily        供给        Furnish        接线端        teminal
中线        Neutral        导线        Lead        在…外面        Outside
放电器        Discharger        开缝的        slotted        频率        Frequency
得到        Achieve        跳开关        Breaker        闭合        Closing
松开        Tripping        永久磁铁        Permanent magnet        帮助        Assist
锁定        Latch        弹簧        Spring        保持        hold
触点        Contact        接触器        Contactor        信号        Signal
获得        Gain        应用        Application        允许        Allow
短暂的        Momentary        通电        Energize        线圈        Coil
极性        polarity        插座        Receptacle        汇流条防护        Bus protection panel
充电器        Charger        主要的        Essential        缺席        Absence
柱螺栓        stud                               
二、TEXT
(1)        the APU driven generator is mounted on the foreard face of the APU accessory drive gearbox. The APU generator produces the AC power required by the airplane systems primarily for ground operation, the generator can also be used as a backup generator in flight. APU is used to furnish 60 KVA of electrical power on the ground and used as AC power source of 50 KVA in flight.
APU驱动的发电机安装在APU附件齿轮箱前表面上。APU发电机可产生飞机在地面操作时系统所需基本交流电，此发电机同时也可做为飞行中的备用电源。APU被用来在地面提供60千伏安的电源及飞行中提供50千伏安的交流电源。
(2)        The APU ac generator has 6 ac terminals:
T1,T2,and T3 are the power terminals, T4,T5 and T6 are the neutral or ground terminals.
T1 and T4 are for phase A, the leads are color-coded red.
T2 and T5 are for phase C, the leads are color-coded blue.
T3 and T6 are for phase B, the leads are color-coded yellow.
These terminal numbering and color-coding is the same as for the engine –driven generators. Cooling air enters through a duct from outside the APU compartment, passes through the generator and discharges into the APU. The generator is attached to the APU accessory drive gearbox with 12 slotted holes over mounting studs. The neutral current transformer sense the total current flowing through the APU generator at the neutral terminal.
   APU发电机有六个交流接线端：
   T1，T2和T3是电源接线端，T4，T5和T6是中线或地面接线端。
   T1和T4为A相，导线颜色为红色。
   T2和T5为C相，导线颜色为蓝色。
T3和T6为B相，导线颜色为黄色。
这些接线端号码及颜色代码与发动机驱动的发电机是相同的。冷却空气通过一个APU外面的管道进来，通过发电机和排气装置进入APU。发电机被放在APU附件驱动齿轮箱上，用12个双头螺栓固定。中线电流转换感受流过APU发电机中线接线端的总的电流。
(3)        The ac power produced by APU generator is of constant frequency. To achieve this, the APU generator drive( including a gearbox) can be used for reducing the high speed of the APU engine to a lower speed. The APU engine drive the generator in lower speed to produce ac power at constant frequency.
APU发电机产生的交流电源是恒频的。为得到恒频电源，APU驱动发电机可将APU发动机高速度降成低速使用。APU发动机以低速驱动发电机，从而产生恒频的交流电。
(4)        The two APU generator breakers( see figure 19-2) connect 115 volt ac, 400 hertz, 3-phase power to the distribution system from the APU generator. The APU generator breakers are located in the bottom of the P6 panel in the flight compartment. The breaker has a dc coil for closing and tripping. A permanent magnet assists closing and latches the breaker in the closed position. An internal spring assists opening and holds it in the open position. The breaker has 6 main 115 volt ac contacts and 20 auxiliary contacts. The auxiliary contacts are used to control the positions of APU generator breakers and external power contactors, and for indicating lights in the flights in the flight compartment. The closing and tripping signals for the breakers are from the P5-4 panel. The breaker conacts position is indicated by the blue APU GEN OFF BUS light on the P5-4 panel. Access to the breaker is gained by opening circuit breaker panerls p6-11 and P6-12 at the bottom of P6 panel.
两中APU发电机跳开关将115伏，400HZ的三相交流电连接到APU发电机的分配系统。APU发电机跳开关安装在驾驶舱P6面板的低部。跳开关有一个打开/闭合用的直流线圈。一个永久磁铁帮助跳开关闭合并锁定在闭合位。一个内部弹簧帮助跳开关打开并保持在松开位。这个跳开关有6个主115伏交流触点和20个辅助触点。这些辅助触点用来控制APU发电机跳开关位置及外部电源接触器，及驾驶舱内的灯光指示。跳开关的闭合或松开信号指示来自P5-4面板。跳开关触点位置由P5-4面板上的蓝色“APU GEN OFF BUS”灯指示。跳开关可通过打开P6面板低部的P6-11及P6-12电路跳开关后接近。
(5)        Application of 28 volt dc to close, allows momentary energizing of the coil . when the breaker closes, the coil deenergizes through the auxiliary contact and the breaker is held closed by the permanent magnet. Application of 28 volt dc to trip. Reverses the polarity of the coil and the contactor opens assisted by the spring. The coil deenergizes through the auxiliary contact.
28伏直流电关闭的应用，允许线圈瞬时接通。当跳开关闭合时，线圈通过辅助触点断电，跳开关通过永久磁铁被保持在闭合位。28伏直流电松开的应用，将线圈极性反向，触点在弹簧的帮助下打开。线圈通过辅助触点断电。
(6)        The 115 volt ac, 400HZ, 3-pahse power from an external source (ground power unit ) can also be supplied to the airplane for systems use. The external ac power system consists of an external power receptacle, bus protection panel, two external power contactors, relays, switches and indicating lights. The ac external power receptacle is located on the right side of the airplane, forward of the nose wheel well, the bus protection panel (BPP) is used for control and protection of the airplane circuits connected to external power. The two external power contactors connect 115 volt ac, 400Hertz, 3-phase power to the distribution system from external power source.
从外部电源的（地面电源）400HZ，115伏三相交流电也能够提供到飞机上供系统使用。外部交流电源系统包括一个外部电源插座，汇流条防换板，两个外部电源接触器、继电器、开关及指示灯。外部交流电源插座位于飞机右侧、前轮舱前方。汇流条防护板用来保护与外部电源连接的飞机线路。两个接触器将外部来的115伏，400HZ的三相交流电源接到分配系统。
(7)        The 115 volt ac system is supplied by two engine driven generators, APU driven generator or external power. The powr is connected to the generator main busses by engine generator breakers. APU breakers and external power contactors. Power is also supplied to two transfer busses through transfer relays. External power can be supplied to the external ac bus and the ground service bus (this bus is used for servicing of the airplane). The ground service bus can also be supplied from generator bus NO.1.
115伏交流电源由两台发动机驱动的发电机、APU发电机或地面电源提供。它被发动机跳开关、APU跳开关或地面电源触点连接到发电机主汇流条上，它也可以通过转换继电器接到两个转换汇流条上。外部电源也能够供到外部交流汇流条及地面服务汇流条上。地面服务汇流条也能够从一号发电机汇流条供电。
(8)        The 28 volt ac system is obtained through transrformers from main, transfer ,and ground service busses. The 28 volt dc power is supplied from the battery and transformer rectifiers to the battery bus and two dc busses. The power is connected to the busses by relays. The battery charger is supplied with power from the 115 volt ac system. The electronic system power is supplied from the 115 volt ac and 28 volt dc system. The standby ac and dc busses are powered normally from the generated ac and dc power. Alternately, the battery supplies power to the standby system. The standby power components are located in the electronics compartment, P6 panel and p5 panel .the purpose of the standby power distribution is to provide 115 volt ac and 28 volt dc power to essential system during absence of normal supply.
通过转换主汇流条、转换汇流条或地面服务汇流条上的电源可得到28伏交流电。28伏直流电由电瓶及转换整流器到电瓶汇流条和两个直流汇流条。28伏直流电被继电器接到这个汇流条上。电瓶充电器由115伏交流电供电。电源系统由115伏交流和28伏直流电提供。备用交流和直流电由正常交流和直流电提供。另一方面，电瓶为备用系统提供电源。备用电源组件位于电子舱、P5及P6面板。备用电源分配的目的是在无法正常供电的期间为必要系统提供115伏交流电或28伏直流电。
LESSON 20 NAVIGATION 导航
一、单词
导航        Navigation        计算        Compute        运动        Movement
包含        Include        子系统        Subsystem        自动定向仪        Automatic director finder
相对方位        Relative bearing         甚高频全向信标        Very high frequency omnirange        仪表着陆系统        Instrument landing system
磁方位角        Magnetic bearing         偏离                航线        Course
转动        Turn        最佳的        Optimum        测距仪        Distance measure equipment
斜距        Slant range        空中交通管制        Air traffic control        识别        Identification
高度        Altitude        大气数据系统        Air data system        全压        Pitot pressure
静压        Static pressure        不同的        Various         惯性基准系统        Inertial reference system
关键的        Key        航向        Hearing         姿态        Attitude
当前位置        Present position        电子飞行仪表系统        Electronic flight instrument system        气象雷达        Weather radar
地图        Map        低空无线电高度表        Low range radio altimeter        绝对的        Absolute
高度        Height         近地警告系统        Ground proximity warning system        听觉        Aural
视觉的        Visual        不安全的        Unsafe        飞行管理计算机系统        Flight management computer system
领航        Navigate        最佳的        Optimization        指点标        Maker beacon
特殊的        Specific         以前        previously        起源        Origin
终点        destination        到来        advent        随着…出现        With the advent of
直接        Direct        大圆弧        Great circle        强烈期望的        Highly desirable
有可能的        potential        可能的        Possible        误差        Error
核实        verify        计算        Computation        冗长        Lengthy
耗费        Comsume        适合于        Suit         机载的        Onboard
附近的        Nearby        远距离的        Distant        复杂的        Complex
最佳的        Optimize        爬高        Climb        剖面        profile
预测        predict        更进一步        further        计划        Projection
分段爬升        Step climb        巡航        Cruise        以及        As well as
下降        Descent        贯穿        Throughout        把…做为目标        Target
利用        Utilization        综合飞行系统附件装置        Integrated flight system accessory unit        航线可更换件        Line replaceable unit
印刷电路板        Print circuit card        试验        Test        抑制        suppression
数模适配器        Data analog adapter        故障        Failure        存储器        Memory
状态        Status        航空无线电公司        Aeronautical radio incorporated        数据总线        Data bus
无线电距离磁指示器        Radio distance magnetic indicator        自检测设备        Build –in text equipment        离散的        discrete
完成        perform        任务        Task        燃油累加装置        Fuel summation unit
飞行控制计算机        Flight control computer                               
二、        TEXT
(1)        the navigation system compute and display the airplane’s position and movement over the earth’s surface. The navigation systems include the following main subsystems:
l        ADF automatic direction finder — ADF system provide a display of the relative bearing to a selected ground transmitter.
l        VOR/ILS(very high frequency omnirange/instrument landing system)— this system provide displays of relative and magnetic bearing to a selected VOR station and deviation from a preselected course. When truned to an ILS frequency, the system provides a display of the lateral and vertical deviation from the optimum landing path.
l        DOM(distance measuring equipment)  —DME system measures the slant range distance to the selected DME facility.
l        ATC (air traffic control)— ATC system transmits airplane identification and altitude data to a ground facility.
l        ADS (air data system)— ADS system measures pitot and static pressure and total air temperature and computes various air data parameters.
l        IRS(inertial reference system)— this system provides outputs of key navigation parameters such as heading, attitude, and airplane present position.
l        EFIS(electronic flight instrument system )— this system providesdisplays of information from various airplane systems.
l        WXR(weather radar) —this system provides a display of the weather conditions forward of the airplane, and can also provide a map display.
l        LRRA(low range radio altimeter)— this system measures the absolute height of the airplane above the earth’s surface.
l        GPWS(ground proximity warning system)— this system uses inputs from other systems to navigatee the airplane and provide optimization of the flight plan.
l        FMCS(flight management computer system)— this system provides the pitot with aural and visual warning of an unsafe flight path relative to the earth’s surface.
l        MKR BCN(marker beacon ) —this system provides an indication when the airpnale is passing over a specific position.
l        TCAS(traffic alert and collision avoidance system)— this system provides the pitots with warnings and advisories of unsafe flight conditions with regard to other airplanes operating in the area.
l        导航系统计算并显示飞机的位置及其在地球表面的移动。导航系统包括下列子系统：
l        自动定向机——此系统提供一个相对一个选定的地面发射台的相对方位角显示。
l        甚高频全向信标/仪表着陆系统——此系统提供飞机相对于一个选定的VOR台的磁方位及飞机与预选航道的偏离显示信号。当转动仪表着陆系统的频率时，此系统显示飞机与最佳着陆路径在水平及垂直方向上的偏差。
l        测距机—— 此系统用来测量飞机与选定的DME设备的斜距。
l        空中交通管制—— 此系统发射飞机识别码及高度信号给地面设备。
l        大气数据系统—— 此系统测量皮托管压力、静压及空气总温并计算出不同的大气数据参数。
l        惯性基准系统—— 此系统输出例如像航向、高度及飞机当前位置等关键导航参数。
l        电子飞行仪表系统—— 此系统提供飞机各系统不同系统的显示。
l        气象雷达—— 此系统提供飞机前方气象状况的显示，并能进行地图显示。
l        低空无线电高度表—— 此系统测量飞机与地球表面的绝对高度。
l        近地警告系统—— 此系统通过其它系统的输入引导飞机并提供最佳参数选定的飞行计划。
l        飞行管理计算机系统—— 此系统用音响或视觉警告给飞行员相对于地球表面不安全的飞行路径。
l        指点信标—— 此系统提供当飞机飞经一个特定的位置时进行指示。
l        警告及防撞系统—— 此系统为飞行员提供在此区域内相对于其它飞机处在不安全的情况下提供警告及建议。
(2)        Previously, airplanes were navigated by flying from station to station along the route from the airplane’s origin to destination. The pitot used distance measuring equipment(DME), VHF omnirange (VOR)and automatic direction finder(ADF) to fly to each station. With the advent of inertial navigation system(INS), it became possible to fly a more direct route from origin to destinatin. A direct, great circle route is highly desirable because of potential fuel and time savings. Because of possible position errors in inertial systems the pitot is required to verify the inertial position with the DOME, VOR and ADF system. The computations required to verify the inertial position are lengthy and time consuming and are much more suited to an onboard computer. Also, since the airplane is not on a course to a nearby station but on a direct course to a distant destination, the computations are move complex.
   
(3)        The flight management computer system (FMCS) continuously calculates the optimum flight path and engine thrust to save time and fuel. During takeoff, the FMCS provides optimized thrust setting for takeoff based on gross weight of the airplane and outside temperature. During climb, the FMCS provides optimized climb profiles by predicting both opimum altitude and cruise speeds.further, the FMCS provides projections of top of climb and step climbs. During cruise, the FMCS optimizes descents by predicting top of descent speeds are targeted to make maximum utilization of the potential energy of the airplane.
飞行管理计算机系统继续计算最佳的飞行路径及发动机推力，以节省时间和燃油。在起飞期间，飞行管理计算机系统依据飞机总重及外界温度为飞机起飞提供最佳的推力设置。在爬升阶段，飞行管理计算机系统通过预测最佳姿态及巡航速度来提供最佳的爬升剖面。更进一步的，飞行管理计算机系统提供爬升到顶的计划及分段爬升。在巡航阶段，飞行管理计算机系统在导航数据的基础上通过预测下降顶端来优化下降。在整个下降阶段，下降速度是
(4)        There are two important equipment used in navigation system, one is the integrated flight systems accessory unit (IFSAU), the other is the digital to analog adapter(DAA). This IFSAU is line replaceable unit (LRU) located in the electronic equipment compartment. Is contains two printed circuit card(A1,A2). Each of the cards is connected to a different rear connector on the LRU. The A1 card is the IFSAU autopilot card, it has circuits that operate independently to monitor, engage, and set autopilot and navigation modes. The A2 card is the IFSAU flight instrument card, it has circuits that operate independently to monitor, set, and test flight instrument system. It also contains suppression diodes and load resistors for externally connected circuits.
(5)        Tow digital to analog adapters(DAA) are installed in the 737 airplane. The DAA is part of inertial reference system(IRS). It stores inflight failures of the IRS in memory and monitors the IRS for current status. THE DAA converts the ARINC 429 data bus output from the IRS into an analog format and sends that data to the radio distance magnetic indicator9RDMI). The DAA converts an IRS BITE request discrete from the flight management computer system into an analog signal and sends it to the IRS.
(6)        The DAA perform other tasks not related with the IRS. They convert VOR/ILS navigation system signals from analog format into ARINC 429 format and sent the data to the electronic flight instrument system (EFIS) for display to the flight crew. The DAA convert analog information from the fuel summation unit into data information and send the information on an ARINC 429 data bus to the FMCS. The DAA also converts the low speed N1 from ARINC 429 format into analog format and sends the N1 information to the engine indicator. The DAA alos converts DME distance from ARINC 568 to ARINC 429 and sends it to the flight control computer(FCC) and the electronic flight instrument system (EFIS).

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真·AZRAEL 发表于 2007-8-11 19:25

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AVIATION GLOSSARY A－E- -                                      
ATIS Airport Terminal Information Service 机场终端信息服务
ATIS Automated(automatic) Terminal Information Service 自动终端情报服务
ATM Air Traffic Management 空中交通管理
ATN Aeronautical Telecommunications Network 航空电信网
ATNP （ICAO）Aeronautical Telecommunication Network Panel （国际民航组织）航空电信网专家组
ATO Actual Time Over 实际经过时间
ATRK Along-Track Error 沿航线误差
ATS Air Traffic Services 空中交通服务
ATSC Air Traffic Services Communication 空中交通服务通信
ATT Attitude 姿态
AUSSAT Australian Satellite 澳大利亚卫星
AUTODIN Automated Digital Network 自动化数字网络
AUTOVON Automatic Voice Network 自动化话音网络
AUX Auxiliary 辅助
AVOL Aerodrome Visibility Operational Level 机场能见度运行等级
AVPAC Aviation VHF Packet Communications 航空甚高频分组通信
AVS Aviation Standards 航空标准
AWANS Aviation Weather And NOTAM System 航空气象和航行通告系统
AWOP （ICAO） All Weather Operations Panel （国际民航组织）全天候运行专家组
AWOS Automated Weather Observing System 自动化气象观测系统
AWP Aviation Weather Processor 航空气象处理器
AWS Aviation Weather Service 航空气象服务
AZ Azimuth transmitter 方位台
B
BARO Barometric 气压
BAZ Back Azimuth 后方位，背航道
BER Basic Encoding Rules 基本编码规则
BER Bit Error Rate 误码率
BIT Built-In-Test 机内测试
BITE Built-In-Test Equipment 机内测试设备
BOP Bit Oriented Protocol 面向位的协议
BPS bits per second 每秒传送位数；每秒比特数
BPSK Biphase Shift Keying 两相相移键控
BRITE Bright Radar Indicator Tower Equipment 塔台高亮度雷达显示设备
BRL Bearing Range Line 方位距离线
BSU Beam Steering Unit 天线方位控制组件
BUEC Backup Emergency Communications 备用紧急通信
C 通信
C-Band Approx. 5,000MHz C波段
C/A (CA) Code Course Acquisition Code 粗获码（民用的）
C/I Carrier-to-Interference Ratio 信号干扰比
C/N Carrier-to-Noise Ratio 信噪比
CA Conflict Alert 冲突告警
CA GPS Course- Acquisition Code 粗捕获码（民用码）
CA/MSAW Conflict Alert/Minimum Safe Altitude Warning 冲突告警/最低安全高度警告
CAA Civil Aviation Administration, Civil Aeronautical Authority, Civil Aviation Authority 民航局
CAAC General Administration of Civil Aviation of China 中国民用航空总局
CAASD Center for Advanced Aviation System Development(The MITRE Corporation) (MITRE公司)高级航行系统开发中心
CAB Civil Aeronautical Bureau 民航局
CARF Central Altitude Reservation Function 中央飞行高度保留功能
CARs Civil Air Regulations 民用航空规则
CASITAF CNS/ATM implementation task force 新航行系统实施特别工作组
CAT Category 仪表着陆等级
CATⅠ Category Ⅰ 一类仪表着陆
CATⅡ Category Ⅱ 二类仪表着陆
CAT Ⅲa Category Ⅲa 三类a级仪表着陆
CAT Ⅲb Category Ⅲb 三类b级仪表着陆
CAT Ⅲc Category Ⅲc 三类c级仪表着陆
CATC Civil Aviation Training Center 民航培训中心
CATMAC Co-operative Air Traffic Management Concept 空中交通管理合作方案
CBA Cost/Benefit Analysis 成本效益分析
C-BAND The frequency range between 4000 and 8000MHz 4000到8000MHz频段
CBI Computer Based Instruction 计算机基本指令
CBT Computer-Based Training 计算机辅助训练
CC Connection Confirm 联接确认
CCA Continental Control Area 大陆管制区
CCC 蜂窝式CNS概念
CCD Consolidated Cab Display 综合机舱显示器
CCIR International Radio Consultative Committee 国际无线电咨询委员会
CCITT International Telegraph and Telephone Consultative Committee 国际电报电话咨询委员会
CCP Contingency Command Post 应急指挥站
CCWS Common controller workstation 通用管制员工作站
CD Common Digitizer 通用数字化仪设备
CDC Computer Display Channel 计算机显示通道
CDI Course Deviation Indicator 偏航指示器
CDM Code division multiplex 码分复用
CDM Continuous Delta Modulation 连续增量调制
CDMA Code Division Multiple Access 码分多址
CDT Controlled Departure Times 管制离场时间
CDTI Cockpit Display of Traffic Information 驾驶舱交通信息显示
CDU Control Display Unit 控制显示组件
CEP Circular error probability 圆概率误差
CERAC Combined Center Radar Approach Control 雷达进近管制联合中心
CFCC Central Flow Control Computer 中央流量管制计算机
CFCF Central Flow Control Facility 中央流量管制设施(功能)
CFDPS Compact Flight Data Processing System 小型飞行数据处理系统
CFWP Central Flow Weather Processor 中央流量气象处理机
CFWSU Central Flow Weather Service Unit 中央流量气象服务单元（组件）
CHI Computer Human Interface 机人接口
CIDIN Common ICAO Data Interchange Network 国际民航组织公用数据交换网
CIS Cooperative independent surveillance 合作式独立监视
CLAM Cleared Level Adherence Monitoring 放行高度保持监视
CLB Climb 爬升
CLK Clock 时钟
CLNP Connectionless Network Protocol 无连接网络规程（协议）
CLR Clear 清除
CMC Central Maintenance Computer 中央维护计算机
CMD Command 命令
CMS Cabin Management System 机舱管理系统
CMU Communications Management Unit 通信管理单元
CNDB Customized Navigation Database 用户导航数据库
CNS Consolidated NOTAM System 综合航行通告系统
CNS/ATM Communication Navigation, Surveillance/Air Traffic Management 通信导航监视/空中交通管理
CODEC Coder/Decoder 编码器/解码器
COM/MET/OPS Communication/ Meteorology/ Operations 通信/气象/运行
COMLO Compass Locator 罗盘定位器；罗盘示位信标
COMM Communication 通信
COMP Compressor 压缩器
COMSEC Communications Security 通信保安
CON Continuous 连续
CONUS Continental, Contiguous, or Conterminous United States 美国大陆本部(四十八州)
COP Change Over Point 转换点
COP Character Oriented Protocol 面向字符协议
COTS Commercial Off-the-Shelf 商业货架产品供应
CPDLC Controller Pilot Data Link Communications 管制员驾驶员数据链通信
CPFSK Continuous Phase Frequency Shift Keying 连续相位频移键控
CR Connection Request 联接申请
CRA Conflict Resolution Advisory 冲突解脱咨询
CRC Cyclic Redundant Check 循环冗余校验
CRCO Central Route Charges Office 中央航路收征费办公室
CRM C Reference Model C参考模式
CRM Collision Risk Modeling 碰撞危险模型
CRM Crew Resource Management 机组人员安排
CRT Cathode Ray Tube 阴极射线管
CRZ Cruise 巡航
CSA Standard Accurate Channel 标准精度通道
CSE Course Setting Error 航线设定误差
CSMA Carrier Sense Multiple Access (datalink protocol) 载波侦听多址访问
C/SOIT Communication/ Surveillance Operational Implementation Team 通信监视运行实施小组（美国）
CTA Calculated Time of Arrival 计算到达时间
CTA Control Area 管制区
CTAS Central Tracon Automation System 中央终端雷达进近管制自动系统
CTL Control 控制
CTMO Central traffic Management Organization 中央交通流量管理组织
CTMO Centralized Traffic Management Organization 中央交通管理组织
CTOL Conventional Take Off and Landing 常规起飞着陆
CTR Control zone 管制地带
CTS Control Tracking Station 控制跟踪站
CU Control Unit 控制单元
C§W Control and Warning 控制和告警
CW Carrier Wave 载波
CWI Continuous Wave Interference 连续波干扰
CWP Central Weather Processor 中央气象处理器
CWSU Center Weather Service Unit 中央气象服务单元
D
D/A Digital-to-Analog 数/模转换
DABS Discrete Addressable Beacon System 离散寻址信标系统
DADC Digital Air Data Computer 数字大气数据计算机
D-ATIS Digital Automatic Terminal Information Service 数字自动终端信息服务
DA Decision Addressing beacon system 决断寻址信标系统
DA Demand Assignment 按需分配
DA/H Decision Altitude(Height) 决断高度
DARC Direct Access Radar Channel 直接存取雷达信道
DARP Dynamic Air Route Planning 动态航线计划
DARPS Dynamic Aircraft (Air) Route Planning Study 动态飞机航线计划研究
DC Departure Clearance 离场放行许可
DC Direct Current 直流(电)
DCC Display Channel Complex 显示通道组合
DCIU Data Control Interface Unit 数据控制接口单元
DCL Departure Clearance Delivery 起飞许可传送
DCPC Direct Controller Pilot Communication 管制员驾驶员直接通信
DES Data Encryption Standard 数据加密标准
DF Direction Finder 测向器
DFCS Digital Flight Control System 数字飞行控制系统
DFDAU Digital Flight Data Acquisition Unit 数字飞行数据采集单元
DGCA Director-General Civil Aviation 民航局长
DGNSS Differential Global Navigation Satellite System 差分全球导航卫星系统
DGPS Differential Global Positioning System 差分全球定位系统
DH Decision Height 决断高度
DIP Diplexer 双工器
DL Data Link 数据链
DLAC Data Link Applications Coding 数据链应用编码
DLAS Differential GNSS Instrument Approach System 差分GNSS仪表进近系统
DLK data link 数据链
DLORT FAA Data Link Operational Requirements Team FAA数据链运行要求工作组
DMAP ICAO Data Link Mobile Applications Panel(proposed) 国际民航组织数据链移动应用专家组（建议）
DME Distance Measuring Equipment 测距设备
DME/N Distance Measuring Equipment/Normal 标准测距设备
DME/P Distance Measuring Equipment/Precision 精密测距设备
DMU Data Management Unit 数据管理单元
DO（DOC） Document 记录（文件）
DOD Department of Defense (美国)国防部
DOP Dilution of Precision 精度扩散因子
DOT Department of Transportation (美国)运输部
DOTS Dynamic Ocean Tracking System 动态海洋跟踪系统
DP Disconnect Request 分离拆线请求
DPF Data Processing Function 数据处理功能
D8PSK Differential Eight-Phase Shift Keying 差分8相移键控
DPSK Differential Phase Shift Keying 差分相移键控
DRMS Distance Root Mean Square 距离均方根值
DRN Document Release Notice 文件发放通告
DSB－AM Double Sideband Amplitude 双边带调幅
DSDU Data Signal Display Unit 数据信号显示单元
DSP Departure Sequencing Program 起飞排序计划；离港排序计划
DT Data 数据
DTE Data Terminal Equipment 数据终端设备
DT&E Development Test and Evaluation 开发测试和评估
DTF Data Test Facility 数据检测设备
DTG 待飞距离
DTN Data Transport Network 数据传输网络
DUAT Direct User Access Terminal 用户直接存取终端
DVOR Doppler Very high frequency Omni-directional Range 多普勒甚高频全向信标
E
EANPG European Air Navigation Planning Group 欧洲航行规划小组
E-DARC Enhanced Direct Access Radar Channel 增强的直接存取雷达信道
EARTS En route Automated Radar Tracking System 航路自动化雷达跟踪系统
EASIE Enhanced ATM and Mode S Implementation in Europe 欧洲S模式和增强的空中交通管理实施项目
EATCHIP European ATC Harmonization Implementation Program 欧洲空中交通管制协调实施计划
EATMS European Air Traffic Management System 欧洲空中交通管理系统
ECAC European Civil Aviation Conference 欧洲民航会议
ECEF 地心地固坐标
EDCT Estimated Departure Clearance Time 预计离港起飞放行时间
EET Estimated Elapsed Time 预计经过时间
EFAS En route Flight Advisory Service 航路飞行咨询服务
EFAS Extended Final Approach Segment 扩展最后进近段
EFIS Electronic Flight Instrument System 电子飞行仪表系统
EFC Expect Further Clearance 预期进一步放行许可
EFIS Electronic Flight Information System 电子飞行情报系统
EGNOS European global navigation overlay system 欧洲全球导航重迭系统
EHSI Electronic Horizontal Situation Indicator 电子平面状态显示器
EIRP Equivalent Isotropic Radiate Power 等效各向同性辐射功率
EISA Extended Industry Standard Architecture 扩展的工业标准结构
EL Elevation Transmitter 仰角台
ELOD En route sector Load 航路扇区负载管制飞机数量
ELT Emergency Locator Transmitter 紧急示位发射机
EMC Electromagnetic Compatibility 电磁兼容
EMI Electromagnetic Interference 电磁干扰
ENRI Electronic Navigation Research Institute （日本）电子导航研究所
EOF Emergency Operations Facility 应急运行设施
EPA Environmental Protection Agency 环境保护署
ER Error 误差
ERL Environmental Research Laboratories 环境研究实验室
ERM En Route Metering 航路计量管制
ERN Earth Referenced Navigation 大地参考导航
ERP Effective Radiated Power 有效幅射功率
ES End System 终端系统
ESA European Space Agency 欧洲航天局
ESCAN Electronic Scanning(radar antenna)
ESMMC Enhanced SMMC 增强的系统维护监视台
ESP En route Spacing Program 航路间隔计划
EST Estimated message 预计信息
ETA Estimated Time of Arrival 预计到达时间                              
ETB Estimated Time of Boundary 预计边界时间
ETD Estimated Time of Departure 预计离港时间
ETG Enhanced Target Generator 增强的显示目标产生器
ETN Estimated Time of Entry 预计进入时间
ETO Estimated Time Over 预计飞越时间
ETSI European Telecommunications Standards Institute 欧洲电信标准学会
EU European Union 欧洲联盟
EURATN European ATN 欧洲航空电信网
EUROCAE European Organization for Civil Aviation Electronics 欧洲民用航空电子学组织
EUROCONTROL European Organization for the Safety of Air Navigation 欧洲航行安全组织(欧安局)
EVS Enhanced Vision System 增强视景系统
EWAS En-route Weather Advisory Service 航路气象咨询服务
F
F&E Facilities and Equipment 设施和设备
F,E&D Facilities, Engineering, and Development 设施、工程和开发
FAA Federal Aviation Administration (美国)联邦航空局
FAATC FAA Technical Center (美国)联邦航空局技术中心
FAF Final Approach Fix 最终进近坐标
FANS ICAO Future Air Navigation Systems （国际民航组织）未来航行系统
FANS Special Committee on Future Air Navigation Systems 未来航行系统特别委员会
FANS(Phase II) Special Committee for the Monitor- ing and Co-ordination of Develop- ment and Transition Planning for the Future Air Navigation System 未来航行系统监督、协调发展与过渡规划 专门委员会
FAR Federal Aviation Regulation 联邦航空条例
FAS Final Approach Segment 最后进近段
FASID Facilities And Services Implementation Document 设施和服务实施文件
FCC Flight Communication Center 飞行通信中心
FCC Federal Communication Commission 联邦通信委员会
FCC Flight Control Computer 飞行控制计算机
FDAU Flight Data Acquisition Unit 飞行数据收集单元
FDDI Fiber Distributed Data Interface 光纤分布数据接口
FDEP Flight Data Entry and Printout 飞行数据输入和输出
FDI Fault Detection and Isolation 故障检测和隔离
FDIO Flight Data Input/Output 飞行数据输入/输出
FDM Frequency Division Multiplex 频分复用
FDMA Frequency Division Multiple Access 频分多址
FDP Flight Data Processor 飞行数据处理器
FDPS Flight Data Processing System 飞行数据处理系统
FDR Flight Data Recorder 飞行数据记录仪
FEATS Future European ATS System Concept 未来欧洲空中交通服务系统方案
FEATS ICAO Future European Air Traffic Management System 国际民航组织未来欧洲空中交通管理系统
FEC Forward Error Correction 前向纠错
FGC Flight Guidance Computer 飞行引导计算机
FGCC Federal Geodetic Control Committee 联邦大地测量管理委员会
FI Flight Inspection 飞机校验
FIC Flight Information Center 飞行信息中心
FIFO First In-First Out 先入先出
FIFO Flight Inspection Field Office 飞行检查现场办事处
FIR Flight Information Region 飞行情报区
FIS Flight Information Services 飞行情报服务
FISA Automatic Flight Information Service 自动飞行信息服务
FL Flight Level 飞行高度层
FLIR Forward Looking Infra-red Detection 前视红外线探测
FM Frequency Modulation 调频
FMC Flight Management Computer 飞行管理计算机
FMEA Failure Mode Effects Analysis 故障模式效果分析
FMS Flight Management System 飞行管理系统
FMS Frequency Management System 频率管理系统
FMSG Frequency Management Study Group 频率管理研究组
FMU Flight Management Unit 飞行管理组件
FMU Flow Management Unit 流量管理单元
FOC Full Operation Capability 全运行能力
FOM Figure of Merit 性能指数
FPA Flight Path Angle 航迹倾角
FPD Flight Plan Data 飞行计划数据
FPS Military Primary Radar 军用一次雷达
FREQ Frequency 频率
FRP Federal Radio navigation Plan 联邦无线电导航计划（美国）
FS Functional Statement 功能描述
FSAS Flight Service Automation System 飞行服务自动化系统
FSDPS Flight Service Data Processing System 飞行服务数据处理系统
FSK Frequency Shift Keying 频移键控
FSP Flight Strip Printer 飞行进程单打印机
FSS Flight Service Station 飞行服务站
FSTN Federal Security Telephone Network 联邦政府保安电话网络
FT Functional Test 功能测试
FTE Flight Technical Error 飞行技术误差
FY Fiscal Year 财政年度; 会计年度
G
GA General Aviation 通用航空
GA Ground annta 地面天线
Gatelink Datalink for packed aircraft 网关数据链路
GADS Generic Aircraft Display System 通用航空器显示系统
GAIT Ground-based Augmentation and Integrity Technique 陆基增强和完好性技术
GAO Government Accounting Office (联邦)政府会计署
GBA Geostationary broadcast area 静止卫星广播区域
GCAS Ground Collision Avoidance System 地面防撞系统
GCS Ground Controlled Approach 地面控制系统
GDLP Ground Data Link Processor 地面数据链处理器
GDOP Geometic Dilution of Position 位置几何扩散因子
GDOP Geometry Dilution of Precision 精度几何扩散因子
GEO Geostationary 静地的
GEO Geostationary Earth Orbit 相对地球静止轨道静止卫星
GES Ground Earth Station 地面地球站
GFE Government-Furnished Equipment 政府提供的设备
GHz Giga hertz 千兆赫兹
GIB GNSS integrity broadcast 全球导航卫星系统完好性数据广播
GIC GNSS Integrity Channel 全球卫星导航系统完好性通道
GICB Ground-initiated Comm-B 地面启动的B类通信
GIRU Ground Interrogator Receiver Unit 地面应答机接收单元
GIS Geographical Information System 地理信息系统
GLONASS Global Orbit Navigation Satellite System 全球轨道导航卫星系统(俄罗斯)
GLS GPS Landing System GPS着陆系统
GM Guidance Material 指导材料
GMC Ground Movement Control 地面活动管制
GMSK Gaussian Minimum Shift Keying
GMT Greenwich Mean Time 格林威治时间
GNAS General NAS 综合国家空域系统
GND Ground 地
GNE Gross Navigational Error 总导航误差
GNR Global Navigation Receiver 全球导航接收机
GNSS Global Navigation Satellite System 全球导航卫星系统
GNSSP ICAO Global Navigation Satellite Systems Panel 国际民航组织全球卫星导航系统专家组
GPSSU Global Positioning System Sensor Unit 全球定位系统（GPS）传感器组件
GOES Geostationary Operational Environmental Satellite 静地运行环境卫星
GOS Grade of Service 服务等级
GOSEP Government Open Systems Interconnection Profile 政府开放系统互联结构
GOSIP Government Open systems Implementation Profile 政府开放系统实施结构
GP Glide-Path 下滑道
GPIP Glide-Path Intercept Point 下滑道截获点
GPIWP Glide Path Intercept Waypoint 滑行道切入点
GPO/GPI General Purpose Output/General Purpose Input 通用输出/通用输入
GPS Global Positioning System 全球定位系统
GPWS Ground Proximity Warming System 近地告警系统
GREPECAS Caribean/South American Planning and Implementation Regional Group 加勒比/南美洲计划和实施区域小组
GRS Ground-Reference Station 地面基准站
GRS80 Geodetic-Reference System－80 大地基准系统－80
GS(G/S) Glide Slope 下滑坡度
GS Ground Speed 地速
GSA General Services Administration 综合服务管理局(联邦政府下属)
GSL General Support Laboratory 综合保障实验室
GSM Global System （or Mobile） Communication 全球通信系统
GWS Graphic Weather Service 图形气象服务
H
H Homing radio beacon 归航无线电信标
HARN High Accuracy Reference Network 高精度参考网
HAT Height Above Touchdown 高于接地点的高度
HCI Human Computer Interface 人机接口
HDD Head Down Display 下视显示器
HDG Heading 航向
HDOP Horizontal Dilution Of Precision 精度水平扩散因子
HEMP High Altitude Electromagnetic Pulse 高空电磁脉冲
HEO High Elliptical Orbit 高椭圆率轨道
HF High Frequency(3-30MHz) 高频
HFDL High Frequency Data Link 高频数据链
HGA High Gain Antenna 高增益天线
HIRF High Intensity Radiated Fields 高强度辐射场
HIWAS Hazardous In-flight Weather Advisory Service 飞行时遇危险天气的咨询服务
HMI Human Machine Interface 人机接口
HPA high power amplifier 高功率放大器
HPF Horizontal Position Fix Error 水平位置坐标误差
HSI Horizontal Situation Indicator 水平位置指示器
HUD Head-up Display 平视显示仪
HUI Head up Display
HVAC Heating, Ventilating, And air Conditioning 加热,通风和空调
Hybird GNSS/ILS Precision Approach/Landing based on combination of GNSS localizer and ILS glide path 基于GNSS航向和ILS下滑道组合的精密进近/着陆系统
Hz Hertz 赫兹
I
IA5 International Alopabet 5 国际字母表第5号码
IACA International Air Carrier Association 国际航空公司协会
IACSP International Aeronautical Communication Service Provider 国际航空通信业务提供者
IAF Initial Approach Fix 初始进近点（坐标）
IAG International Association of Geodetical 国际测地协会
IAIN International Association of Institutes of Navigation 国际导航学会联合会
IAOPA International Council of Aircraft Owner and Pilot Associations 航空器企业主和驾驶员协会国际委员会
IAP Instrument Approach Procedure 仪表进近程序
IAR Intersection of Air Routes 航路交叉点
IAS Indicated Air Speed 指示空速
IASC Inter Area Speech Circuit 区域间话音线路
IATA International Air Transport Association 国际航空运输协会
IBAC International Business Aviation Council 国际商业航空委员会
ICAO International Civil Aviation Organization 国际民航组织
ICCAI(A) International Co-ordination Council of Aerospace Industries Associations 国际宇航工业联合会合作委员会
ICD Interface Control Document 接口控制文件
ICO Interim Circle Orbit 中高度圆轨道
ICSS Integrated Communications Switching System 综合通信转换系统
ID Identifier(Identification) 标识码(编码、识别标志)
ID Instrument Departure 仪表离场
IDSG ICAO Internet Working Standards Drafting Group 国际民航组织网间标准起草小组
IEEE Institute of Electrical and Electronic Engineers 电气和电子工程师学会
IF Intermediate approach Fix 中间进近定位点
IFALPA International Federation of Airline Pilots Associations 航空公司驾驶员协会国际联合会
IFATCA International Federation of Air Traffic Controllers' Associations 空中交通管制员协会国际联合会
IFCN Interfacility Flow Control Network 设施(单位)间流量管制网络
IFF 敌我识别器
IFM Integrated Flow Management 综合流量管理
IFR Instrument Flight Rules 仪表飞行规则
IFRB International Frequency Registration Board 国际频率注册委员会
IFSS International Flight Service Station 国际飞行服务站
IBM International Business Machines (美国)国际商用机器公司
ILA International Law Association 国际法律协会
ILS Instrument Landing System 仪表着陆系统
IMA Integrated Modular Avionics 集成化模块式航空电子设备
IMAWP Initial Missed Approach Waypoint 起始复飞航路点
IMC Instrument Meteorological Conditions 仪表气象条件
IMCS Interim MCS 过渡性监控/管制软件
IMO International Maritime Organization 国际海事组织
IMS Integrity Monitoring System 完好性监视系统
IN Information Need 信息需求
INMARSAT International Marine Satellite Organization 国际移动卫星组织（原名国际海事卫星组织）
INS Inertial Navigation System 惯性导航系统
INS Insert 插入
INTNET Integrated Data Communications Network 集成化数据通信网络
I/O input/output 输入/输出
IOACG Informal Indian Ocean Air Traffic Services Coordinating Group 非正式印度洋空中交通服务协调小组
IOC Initial Operational Capability 初始运行能力
IOD GPS Issue of Data 全球定位系统数据发布
ION Institute of Navigation 导航学会
IOR Indian Ocean Region 印度洋区域
IOT§E Initial Operational Test and Evaluation 初始运行测试和评估
IP Internetwork Protocol 网络间协议
IPACG Informal Pacific Air Traffic Control Coordination Group 非正式太平洋空中交通管制协调小组
IRS Inertial Reference System 惯性参考系统
ISA International Standard Atmosphere 国际标准大气
ISDN Integrated Service Digital Network 综合业务数字网络
ISNS 国际卫星导航服务
ISO International Organization for Standardization 国际标准化组织
ISPACG Informal South Pacific ATS Co-Ordination Group 非正式南太平洋空中交通服务协调小组
ISSS Initial Sector Suite Subsystem 起始扇区管制席位分系统
ITU International Telecommunication Union 国际电信联盟
ITWS Integrated Terminal Weather Service 综合终端气象服务
IVAD Integrate Voice and Data 综合话音和数据（通信数据链）
IVRS Interim Voice Response System 过渡性话音响应系统
IWP Interim Working Party 临时工作组
JAWS Joint Airport Weather Studies 联合机场气象研究
JCAB Japan Civil Aviation Bureau 日本民航局
JAWS Joint Airport Weather Studies 联合机场气象研究
JPO Joint GPS Planning Office 联合GPS规划办公室
JSS Joint Surveillance System 联合监视系统
Kbps Kilo bits per second 千位每秒
KDP Key Decision Point 关键性决定点
kHz Kilohertz 千赫
KLAAS Kinematics Local Area Augmentation System 动态地面局域增强系统
KLADGNSS Kinematics Local Area Differential GNSS 动态地局域差分GNSS                                 
kW Kilowatt 千瓦
kWh Kilowatt hour 千瓦小时
L
L1 1575.42MHz L-Band carrier L1频率
L2 1227.6MHz L-Band carrier L2频率
LAAS Local Area Augmentation System 局域增强系统
LACAC Latin American Civil Aviation Commission 拉丁美洲民航委员会
LADGNSS Local Area Differential GNSS 局域差分全球卫星导航系统
LADS 局域差分系统
LAN Local Area Network 局域网
LAT/LONG Latitude/Longitude
Lat/Long Reference Waypoint 经/纬度
经/纬度参考点
L-Band Approx 1,500MHz L 波段（1500兆赫附近频段）
LCD Liquid Crystal Display 液晶显示
LCN Local Communications Network 局域通信网络
LDGPS Local Differential GPS 本地差分GPS
LEO Low Earth Orbit 近地轨道、低高度轨道
LGA Low Gain Antenna 低增益天线
LCN Local Communications Network
LLWSA(S) Low Level Wind Shear Alert System 低空风切变报警系统
LMM Locator Middle Marker 航向中指点标
LNA Low Noise Amplifier 低噪音放大器
LNAV Lateral Navigation 侧向导航
LOC Localize Transmitter(Localizer) 航向台发信机
LOM Locator Outer Marker 航向外指点标
LON Longitude 经度
LORAN－C Long Range Navigation System 罗兰－C导航系统
LPC Linear Predicative Coding 线性预测编码
LRR Long Range Radar 远程雷达
LRU Line Replaceable Unit 在线替换部件
LSB Least Significant Bit 最低有效位
LVA Large Vertical Aperture 大垂直孔径
M
MALSR Medium-intensity Approach Lighting System with Runway alignment indicator lights 中级亮度进近照明系统，并有跑道对准线显示灯
MAP Missed Approach Point 复飞点
MAR Minimally Attended Radar 需低度护理的雷达
MASPS Minimum Aeronautical System Standards 最低航空系统标准
MASPS Minimum Aircraft (Aviation) System Performance Specification(Standards) 最小飞机(航空)系统性能标准 扩展频谱
MAWP Missed Approached Waypoint
MB Market Beacon 指点标
MBI Message Block Identifier 信息块指示器
mbps、Mbit/s mega bits per second 兆位每秒
MCA Minimum Crossing Altitude 最低穿越高度
MCC Maintenance Control Center 维护控制中心
MCDU Multifunction Control Display Unit 多功能控制显示单元
MCI Mode C intruder 装有C模式应答器的入侵飞机
MCS Master Control Station 主控站
MCS Monitoring/Control Software 监控/管制软件
MDA Minimum Descent Altitude 最低下降高度
MDT Maintenance Data Terminal 维护数据终端
MEA Minimum En-route Altitude 最低航路高度
MED Manual Entry Device 人工输入器
MET Meteorology 气象
METAR Meteorological Report of Aerodrome Conditions 机场条件气象报告
MFCP Multifunction Control Display Panel 多功能控制显示面板
MFDU Multifunction Display Unit 多功能显示单元
MHz Megahertz 兆赫
MIDANPIRG Middle East Air Navigation Planning and Implementation Regional Group 中东地区航行规划<请合法使用í?t>实施小组
MIFR Master International Frequency Registration 国际频率注册管理站(员)
MIL Military 军方
MKR Marker 指点标
MLS Microwave Landing System 微波着陆系统
MMALS Multi-Mode Approach and Landing System 多模式进近和着陆系统
MMI Man-Machine Interface 人机接口
MMR Multi-Mode Receiver 多模式接收机
MMS Maintenance Management System 维护管理系统
MMW Millimeter Wave 毫米波
MNPS Minimum Navigation Performance Specification 最低导航性能规范
MNPSA MNPS airspace 最低导航性能规范空域
MNT Mach Number Technique 马赫数技术
MOCA Minimum Obstruction Clearance Altitudes 最低超障净空高度
Mode S specific services S模式特定业务
MODEM Modulator-Demodulator 调制解调器
MOPR Minimum Operational Performance Requirements 最低运行性能要求
MOPS Minimum Operational Performance Standards 最低运行性能规范
MORA Minimum Off-Route Altitude <请合法使用软件>低偏离航路高度
MOS Metal-Oxide Semiconductor 金属-氧化物半导体
MOU Memorandum Of Understanding 备忘录
MPS Maintenance Processor Subsystem 维护处理机分系统
MRA Minimum Reception Altitude 最低接受高度
MRT Multi-Radar Tracking 多雷达跟踪
MRT-VU Multi-Radar Tracking using Variable Update 采用变化更新的多雷达跟踪
MSA Minimum Sector Altitude 最低扇区高度
MSAT 移动业务卫星系统（美国的）
MSAW Minimum Safe Altitude Warning 最低安全高度警告
MSCP Mobile Satellite Service Provider 移动卫星业务提供者
MSE Mean Square Error 均方误差
MSK Minimum Shift Keying 最小移频键控
MSL Mean Sea Level 平均海平面
MSP Mode S specific protocol S模式特别协议(规程)
MSU Mode Select Unit 模式选择单元
MTBA Mean Time Between Alarm(Warning) 平均告警间隔时间
MTBF Mean Time Between Failure 平均故障间隔时间
MTBO Mean Time Between Outage 平均故障停工间隔时间
MTBR Mean Time Between Repairs 平均故障修复间隔时间
MTBUR Mean Time Between Unit Replacements 平均更换故障单元间隔时间
MTBW Mean Time Between Warning 平均告警间隔时间
MTD Maintenance Terminal Display 维护终端显示器
MTI Moving Target Indicator 活动目标指示器
MTM Module Test and Maintenance 模块测试和维护
MTMIU Module Test and Maintenance Bus Interface Unit 模块测试和维护总线接口单元
MTN MEGA Transport Network MEGA运输网络
MTSAT Multi-Functional Transport Satellite 多功能传送卫星（日本）
MTTDA Mean Time To Dispatch Alert 平均签派告警时间
MTTF Mean Time To Failure 平均故障时间
MTTM Mean Time To Maintenance 平均维护时间
MTTR Mean Time to Repair 维平均修时间
MTTR Mean Time to Restore 平均恢复时间
MU Management Unit 管理单元
MUS Minimum Use Specification 最低应用规格
MUX Multiplexer 复用器
MN Multisensor Navigation 多传感器导航
MUX Multiplexer 多工器，复用器
MWARA Major World Air Route Area 世界主要航路区
MWO Meteorological Watch Office 气象观测台
N
N Navigation 导航
NA Not Applicable 不可用
NACK Negative Acknowledgment 出错通知
NAD North American Datum 北美数据(基准)
NADIN National Airspace Data Interchange Network 国家空域数据交换网
NAGU 咨询报告
NAILS National Airspace Integrated Logistics Support 国家空域综合后勤保障
NAPA 国家公共管理科学院（美国）
Nanosecond One billionth of a second 十亿分之一秒
NAR National Airspace Review 国家空域审议
NARACS National Radio Communications System 国家无线电通信系统
NAS National Airspace System 国家空域系统
NASA National Aeronautics and Space Administration 国家航空和宇航局(美国)
NASNET National Airspace System Network 国家空域系统网络
NASP National Airport System Plan 国家航空港系统计划
NASPALS NAS Precision Approach and Landing System 国家空域系统进近和着陆系统
NAT North Atlantic 北大西洋地区
NAT ADSG North Atlantic Automatic Dependent Surveillance Development Group 北大西洋自动相关监视开发小组
NAT ATS North Atlantic Air Traffic Services 北大西洋空中交通服务
NAT SPG North Atlantic Systems Planning Group 北大西洋系统规划组
NATCOM National Communications Center, Kansas City, Missouri 国家通信中心(位于密苏里州堪萨斯城)
NATS National Air Traffic Service 国家空中交通服务
NAV Navigation
NAVAID Navigational Aid 导航设施
NAVAID Radio Aid to Navigation 无线电助(导)收设备
NAVD North American Vertical Datum 北美垂直向数据
NCA National Control Authority 国家指挥当局
NAWP National Aviation Weather Processor 国家航空气象处理机
NCC Network Control Center 网络控制中心
NCD No-Computed Data 无算出数据
NCIU NEXRAD communications interface unit 改进型气象雷达通信接口单元
NCP Network Control processor 网络控制处理器
NCS Network Coordinating Station 网络协调台
NDB Nondirectional Radio Beacon 无方向信标
NEAN North European ADS-B Network 北欧ADS－B网络
NEOF National Emergency Operations Facilities 国家应急指挥设施
NEXRAD Next Generation Weather Radar 改进型气象雷达；下一代气象雷达
NGRS National Geodetic Reference System 国家测地参考系统
NGS National Geodetic Survey 国家测地勘察
NICS NAS Interfacility Communications System 国家空域系统设施间的通信系统
NIST National Institute of Standards and Technology 国家标准和技术研究所
NLES 导航岸站
NM (NMI) Nautical Mile 海里,节
NMC National Meteorological Center 国家气象中心(美国)
NMCE Network Monitoring and Control Equipment 网络监控设备
NMDPS Network Management Data Process System 网络管理数据处理系统
NMS Navigation Management System 导航管理系统
NOAA National Oceanic and Atmospheric Administration 国家海洋和大气局(美国)
NOPAC North Pacific 北太平洋
NOTAM Notice to Airmen 航行通告
NPA Non-Precision Approach 非精密进近
NPDU Network Protocol Data Unit 网络协议数据单元
NPLAS National Plan of Integrated Airport Systems 国家综合航空港系统的计划
NRC National Research Committee 国家科学研究委员会（美国的）
NSAP Network Service Access Point 网络服务访问点
NSB National Secure Bureau 国家保安局（美国的）
NSC Network Service Centre 网络服务中心
NSDU Network Service Data Unit 网络服务数据单元
NSE Navigation System Error 导航系统误差
NSSF NAS Simulation Support Facility 国家空域系统的仿真保障设施
NTLA National Telecommunications Information Agency 国家电信资料署(美国)
NTSB National Transportation Safety Board 国家运输安全委员会(美国)
NWS National Weather Service 国家气象服务(美国)
O
O&M Operation and Maintenance 运行和维修
O.R. Operational Requirement 运营要求
OACC Oceanic Area Control Center 海洋区域管制中心
OAS Obstacle Assessment Surface 障碍物评价面
OAS Oceanic Automation System 海洋自动化系统
OCA Obstacle Clearance Altitude 超障净高度
OCA Oceanic Control Area 海洋管制区
OCH Obstacle Clearance Height 超障高
OCM Oceanic Clearance Message 海洋放行许可信息
OCP ICAO Obstacle Clearance Panel 国际民航组织超障净空专家组
OCS 运行控制系统
OCS Obstacle Clearance Surface 超障面
ODALS Omnidirectional Approach Lighting System 全向进近灯光系统
ODAPS Oceanic Display and Planning System 远洋飞行显示和规划系统
ODF Oceanic Development Facility 海洋开发设施
ODIAC Operational Development of Initial Air-ground data Communications 早期空-地数据通信运行开发
ODL Oceanic Data Link 海洋数据链
OEM Original Equipment Manufacturer 原始设备制造商
OFDPS Offshore Flight Data Processing System 近海飞行数据处理系统
OLAN Onboard Local Area Network 机载局域网
OLDI On-line Data Interchange 联机数据交换
OMB Office of Management and Budget 国家管理和预算局(美国)
OMEGA A navigation system that uses two high-powered transmitter grounds stations to broadcast a continuous wave signal. 奥米加导航系统
ODALS Omnidirectional Approach Lighting System 全向进近灯光系统
OOOI Out-Off-On-In 滑出-起飞-接地-停靠门位
OP Operational 运行
OP SUP Operational Supervisor 运营监督
OPMT Operations Planning Management Team 运营规划管理小组
OPTUS Name of one of Australia's Telecommunications Providers 澳大利亚电信业务提供者之一的名字
OR Operational Requirements 运行要求
ORD Operational Readiness Demonstration 运行准备就绪示范
ORI Orientation 面向
OSHA Occupational Safety and Health Administration 职业安全和卫生局(美国)
OSI Open Systems Interconnection 开放系统互联
OSST FAA Oceanic Separation Standard Team 联邦航空局海洋间隔标准小组（美国）
OTA Office of Technology Assessment 技术评估办公室(美国)
OTC Overseas Telecommunications Company 海外通信公司
OTS Organized Track Structure 编组航迹系统
P-Code Precision Code (精)P-码
oxy Oxygen 氧气
P
P 精密码（军用码）
PA Preassignment Arrangement 预先分配
PAC Pacific 太平洋
PACOTS Pacific Organized Track System 太平洋组织的跟踪系统
PANS Procedures for air navigation services 空中航行服务程序
PANS-OPS Procedures for Air Navigation Services-Aircraft Operations 航行服务-航空器运营程序
PANS/RAC Procedures for Air Navigation Services-Rules of the Air Traffic 空中导航服务程序，空中交通服务规则
PAPI Precision Approach Path Indicator 精密进近航道指示器
PAR Precision Approach Radar 精密进近雷达
PATWAS Pilots Automatic Telephone Weather Answering Service 驾驶员电话询问气象的自动回答服务
PCA Positive Control Area 绝对管制区
PCC Pilot Controller Communication 驾驶员管制员通信
PCFL Pre-Cleared Flight Level 预放行高度
PCI Protocol Control Information 协议控制信息
PCM Pulse Code Modulation 脉码调制
P-Code The GPS precision code GPS精密码（军用码）
PCS Power Conditioning System 电力调节系统
PDC Pre-Departure Clearance 起飞前放行许可
P-DME Precision Distance Measuring Equipment 精密测距仪
PDN Public Data Network 公共数据网
PDOP Position Dilution of Precision 位置精度扩散因子
PEDI Planning, Education, Demonstration and Implementation 规划、教育、演示和实施
PER Packed Encoding Rules 分组编码规则
PET Pacific Engineering Trials 太平洋工程试验
PF Position Fix Error 位置固定误差
PFCS Primary Flight Control System 主要飞行控制系统
PFE Path Following Error 路径跟踪误差
PFL Planned Flight Level 计划飞行高度
PHARE Program for Harmonized ATM Research in EUROCONTROL 欧安局空中交通管理研究协调计划
PIAC Peak Instantaneous Aircraft Count 瞬时峰值飞机数目
PIREP Pilot Report 驾驶员报告
PL Psuedolite 伪卫星
PN Pseudo-noise 伪噪音
PNCS Performance Navigation Computer System 导航计算机系统性能
POB Persons On Board 机上人员
POC Proof Of Concept 概念验证
POR Pacific Ocean Region 太平洋区域
PPS Precise Positioning Service 精密定位服务
PR Psuedo-Range 伪距离
PRC Pseudorange Correction 伪距校正
PRE Pseudo-Range Error 伪距误差
PRF Pulse Repetition Frequency 脉冲重复频率
PPI Plan Position Indicator 平面位置显示器
PRM Precision Runway Monitoring 精密跑道监视
PRN Pseudo Random Number 伪随机噪数字
PROFS Program for Regional Observing and Forecasting Services 地区观测和预报服务项目
PRR Pseudo-Range Rate 伪距变化率
PSK Phase Shift Keying 相移键控
PSR Primary Surveillance Radar 一次监视雷达
PSTN Public Switched Telecommunications Network 公共电信交换网
PTR Production Test Requirements 产生测试请求
PTT Push To Talk 按下发话
PTT Post、Telegraph、Telephone 邮政、电报、电话
PUPS Principal User Processor 主要用户处理器
PVC Permanent Virtual Circuit 永久性虚拟电路
PVD Plan View Display 平面图显示器
PVT Position, Velocity, Time 位置、速度、时间
PZ－90 基准坐标系统（俄罗斯）
Q
QAM Quadrate Amplitude Modulation 正交调幅
QC Quality Control 质量控制
QFE Atmospheric Pressure at Aerodrome Elevations or at Runway Threshold 在机场海拨高度或跑道端头的大气压
QNH Altimeter Sub-scale Setting to obtain Elevation when off the Ground 高度表示刻度设置以得到离地时的海拨高度
QOP Quality Operating Procedures 质量操作程序
QOS Quality-Of-Service 服务质量
QPSK Quadruple Phase Shift Keying 四相相移键控
R
R&D Research and Development 研究和开发
R,E&D Research, Engineering and Development研究,工程和开发
RA Resolution Advisory 解脱咨询
RAAS Regional Augmentation System 区域增强系统
RAC Rules of the Air and ATS 空中规则和空中交通服务
RACGAT Russian/American Coordinating Group on Air Traffic Control 空中交通管制俄/美协调组
RADNET Radar Data Network 雷达数据网
RADS Radar Alphanumeric Display System 雷达字母和数字显示系统
RAFC Regional Area Forecast Center 区域预报中心
RAI Radio Altimeter Indicator 无线电高度指示器
RAIM Receiver Autonomous Integrity Monitoring 接收机自主完好性监测
RAMP Radar Modernization Project 雷达现代化计划
RAPPS Remote Area Precision Positioning System 边远地区精密定位系统
RAN Regional Air Navigation 区域空中导航
RBDS Radio Broadcast Data System 无线电广播数据系统
RCAG Remote Center Air/Ground communications facility 空对地通信设施的遥控中心
RCC Rescue Coordination Center 援救协调中心
RCCC Regional Communications Control Center 地区通信控制中心
RCE Radio Control Equipment 无线电控制设备
RCF Radio Communication Failure 无线电通信故障
RCF Remote Communications Facility 遥控通信设施
RCL Radio Communications Link 无线电通信链路
RCL Runway Center Line 跑道中心线
RCO Remote Communications Outlet 遥控通信引出线
RCP Required Communication Performance 所需通信性能
R&D Research and Development 研究和开发
RDARA Regional and Domestic Air Route Area 地区和国内航路区
RDF Radar Data Function 雷达数据功能
RDH Reference Datum Height 基准高度
RDMI Radio Distance Magnetic Indicator 无线电距离磁指示器
RDP Radar Data Processing 雷达数据处理
RDPS Radar Data Processing System 雷达数据处理系统
RDS Radio Data System 无线电数据系统
RDSS Radio Determination Satellite Service 无线电测位卫星系统
RDT&D Research, Development, Trials and Demonstrations 研究、开发、试验和演示
RECAP Reliability Evaluation and Corrective Action Program 可靠性评估和修改工作项目
REIL Runway-End Identification Lights 跑道终端识别灯；跑道终端标志灯
RF Radio Frequency 无线电频率
RFI Radio Frequency Interference 无线电频率干扰
RFP Request for Proposal 提案建议
RFTP Request For Technical Proposal 技术建议提案
RFU Radio Frequency Unit 射频组件
RGCSP ICAO Review of the General Concept of Separation Panel 国际民航组织飞行间隔总概念审查专家组
RGIC Ranging GNSS Integrity Channel 全球导航系统完好性信道范围
RGS Remote Ground Station 远端地面站
RHCP Right-Hand-Circular Polarized 右旋圆极化
RLASM Reduced Lateral Separation Minima 减小的最小侧向间隔
RLLS runway lead-in lighting system 跑道引进灯光系统
RLOSM Reduced Longitudinal Separation Minim 减小的最小纵向间隔
R&M Reliability and Maintainability 可靠性和可维护性
RML Radar Microwave Link 雷达微波链路
RMM(S) Remote Maintenance Monitoring System 远端维护监视系统
RMS Reference Monitoring Station 基准监控站
RMS Remote Monitoring Subsystem 远端监视分系统
RMS Root-Mean-Square 均方根值
RMSC RMS Concentrators 远端监视分系统集中器
RNAV Area Navigation 区域导航
RNG Range 距离、范围
RNP Required Navigation Performance 所需导航性能
RNPC Required Navigation Performance Capability 所需要导航性能能力
RNP GM Guidance Material for Required Navigation Performance 所需导航性能指导材料
RO Roll Out 出厂、装备完备
ROB Right Outboard 右（飞机）外侧、右（飞机）机翼翼尖处
ROC Rate Of Climb 爬升率
ROD Rate Of Descent 下降率
RPG Radar Products Generator 雷达分量发生器
RPS Radar Position Symbol 雷达位置符号
RRWDS Radar Remote Weather Display System 雷达远端气象显示系统
RSC Rescue Sub-Center 援救分中心
RSP Required System Performance 所需系统性能
RSS Root-Sum-Square ( root of squares sum) 平方和根值
RSSCD Runway Surface Condition 跑道道面情况
RTA Required Time of Arrival 要求的到达时间
RTCA Radio Technical Commission for Aeronautics 航空无线电技术委员会
RTCM Radio Technical Commission for Maritime 海事无线电技术委员会
RTD Research and Technical Development 研究和技术开发
RTDGPS Real-Time DGPS 实时差分全球定位系统
RTI Real-Time Interrogate 实时询问器
RTK Real Time Kinematics carrier tracking 实时动态载波跟踪（技术）
RTR Remote Transmitter/Receiver 远端无线电收/发信机
RTS Request To Send 请求发送
RVR Runway Visual Range 跑道视程
RVSM Reduced Vertical Separation Minima 缩减的垂直间隔最低标准
RVV Runway Visibility Value 跑道能见度值
RWY Runway 跑道
S
S Surveillance 监视
SA Selective Availability 选择可用性
SAR Search And Rescue 搜索与救援
SAR System Analysis Recorder 系统分析记录器
SARPs（SARP） Standard and Recommended Practices 标准和建议措施
SARSR Air route surveillance radar 航路监视雷达
SATCOM Satellite Communication 卫星通信
SCAA 瑞典民航局
SCAT Special Category 特别类型
SCAT-I Special Category-I precision approach 特别Ⅰ类精密进近
SCDU Satellite Control Data Unit 卫星控制数据单元
SCPC single channel per carrier 单路单载波
SCSI Small Computer System Interface 小型计算机系统接口
SD standard deviation 标准偏差
SDM Space Division Multiplex 空分复用
SDM System Definition Manual 系统定义手册
SDMA Space Division Multiple Access 空分多址
SDU Satellite Data Unit 卫星数据组件
SEI System Engineering and Integration 系统工程和集成
SELCAL Selective Calling system 选择呼叫系统
SEP Spherical Error Probability 球形误差概率
SET System Embedded Training 系统附带培训
SICAS Secondary Surveillance Radar Improvements and Collision Avoidance 二次监视雷达改进和防撞系 统（国际民航组织）
SICASP ICAO Secondary Surveillance Radar Improvements and Collision Avoidance Panel 国际民航组织二次监视雷达改进和防撞系 统专家组
SID Standard Instrument Departure 标准仪表离场
SIF Standard Interchange Format 标准相互交换格式
SIGMET Significant Meteorological Information 重要气象信息
SIGWX Significant Weather 重要天气
SITA International Society for Aeronautical Telecommunications 国际航空电信协会
SIU Satellite Interface Unit 卫星接口单元
SLAP Standard Instrument Approach Procedure 标准仪表进近程序
SLS Satellite-based Landing System 星基着陆系统
SM 保密模块
SMC System Management and Communication 系统管理和通信
SMC Surface Movement Control 场面活动管制
SMGCS Surface Movement Guidance and Control Systems 场面活动引导和控制系统
SMMC System Maintenance Monitor Console 系统维护监控台
SMR Surface Movement Radar 场面活动监视雷达
SNOWTAM A special NOTAM for notifying snow. ice etc. 雪情通告
SNR Signal-to-Noise Ratio 信噪比
SOIT Satellite Operational Implementation Team 卫星运行实施小组
SOLAS Safety of Life at Sea(IMO standard) 洋区生存安全标准（IMO）
SOP Standard Operating Procedure 标准运行程序
SPDS Space-based Position Determination System 星基位置测定系统
SPS Standard Position Service 标准定位服务
SRADD Software Requirements And Design Description 软件要求和设计描述
SRD System Requirements Document 系统需求文件
SRR Search and Rescue Region 搜寻和援救区
SSALF Simplified Short Approach Lighting System with sequenced Flashing lights 简易短距进近近灯光系统,并有顺序闪光灯
SSALR Simplified Short Approach Lighting system with Runway alignment indicator lights 简易短距进近灯光系统, 并有跑道对准线指示灯
SSB Single Sideband 单边带
SSF System Support Facility 系统保障设施
SSL System Support Laboratory 系统保障实验室
SSMA Spreaded Spectrum Multiple Access 扩频多址
SSR Secondary Surveillance Radar 二次监视雷达
SSR Mode A/C Secondary Surveillance Radar 二次监视雷达A/C模式
SSR Mode S Secondary Surveillance Radar with Selective Addressing 二次监视雷达S模式（选址模式）
SSSC Single Sideband Suppressed Carrier 单边带抑制载波
SST Supersonic Transport 超音速运输机
STAR Standard Instrument Arrival Routes 标准仪表进场航线
STC Supplementary type certification 补充型号认证
STCA Short Term Conflict Alert 短期冲突告警
STDMA Self- organizing Time Division Multiple Access (datalink) 自组织时分多址
STEP Service Test and Evaluation Program 服务试验和评估项目
STOL Short Take Off and Landing 短距起飞和着陆
STP Standard Temperature and Pressure 标准气温和气压
SV Space Vehicle 空间运载体(卫星)
SVN Space Vehicle Number 卫星号
SVS Synthetic Vision System 综合视景系统
SVU Satellite Voice Unit 卫星话音单元
S/W Software 软件
T
T&E Test and Evaluation 试验和评估
TA Traffic Advisory 交通咨询
TA Transition Altitude 过渡高度
TAA Terminal Advanced Automation 终端高级自动化
TACAN Tactical Air Navigation 战术空中导航（塔康导航系统）
TACS Technical Activities Committee 技术工作委员会
TARTAR Meeting for the planning and coordination of implementation of ATS Routes Through the Airspace of the Russian Federation, including Middle Asia 通过俄联邦包括中亚的ATC航路实施协调和规划会议
TAS True Air Speed 真空速
TBA To be Announced 待发布
TBD To Be Determined 待定
TC Type Certificate 型号认证
TCA Terminal Control Area 终端区
TCAS Traffic (alert and) Collision Avoidance System 交通（告警和）避撞系统
TCASⅠ Traffic (alert and) Collision Avoidance SystemⅠ 一类TCAS（提供告警）
TCASⅡ Traffic (alert and) Collision Avoidance SystemⅡ 二类TCAS（提供告警并提供冲突咨询）
TCC Terminal Control Center 终端管制中心
TCCC Tower Control Computer Complex 塔台管制计算机组
TCH Threshold Crossing Height 跑道入口跨越高度
TCM Technical Coordination Meeting 技术协调会
TCP Transport Control Protocol 运输控制规程(协议)
TCP/IP Transmission Control Protocol/Internetwork Protocol 传输控制协议/网络间协议
TCS Tower Communications System 塔台通信系统
TCWP Threshold Crossing Waypoint 跑道跨越点
TDLS Tower Data Link System 塔台数据链系统
TDM Time Division Multiplex 时分复用
TDM Track Definition Message 跟踪定义信息
TDMA Time Division Multiple Access 时分多址
TDOP Time Dilution Of Precision 时间精度扩散因子
TDWR Terminal Doppler Weather Radar 终端多普勒气象雷达
TDZ Touch-Down Zone 接地区域
TELCO Telephone Company 电话公司
TERPS Terminal Instrument Procedures 终端仪表程序                 
TFTS Terrestrial Flight Telephone System 全球飞行电话系统
TGL Touch and Go Landing 连续起落
THR Threshold 跑道入口
TIS Traffic Information Service(uplinking of Mode S data) 交通情报服务（S模式数据上行链）
TKE Track Angle Error 航迹误差
T/L Top-Level 顶层（设计）
TL Transition Level 过渡层(级)
TLS Target Level of Safety 安全目标等级
TMA Terminal Control Area 终端控制区
TMA Terminal Maneuvering Area 终端机动区
TML Television Microwave Link 电视微波链路
TMP Traffic Management Processor 交通管理处理器
TMS Traffic Management System 交通管理系统
TMT 电信移动卫星公司（加拿大）
TMU Traffic Management Unit 交通管理单元
TN 挪威电信公司
TNA Turn Altitude 转弯高度
TNH Turn Height 转弯高
TOC Top of Climb 爬高顶点
TOD Top of Descent 下降极限
TOGA（TO/GA） Take-Off, Go-Around 起飞、复飞
TPX Military beacon system 军用信标系统
T/R Receiver-Transmitter 收发信机
TRACAB Terminal Radar Approach Control in the tower Cab 在塔台舱的终端雷达进近管制
TRACON Terminal Radar Approach Control 终端雷达进近管制
TRACS Terminal Radar and Control System 终端雷达和控制系统
TREAT Trans EUR/ASIA Air Traffic Management Initiative(for FANS-1 Equipped Aircraft ) 跨欧亚空中交通管理启动项目（提供给装备FANS－1的航空器使用）
TRP Mode S Transponder S模式应答器
TRSA Terminal Radar Service Area 终端雷达服务区域
TSC DOT Transportation System Center 运输部运输系统中心(美国)
TSD Traffic Situation Display 交通状态显示器
TSE Total System Error 总系统误差
TSO Technical Standards Order 技术标准指令
TSR Terminal Surveillance Radar 终端监视雷达
TSSF Terminal System Support Facility 终端系统保障设施
TAA Terminal Advanced Automation 终端高级自动化
TV Television 电视
TVOR Terminal VOR 终端甚高频全向信标
TWDL Two-Way Data Link 双向数据链
TWEB Transcribed Weather Broadcast 抄录的气象广播
TWR Tower 塔台
U
UAC Upper Area Control Center 高空区域管制中心
UAR Upper Air Route 高空航路
UAV Uniform Annual Values 年均值
UDRE User Differential Range Error 用户差分测距误差
UDS 国家差分系统
UERE User Equivalent Range Error 用户等效测距误差
UFDR Universal Flight Data Recorder 通用飞行数据记录器
UHF Ultra High Frequency(300-3000MHz) 特高频
UIC Upper Information Center 高空情报中心
UIR Upper Flight Information Region 高空飞行情报区
ULR Ultra Long Range 超远程
UNDP United Nations Development Program 联合国开发计划署
UPS Uninterruptible Power System 不间断供电系统
URA User Range Accuracy 用户测距精度
URE User Range Error 用户测距误差
USAF United States Air Force 美国空军
USCG United State Coast Guard 美国海岸警卫队
UTA Upper Control Area 高空管制区
UTC Universal Time Coordinated 世界协调时
UUHF Ultra High Frequency 超高频
V
V1 Critical engine failure velocity 发动机失效速度
V2 Takeoff climb velocity 起飞爬升速度
VAC Visual Approach Chart 目视进近图
VASI(S) Visual Approach Slope Indicator System 目视进近坡度指示系统
VCS Voice Communication System 话音通信系统
VDL VHF Datalink 甚高频数据链
VDOP Vertical Dilution Of Precision 垂直精度扩散因子
VDR VHF Data Radio 甚高频数据无线电
VFOP Visual Flight Rules Operations Panel 目视飞行规则运行专家组
VFR Visual Flight Rules 目视飞行规则
VHF Very High Frequency(30-300MHz) 甚高频
VHF R/T Very High Frequency Receiver/Transmitter 甚高频收/发信机
V/L VOR/Localizer 全向信标/航向台
VLF Very Low Frequency 甚低频
VMC Visual Meteorological Conditions 目视气象条件
VNAV Vertical Navigation 垂直导航
VNR VHF Navigation Receiver 甚高频导航接收机
VOLMET Meteorological Information for Aircraft in Flight 飞行中的气象信息
VOR VHF Omnidirectional Radio Range(navigation beacon) 甚高频全向信标
VOR/DME A system in which a VOR and DME station are co-located 甚高频全向信标和测距仪合装的台址
VORTAC VOR Co-located with TACAN 甚高频全向信标塔康
VOT VHF Omnidirectional range Test 甚高频全向信标试验
VOX Voice Transmission 话音传输
VRS Voice Response System 话音响应系统
VSAT Very Small Aperture Terminal 甚小孔径终端
VSCS Voice Switching and Control System 话音交换和控制系统
VSI Vertical Speed Indicator 垂直<请合法使用软件><请合法使用软件>器
VSM Vertical Separation Minimum 垂直间隔最低标准
VSP Vertical Speed 垂直速度
VSWR Voltage Standing Wave Ratio 电压驻波比
VTOL Vertical Take Off and Landing 垂直起飞和着陆
VASI Visual Approach Slope Indicator 目视进近坡度指示器
W
WAAS Wide Area Augmentation System 广域增强系统
WADGPS Wide Area Differential GPS 广域差分全球定位系统
WADS Wide Area Differential System 广域差分系统
WAFC World Area Forecast Center 世界区域预报中心
WAFS World Area Forecast System 世界区域预报系统
WARC World Administrative Radio Conference 世界无线电行政大会
WCP Weather Communications Processor 气象通信处理器
WDI Wind Direction Indicator 风向指示器
WGS World Geodetic Survey 世界测量系统
WGS-72 World Geodetic Survey of 1972 标准测地系统1972年标准
WGS-84 World Geodetic Survey of 1984（Standard Geodetic reference System） 标准测地系统1984年<请合法使用软?t>
WMSC Weather Message Switching Center 气象信息交换中心
WMSCR WMSC Replacement 气象信息交换中心更新
WP Way Point 航路点
WRS Wide-area Reference Station 广域<请合法使用èí?t>站
WS Wind Shear 风切变
WS Wind Speed 风速 WSR Weather Service Radar 气象服务雷达
Wx Weather 气象         WXR Weather Radar 气象雷达
XCVR Transceiver 收发信机
XLS Multi-mode Landing System 多模式着陆系统
XMT Transmitter 发射机          XPDR Transponder 应答机
XT(XMTR) Transmitter 发射机
XTK 航迹侧向偏离
YSAS Yaw Stability Augmentation System 偏航稳定增强<请合法使用软件>      YD Yaw Damper 偏航阻尼
Z-Marker Z maker beacon Z指点标

[ 本帖最后由 真·AZRAEL 于 2007-8-11 19:29 编辑 ]

真·AZRAEL 发表于 2007-8-11 19:25

. u4 m. Y: t4 z+ r; T7 Q

飞机常用单词英汉对照 1
manned flight 有人驾驶的飞机
aerodynamics 空气动力学
cambered surface 弧面，弯曲面
characteristic 性能，特性
drawing 图纸
glider 滑翔机
lift 升力
model 模型，样机
structure 结构，构造
transportation 运输；运输工具
wing 机翼
biplane 双翼机
control v. 操纵，控制，驾驶
rib 肋，翼肋
cloth fabric 布织物
lifting surface 升力面
girder 桁架，构架，机架，骨架
bamboo 竹材
strip 带状物，狭片，长条，简易机场，跑
道
piano wire 钢琴丝
auxiliary surface 辅助翼面
stability 安定性，稳定性
configuration 外形，形状，结构，构造型
式，布局
truss type structure 桁架式结构
strut 支柱，支撑
wire-braced wing 张线支撑的机翼
cockpit 飞机驾驶舱
fabric-covered body 织物覆盖的机体
fuselage 机身
engine 引擎，发动机
tail 尾部
strong lightweight structure 坚固的轻型结
构
resistance 反抗，抵抗，阻力，阻尼，电阻
friction 摩擦，摩擦力
potential speed 潜在速度
strength 强度
plane 飞机
designer 设计者
superstructure 上层结构，上部结构
wooden former 木质翼肋，木质隔框
stringer 桁条，长桁
smooth streamline shape 光滑流线型
welded thin-wall steel tubing 焊接的薄壁钢
管
stressed-skin structure 承力蒙皮结构
plywood eggshell-like structure 层板薄壳式
结构
laminated wood ring 层半框架，胶合板框
架
landing gear 起落架
aluminum-alloy sheet 铝合金板
monocoque structure 硬壳结构
all-metal aircraft 全金属飞机
semi-monocoque structure 半硬壳式结构
rigidity 刚度
structural challenge 结构方面的困难（挑
战）
high-altitude flight 高空飞行
mysterious adj. 神秘的，费解的
fatigue 疲劳
pressurization and depressurization cycle 增
压减压循环
fail-safe construction 破损安全结构
rip-stop doubler 止裂加强板
strategic location 关键部分
crack 裂纹
structural component 结构部件
stress 应力
aviation maintenance technician 航空维修技
师
aircraft structure 飞机结构
control surface 操纵面，舵面
stabilizer 安定面
flap 襟翼
trim tab 调整片
spoiler 扰流板，阻流板，气流防护板
rudder 方向舵
attitude 状态，姿态，姿势
compression 压缩，压力
tension 拉伸，拉里，张力
torsion 扭曲，扭转，扭力，扭转
bending 弯曲，挠曲
shear 剪切，剪力，切变，切力
definition 定义，阐明，确定，明确
crush v. 压碎，击碎，牙边，挤压
press v. 压缩，冲压，挤，推
stretch v. 伸展，伸长，拉紧，延伸
cable 钢索
bolt 螺栓
material 材料
layer 层，夹层，薄片，条
river 铆钉
tensile force 拉力
overstressing 过度应力，超限应力
permanent deformation 永久变形
strain v. 硬变，变形，延伸率，过度使用
airworthy adj. 适航的，飞行性能好的
assembly 组合，装配，总装组件，部件，
装配件
stress analysis 应力分析
performance 性能，特性，行为，表现，实
行，实施，完成，操作
specification 详细说明，技术规格，技术条
件，说明书
danger 危险
failure 失败，故障，事故，破坏，断裂
nomenclature 术语，专用名称
aileron 副翼
trailing edge 后翼
wing tip 机翼翼端
roll v. 滚转，横滚，滑跑
lifting force 升力
jet airplane 喷气式飞机
cruise speed 巡航速度
approach speed 进场着陆速度，进近速度
landing speed 着陆速度，接地速度
chord line 弦线
angle of incidence 安装角
airfoil 翼型，翼剖面，机翼，翼面，气动
力面
longitudinal axis 纵轴
stabilizer setting angle 安定面安装角
horizontal stabilizer 水平安定面
vertical stabilizer 垂直安定面
sweep angle 后掠角
reference line 参考线
horizontal axis 水平轴线
antidrag wire 反阻力张线（承受与飞行阻
力相反的惯性力的对角张线）
leading edge 前缘
antilift wire 反升力张线
balanced control surface 平衡操纵面
equilibrium 平衡状态
hinge axis 铰链轴
static condition 静止状态
beltframe 连接隔框
skin 蒙皮
frame 框，隔框，壁板式隔框
boom (tailboom) 尾撑,尾梁
built-up structure 组合结构，拼装结构
cabin 机舱，客舱
helicopter 直升机
rotor 转子，叶轮，旋翼
tail rotor 尾桨
power train 动力系列
compartment 隔舱，舱，隔间，室
former 隔框，翼肋，维型框，假肋
cabane 顶架
canard 鸭式飞机，鸭式布局，鸭式翼，前
置平尾，前舵
cantilever beam 悬臂梁
external bracing 外部支撑
center section 中翼，中段
outer wing panel 外翼段
passenger 旅客，乘客
cabin airplane 闭舱式飞机
cockpit canopy 座舱盖，驾驶舱盖
control cable 操纵钢索
control lever (control stick) 驾驶杆，操纵杆
longitudinal control surface 纵向操纵面
lateral control surface 横向操纵面，横侧操
纵面
elevator 升降舵
ruddervator 方向升降舵（V型尾翼的）
control wheel 驾驶盘
semiwheel 半盘式
cowling 整流罩，包皮，防护罩
removable cover 可卸口盖
decalage 翼差角
dihedral angle 上反角
drag strut 阻力支柱（在布制蒙皮机翼结构
中，用以支持阻力张线的加强肋）阻力杆（起
落架前拉杆和后撑杆）
drag wire 阻力张线
pitching movement 俯仰运动
elevon 升降副翼
all-wing aircraft 三角翼飞机
fairing 整流罩，整流装置
streamlined contour 流线型外形
fireproof wall (fire-resistant wall) 防火墙
gap 间隙，间隔，翼隔
superposed airfoil 重叠机翼（双翼机获三
翼机）
stability 安定性，稳定性
inspection door 检查口盖
interplane strut 翼间支柱
jury strut 辅助撑杆，副支柱，保险撑杆
alighting gear 起落架，着陆装置
propeller blade 螺旋桨桨叶
lift wire (flying wire) 升力张线
longeron 大梁（机身或短舱的）
plating 重型金属蒙皮，表面镀层的金属板
yawing movement 偏航运动
pedal 脚蹬
shock absorber 减震器，缓冲器
slat 缝翼
attack angle 攻角，冲角，迎角
span 展长
spanwise a. adj. 延机翼展向
spar 机翼翼梁
spinner 螺旋桨整流罩
stagger 斜罩角
compressor blade 压缩机叶片
tandem-rotor helicopter 纵列式（双旋桨）
直升机
stagger wire 斜罩张线
sweepback 后掠角
antitorque rotor 尾桨，反扭矩尾桨
tail skid 尾撬，尾部保护座
tail wheel 尾轮
chordwise adj. 弦向
auxiliary fuel tank 副油箱，辅助油箱
antenna 天线
anti-collision light 防撞灯
stair door 登机梯舱门
engine nacelle 发动机短舱
deicer boot 除冰带
navigation light 航行灯
construction 结构，构造
longitudinal member 纵向构件
bending stress 弯曲应力
landing 着陆，接地，降落

飞机常用单词英汉对照 2
cantilever wing 悬臂机翼，张臂机翼
high-performance aircraft 高性能飞机
external strut 外撑杆
basic feature 基本特征
beam 辆，横梁，柱
monospar adj. 单梁，单梁的
two-spar adj. 双梁，双梁的
multispar 多梁，多梁的
web （大梁）腹板，辅助梁，纵墙，肋板
shear web 承减腹板
spanwise member 翼展方向构件，展向构
件
high-wing monoplane 上单翼机
tie rod 连干，系杆
brace wire 张线
drag load 阻力，阻力载荷
built-up I beam 装配的I型梁，组合的I型
梁
extruded I beam 挤压成型的I型梁
plain rib 普通肋，平面肋
chordwise member 弦向构件
compression rib 抗压翼肋，加强翼肋
cap strip 翼肋缘条
solid plywood web 整体的层板（胶合板）
腹板
cross bracing 交叉撑杆，横撑杆
gusset vt. 角撑，角撑板，装角撑板于
nail vt. 铁钉，钉住，用钉钉牢
stamped rib 模锻翼肋
truss-type cross section 桁架式横截面
stiffener 加强杆，加强板，加强件
fabric covering 布制蒙皮
plywood covering 胶合板蒙皮，层板蒙皮
tubular member 管型构件
formed rib 维型翼肋
integral fuel bay 整体油箱
attachment fitting 安装街头，连接接头
inspection 检查
service vt. 服务，使用，维护，维修，检查，
保养
frontspar 前梁
butt-rib 根部翼肋，平端头翼肋
flange vt. 翼梁缘条，凸缘，突缘，（在-----
上）安装突缘
end bow 机翼端部弯曲部分
nose rib 前缘翼肋
trailing edge strip 后缘条
aileron control cable 副翼操纵钢索
aileron control bell crank 副翼操纵双摇臂，
副翼操纵双摇臂曲板
tape v. 布带，带子，用带系扎
FWD fuselage fitting 机身前接头
washer 垫圈，垫片
nut 螺帽
retainer 护圈，卡圈，挡板，保持器
dowel pin 定位销，和缝销钉，暗钉
fuel vent line 燃油系统通气管路
door 舱门，口盖，入口
plate 板，盘，口盖
tab 调整片，补偿片，操纵片，标签
aileron tab 副翼调整片
position light 航行灯
landing and taxi light 着陆滑行灯
fuel filler door 燃油注油口
pitot tube 空速管，全静压管，全压管
stall warning unit 失速警告装置
RAM air inlet 冲压空气进口
Federal Aviation Administration 联邦航空
管理局
Advisory Circular 咨询通告
jet airliner 喷气式班机，喷气式航线客机
jet engine 喷气发动机
section 剖面，截面，型材，段，区域，部
分
assembly jig 装配架，型架
inboard wing 内翼
age hardening 时效硬化
dimension 尺寸，大小
bending load 弯曲载荷
tensional load 扭转载荷
stretch press 张拉成型机
airfoil surface 翼型表面
die vt. 冲切，用模（压）成型，模子，冲
模，压模
jaw 夹紧装置，钳口，夹爪
airfoil contour 翼型外形
formed 7075 sheet 成型的7075钣
tab segment 弓形薄片接头
forging adj. 锻造件
splice vt. 拼接，绞结，拼接板，绞结处
junction 接合，接合处，连接点
wing tank 机翼油箱
sealing compound 密封剂，密封腻子，封
口胶
center line 中心线，中线
mating adj. 配合，连接，配合的，相连
platform 平台
hydraulic cylinder 液压做动筒
synthetic rubber 合成橡胶
center wing 中翼
outboard wing 外翼
swept-wing 后略翼
nacelle 吊舱，发动机短舱
production break 工艺分离面
wide-bodied airliner 宽机体客机
flight control surface 飞行操纵面
pylon 吊架
main frame 承力构架，主构架，承力隔框
torque box 承扭盒段
auxiliary structure 辅助结构
permanent type fastener 永久式紧固件
butt-spliced 平头对接，平头拼装
flush fastener 埋头紧固件
honeycomb panel 蜂窝板
interference-fit 经配合，干涉配合
close-tolerance fastener 高精度公差紧固件
play 浮动，间隙，游隙
tolerance 配合公差，容差，加工裕度
flap vane 开缝襟翼导流片
exterior plate doubler 外部双重加强板
slat track 缝翼滑轨
can 筒型壳，密封外壳，包套
crew 空乘人员，机组，空勤组
cargo 货物
controls 操纵系统
item 项目，零件，产品（均指已列入清单
的项目）
streamline form 流线型式
accessory adj. 附属的，辅助的，附件，辅
助设备，部件
carburetor 汽化器，化油器，增碳器
magneto 磁电机
ignition lead 点火器导线
strainer 过滤器
fuel line 燃油管道
turnover 回转，循环，翻倒，倒置
emergency exit 紧急出口
capacity 容量，容剂，能力
classification 分类，类别，归类
assemblage 装配，安装，总装配件
bar 杆，棒，条
lateral bracing 横向支撑
tubular fuselage member 管状机身构件
interval 间隔，间隙，距离
bay 隔间，隔舱，段
diagonal member 斜构件，对角构件
percentage 百分比，百分数，比率
ring 环，圈，环形隔框
bulging 膨胀，凸出，褶皱皮
buckling 皱损，皱褶，波纹
glue v. 胶，粘结剂，胶合，粘结
aircraft-quality plywood 航空质量级的层
板
reinforcement 加强，加固，加强件，加强
部分
spar varnish 清光漆
waterproof protective material 防水保护材
料
deterioration 变质，恶化，损坏
penetration 尽头，穿透
moisture 湿气，潮气，水气
protective coating 保护涂层
hangar 机库，把-----放入机库中
evidence 证据，迹象，形迹
rot 腐烂，腐朽
fungus 霉菌，真菌
wood cell 木材组织，木材微孔
cone 圆锥，锥体，锥状物
conical shape 圆锥形状
cylindrical shape 圆柱形
dope 航空用漆，涂布油
fiberglass 玻璃纤维
stinger 尾不整流锥
turbulence 紊流
airflow 气流
streamlined nose 流线型机头
fail-safe feature 破损安全特性
tail section 尾部，尾段，尾舱
titanium 钛
rip-stop doubler 止裂加强板
beaded doubler 串珠加强板
window belt 窗口地带
panel 壁板，地板，板材，仪表板，操纵台，
面板，翼段
various stage 不同阶段
semiautomatic riveting machine 半自动铆
接机器
shaved riveting 平面铆接
dlampong aetion 夹紧力，夹紧作用
pounds per square inch (psi) 磅平方英寸
kilo-pascals (kpa) 千帕斯卡
uniform fastening 均匀一致的连接，均匀一
致的紧固件
countersunk cavity 埋头窝
sealing quality 密封性
fatigue life 疲劳寿命
longitudinal stiffener 纵向加强件
flattened hat section 扁帽型截面
stress level 应力水平
gauge 规格，尺寸，测量器，量规，卡规，
铆钉行距
pressure-cabin section 压力舱部分
upside-down position 倒置位置
dolly 平台车，铆钉顶铁，抵座，圆形锻磨
fixture 夹具，卡具，定位装置，安装用具，
型架，紧固
extruded z transverse frame 挤压成型Z型
截面的横向构件
mating jig 装配架，总装型架
cockpit enclosure 驾驶舱盖
subassembly 分装件，部件，局部装配件
fuselage shell 机身外壳
channel frame 槽型截面构件
floor 地板，底面
seat track 座椅滑轨
carpet 毡层，地毯，铺设地毯
expansion beam 伸缩梁
flight compartment 机组舱，空勤组舱
attachment 廉洁，固定，接头
stud bolt 桩螺栓
passenger compartment 客舱
nut strip 螺帽导板
splice plate 拼接板
spacer 间隔片，隔离物，垫片，垫圈
insulation 绝缘，隔离

飞机常用单词英汉对照 3
aisle panel 通道板
freight v. 货物，货运，装货
facilities v. 设备，装置，工厂，实验室
fabrication 制造，装配，生产
individual panel section 单独的壁板区段
railroad car 有轨电车
handing 处理，加工，操纵，管理，装卸，
搬运，吊运
handle v. 收兵，把手，处理
suction-cup principle 空吸杯装置
overhead monorail system 高架单轨吊车系
统
manufacturing cycle 生产周期
sheet-metal holder 钣金夹持器
arrangement 排列，布置，安装，构造，布
局
station number 站位编号
distance 距离
zero reference point 零参考点
floor beam 地板梁
keel beam 龙骨梁，底部大梁
stretch-formed skin panel 拉伸成型蒙皮板
stressed skin 承力蒙皮
multiple-element contracture 多元件构造
torsional unit 整体部件，组合件
advancement 进步，前进，改进
state-of-the-art 技术发展水平，目前工艺水
平，工艺状态
cutaway drawing 剖视图
intercostal 加强肋，肋间的
material 材料
process 过程，流程，工序，步骤，工艺规
程，工艺技术，制作方法
conclusion 结论
fatigue crack 疲劳裂纹
corrosion 腐蚀
cause 原因，理由，起因
stress concentration 应力集中
surface corrosion 表面腐蚀
galvanic corrosion 电化腐蚀
pitting corrosion 点状腐蚀，坑蚀
intergranular corrosion 晶界腐蚀
exfoliation 剥离，剥落
stress corrosion 应力腐蚀
fretting corrosion 磨损腐蚀，擦伤腐蚀
dissimilar metal 不同金属
metal bonding 金属粘结
seam 接缝，接口，接合面
damage 损伤，破坏，故障，事故
roller 磙子，滚桶，碾压机
chemical cleaning 化学清洁
etching process 浸蚀加工，酸洗处理
corrosion-inhibiting epoxy-type primer 防腐
蚀环氧树脂底层涂料
curing 处置，处理，固化处理
epoxy adhesive 环氧树脂粘结剂
Teflon fluorocarbon resin release cloth 特氟
隆碳氟化合物树脂防粘布
bleed cloth 透气布
vacuum bag 真空袋
autoclave 蒸压器
adhesive 粘性的，粘合剂
thermosetting epoxy resin 热固型环氧树脂
ultrasonic inspection equipment 超声波探
伤设备
void 空学，空洞
porosity 集气孔，沙眼，松孔
cabin altitude 座舱高度
pressure differential 压力差
flight station 乘员舱，（机组人员）飞行工
作位置
cabin pressurization load 座舱增压载荷
titanium fail-safe strap 钛金属破损安全带
clad alloy 包覆金属
entrapment 夹带，截留
formation 形成，组成，构成
lighter-gauge skin 较薄的机身蒙皮
heavy-gauge skin 大规格蒙皮，厚蒙皮
shot penning 喷丸强化，喷丸处理
main frame 主隔框，承力隔框，中部最大
隔框，主机架
stopper 止动器，限制器
channel 槽型型材，沟槽，管道，通道
cut out 切口，开口
attaching-clip angle 固定卡箍的角材
overlapping 重迭，搭接
overlapping stringer 搭接桁条
center line 中心线
transverse beam 横梁
wing box 机翼翼盒
wheel well 机轮舱，轮舱
deck 地板，层舱
sulfuric acid anodizing 硫酸阳极化处理
organic-coated steel fastener 有机物涂层的
钢紧固件
polyurethane painting 聚氨酯涂料
corrosion-prone area 易于腐蚀的部位
filled-sealed adhesive 嵌缝密封粘合剂
passenger door 客舱门
center elevating coat room 中央升运保护涂
层位置
galley service center (机上) 厨房服务中心
radome compartment 雷达无线整流罩舱
avionics compartment 电子设备舱
cargo compartment 货舱
center wing 中央翼，中翼
cargo door 货舱舱门
accessory compartment 附件舱
waste tank compartment 废液容器舱
fuel vent collection box 燃油通气集油盒
（进入同期管道的油在此集中再抽回油箱）
rueling interconnect line 加油互连通管道
fuel tank 燃油油箱
escape chute 应急离机口，应急离机滑梯，
应急脱离滑道
pressure fueling/defueling couplings 压力加
油/放油接头
hydraulic service center 液压服务中心
galley lift （机上）厨房升降梯
air conditioning duct 空气调节系统管道，
空调管
first class seating 头等舱座椅
lavatory 卫生间，盥洗室
weather radar 气候雷达
curved windowshield panel 弯曲成型的挡
风玻璃
Rolls Royce RB211 turbofan 罗—罗，
RB211涡轮风扇
geared elevator 随动升降舵（可操纵水平安
定面的）
flying stabilizer 可操纵安定面
auxiliary power unit (APU) 辅助动力装置
pressure dome 球形气密隔框
electronic service center 电子设备服务中
心
after hold (bulk cargo) 后货舱（散装货物，
笨重货物）
coach class seating 二等舱座位
conteinerised cargo 集装箱货物
double slotted flap 双开缝襟翼
inner aileron 内副翼
outer aileron 外副翼
full span slat 全展长缝翼
inward retraction main wheel 向内收起的
主机轮
forward retraction nose wheel 向前收起的
前机轮
air conditioning bay 空调设备舱
scale 规模，比例，标尺
fin 鳍，垂直安定面，垂直尾翼，立尾
elevator 升降舵
empennage 尾翼
appearance 外形，外貌，外表，外观，出
现，出版，发表
span 翼展，跨距，间距
auxiliary spar 辅助梁
hinge v. 铰链，合页，铰接接头
installation 装置，设备，安装，装配
dorsal fin 背鳍
streamlined fairing 流线型整流罩
swept-back vertical stabilizer 后掠式垂直
安定面
stabilator 全动式水平尾翼
primary controls 主操纵系统
secondary controls 辅助操纵系统
aileron assembly 副翼装配件
repair 修理
maintenance 维护，维修
technician 技术人员，技师，专门人员
proof of strength 强度验证，强度试验
limit load test 最大使用载荷试验，限制载
荷试验
horn 角状物，操纵摇臂
rigging load 校装载荷，水平调整载荷，装
配载荷
rational manner 合理的方式
conservation manner 保守的方式
movable tail surface 可动的尾部翼面
adjustable stabilizer 可调节的安定面（安定
面的安装角，可以改变）
ultimate bearing strength 极限挤压强度
mass balance 质量平衡
concentrated mass balance weight 集中的质
量平衡重量
control system operation 操纵系统的工作
function 功能，职能，作用
confusion 混淆，干扰，混乱
primary flight controls 飞行主操纵系统
pitch 抚养，绕横轴的运动，桨叶角，桨距，
紧固件的间距
yaw v. 偏航运动，偏航
two-control airplane 双操纵面飞机
lateral control 横侧操纵
directional control 方向操纵
stop v. 停止，制动，止动器，止动块，止
动装置
wear v. 磨损
slackness 松弛度
take-up adjustment 拉紧调整
trim system 配平系统
precaution vt. 预防措施，小心，注意，警
惕
pilot 驾驶员
trim device 配平装置
irreversible tab 不可逆调整片
reliability 可靠性
unmistakable warning 清除无误的警告，明
显的警告
control system lock 操纵系统锁
light twin airplane 轻型双发动机飞机
jackscrew attachment point 螺旋千斤顶安
装点
hinge point 铰接点
elevator balance panel bay 升降舵平衡翼板
隔间
flash beacon 闪光灯标
attach bracket 固定支架
primary flight control surface 飞行主操纵
面
cruising operation 巡航操作
fabric 织物，织品，布，纤维织品
water-proof 放水，不漏水，不透水
coating 涂层
drain hole 放油孔，排水孔，泄漏孔
hinge line 铰链轴线

飞机常用单词英汉对照 4
auxiliary control surface 辅助操纵面
doubler 加强板
balance weight 平衡重量
access door 检查口盖，工作窗，舱门
access panel 口盖，舱盖
honeycomb 蜂窝结构
vertical axis 立轴
flutter 颤振
aerodynamic surface 气动力面
bracket 支架，托架
hinge bracket 铰链支架，铰链架
displacement 位移，偏转，偏度
aerodynamic efficiency 空气动力效率，气
动效率，升阻比
control tab 操纵屏，随动补偿片
static balance 静态平衡
aerodynamic balance 气动平衡，气动补偿
dynamic balance 动平衡，飞行中立或力矩
的平衡
ruddervator V型尾翼，方向升降舵
secondary flight control surface 飞行辅助
操纵面
straight and level flight 直线水平飞行
servo tab 伺服片，随动补偿片，操纵片
control wheel 驾驶盘，操纵轮
crank 祛病，手柄，摇臂
cable system 钢索系统
actuating device 致动装置
screwjack 螺旋千斤顶，螺旋致动器
logical manner 合理的方式
top rim 顶部轮缘，顶部轮圈
position indicator 位置指示器
push-pull rod 推拉杆，传动杆
set-back hinge line 后置铰链轴线
track fitting 滑轨接头
leading edge slat 前缘缝翼
scalloped doubler 扇形式样加强板
fiberglass trailing edge 玻璃纤维后缘
beaded-doubler inner skin 串珠状加强板内
蒙皮
feedback fitting 反馈接合
actuation 致动器
damper 阻尼器，缓冲器，减震器
hinge pin 铰链销
cotter pin 开口销，开尾销
bearing 轴承
control arm 操纵臂，操纵杆
balance-weight arm 平衡重量支撑臂
detachable elevator 可拆卸的升降舵，可分
开的升降舵
copilot 副驾驶员
headroom 净空（高度），头上空间
visibility 能见度，视野
clearance 间隙，间距，惊恐，余地，清理，
排除
parachute 降落伞
provision 准备，预备，设备，装置
aerobatics 特技飞行，航空表演
demonstration 论证，说明，显示，示范
flight test 飞行试验
flying ability 飞行技能，飞行员驾驶技术
egress 出口，出路，外溢
personnel 全体人员，全体职员
navigator 导航设备，导航仪，领航员
flight engineer 随机工程师，空勤机械师
appurtenance (常用复数) 附属设备，附件，
配件，辅助工具
safety vt. 安全性，安全措施，安全，保险
assurance 确信，把握，信心，保证
concentration 集中，浓缩，聚集
propeller-driven airplane 螺旋桨飞机
blade 叶片，桨叶
air-transportation service 空运服务
seal 蜜蜂，封严，密封装置，密封垫，密
封胶
windshield 风挡，风挡玻璃
single-place airplane 单座飞机
accommodation 调节机能，适应，供应，
膳宿供应，座位，铺位
agriculture aircraft 农业用机
instrument 仪表，仪器
furnishing 装备，装置，设备，供给
dual controls 双重操纵机构
first pilot 正驾驶，机长
second pilot 副驾驶
statement 叙述，陈述，论点
up-to-date information 最新的资料
ventilation 通风，排起，换气
vision 观测，目击，观测，视线，视力
windshield wiper 雨刷，风挡刷
storm window 风雨窗，双层窗
airstream 气流
glare v. 闪光，强烈刺目的光
reflection 反射，折射，偏射
windshield panel 风挡窗格玻璃，窗格玻璃
impact 碰撞，冲击，撞击
flight path 飞行轨迹，航迹
velocity 速度
transparent plastic sheet 透明塑料板
flanged doubler 弯边的加强板，带凸缘的
加强板
retaining strip 固定带
waterproof adhesive tape 防水胶布带
vinyl channel 乙烯塑料槽型件
thickness 厚度
stiffness 刚度，刚性，安定性，稳定性
contour 轮廓线，外形
cowl deck 整流罩平台
felt seal 毛毡密封
indentation 压痕，凹槽
manufacturer 制造厂，生产厂家
maintenance manual 维修手册
laminated panel 层板
forged frame 锻制框架，锻造框架
hnoist provision 起重设备
gasket seal 垫片密封，填料密封
removal 拆卸
vinyl interlayer 乙烯塑料中间层
phenolic spacer 酚醛垫片，酚醛间隔物
phenolic block 酚醛块
gasket silicone seal 硅铜填料密封剂
semi-tempered glass 半强化玻璃
terminal 终端，终止，接线柱，引线接头
autopilot engage 自动驾驶仪接通
navigation marker light 航行标示灯，导航
信标接收机信号灯
airspeed indicator 空速指示器，空速表
pilot directional indicator 自动驾驶仪航向
指示器
gyro horizon 陀螺地平议，航空地平议
compass card 罗盘刻度盘
altimeter 高度表，高度计
rate of climb 爬升率
emergency pneumatic brake 应急气动刹
车，应急冷气刹车
autopilot axis indicator 自动驾驶仪接通指
示器
ice-detector light 积冰探测灯
engine pressure ratio 发动机压力比，发动
机增压比
engine r.p.m 发动机每分钟转速
thrust-reverser operating light 反推力工作
指示灯
tailpipe temperature 排气温度管，涡轮后温
度
master warning 主警告
gear down, lock light 起落架放下，锁定信
号灯
fuel flow 燃油流量
tachometer 马赫数表，M数表
navigation radio selection 导航无线电选择
仪
glide slope light 下坡滑度指示灯
autopilot disengage 自动驾驶仪切断
radio and radar control 无线电和雷达控制
air-brake handle 气动刹车减速手柄，减速
扳手柄
weather radar scope 气象雷达显示器
thrust lever 推力杆，油门杆
parking-brake letch 停机刹车锁
engine start lever 发动机启动手柄
turn and bank indicator 转弯侧滑仪
hydraulic system pressure 液压系统压力
stabilizer trim wheel 安定面配平手轮
rudder trim 方向舵配平
door post 门框
aluminum extrusion 铝挤压件
outer retainer 外部固定件，外部保持件
temperature sensing element 热敏元件
five-ply laminated panel 五层层压窗格玻
璃
insert 垫圈，插入物
defog bus bar 清除混蚀汇流条，扫雾汇流
条
conductive coating 导电敷层
chip retarder 碎裂阻聚剂
anti-ice bus bar 防冰汇流条
air carrier 航空运输公司，空运工具，运输
机
presence 存在
fuel fume 燃油蒸汽，燃油雾气
carbon mobixide 一氧化碳
dangerous trace 危险的痕迹
ventilation system 通风系统
heating system 加温系统
pressurization system 增压系统
first-class section 一等客舱段
trijetliner 三发喷气式航线客机
airline 航线，航空公司
coach section 二等舱客段
broad lofty ceiling 宽阔高耸的舱顶
spaciousness 宽敞，宽敞度
aisle 通道，走廊
divider 分配器，分隔器
personal effects 个人财物
carry-on luggage 随身的行李
safety-belt 安全带，保险带
cycle pressurization loading 循环增压载荷
pressurized airliner 座舱增压式航线客机
cabin sidewall lining 座舱侧壁材料
fail-safe structure 破损安全结构
acrylic plastic 聚丙烯塑料
peripheral seal 周边密封，周缘密封
sponge rubber 泡沫橡胶，多孔橡胶
spring retainer 弹簧座圈
shouldered screw 带托肩的螺钉
window-frame forging 窗框锻件
reveal 窗框半槽边，窗侧
retaining bracket 固定架
window ring pan 环形窗框
clip 夹子，卡箍
slit 长缝，裂缝
conditioned air 以调节空气
condensation 凝聚，凝结
acoustical seal 吸音密封
window shade 窗户遮光罩，窗帘
acoustical pane 吸音窗玻璃
side wall panel 侧壁板
formed sheet-metal structure 预成型钣金结
构
hydro press 水压机
stamp press 冲压机，模锻压力机
drop hammer 落锤
entrance 进口
upholstered cabin 装饰过的座舱

飞机常用单词英汉对照 5
matching upholstered panel 匹装备饰板
door latching 门扣
locking mechanism 锁机构
forward entry door 前登机门
hinge gate 铰接活门
door opening 舱门口
hinging mechanism 铰接机构，门枢机构
controlling mechanism 操纵机构，控制机
构
plug 塞子，孔塞，堵塞物
securing mechanism 关紧机构
inside handle 内部手柄
cam plate 凸轮盘，凸轮板
latching-crank assembly 柄锁装配件
angular movement 角运动
latch rod 锁杆
latch roller 锁滚柱
cock-crank assembly 竖起的曲柄装配件
torque-tube crank 扭转曲柄
hinge arm 铰接臂
guide arm 导向支臂
snubber 缓冲器，消音器
assist handle 辅助手柄
radius link 摇柄
pivot axis 止动销
stop pin 止动板
latch pin 锁销
door-open stowing latch lever 舱门打开收
锁杆
remainder 剩余部分
recessed handle 隐藏式手柄，隐藏在凹坑
处的手柄
complexity 错综复杂，复杂的事物
bogy 小车，转向架
normal mode 普通型
emergency mode 应急型
auxiliary mode 辅助型
emergency evacuation slide 应急排空滑块
deployment 部署，展开，散开，开伞
reveal seal 窗侧密封
outer pane spring assembly 外部窗格玻璃
弹簧装配件
permanently mounted screw 永久性固定螺
钉
nutplate 托板螺帽
ventilation hole 通气孔
ventilation slot 通气缝
window trim 窗狂细木工件，窗框装饰
trim pad 细木窗框衬垫
escutcheon plate 锁眼盖，孔罩板
handle mechanism housing 手柄机构外壳
avionics compartment lower door 电子设备
下舱门
avionics compartment aft door 电子设备后
舱门
air conditioning compartment door 空调舱
门
forward passenger door 前客舱门
center accessory compartment door 中央辅
助设备舱门
overawing passenger door 机翼上方客舱门
center cargo door 中央货舱门
APU compartment door 辅助电源设备舱舱
门
tail cone lower door 尾锥下舱门
overstress 过大应力，过载，超载
overstressing 过应力，超限应力
landing load 地面载荷（指起飞，着陆或在
地面滑行时，飞机结构承受的载荷）
fixed landing gear 固定式起落架
retractable landing gear 收放式起落架
conventional arrangement 常规配置，正常
配置
tricycle arrangement 前三点布局，前三点
配置
tricycle landing gear arrangement 前三点式
起落架布局
nose wheel 前轮
old conventional gear 旧式常规起落架
tail-wheel type 尾轮式
main gear 主起落架
strut 支柱，撑杆，吊架
body-gear strut 机身起落架支柱
wing-gear strut 机翼起落架支柱
nose-gear wheel 前起落架机轮
main wheel 主轮
axis 轮轴，车轮
main beam 主梁
caster 脚轮，转向轮
swivel 旋转接头，旋转节，旋转
shock-absorbing method 减震方法
rubber shock cord 橡皮减震绳，缓冲绳
rubber disk 橡皮盘
coil spring 螺旋弹簧，盘簧
hydraulic piston 液压活塞
flexible spring steel 柔性弹簧钢
oleo 油液减震器，油液减震支柱
air-oleo 空气—油液减震器
spring-oleo 弹簧—油液减震器
flexibility 柔性，韧性，挠性
elasticity 弹性
alloy steel 合金钢
brake 刹车
air-oleo strut 油气式减震支柱
cylinder 气缸，做动筒，圆筒
metering piston 分油活塞，分油柱塞
orifice 小孔
metering pin 调节油针
taxi 滑行
cross-sectional drawing 剖视图
retracting system 收起系统
trunnion 轴颈，枢轴，耳轴
retracting mechanism 收起机构
electric operated screw 电操纵螺杆
hydraulic actuating cylinder 液压致动作动
筒
civil airplane 民用飞机，民航飞机
linking device 连接机构
drop-test 着陆重量（起落架）落震试验，
冲击试验
wheel well door 起落架舱门，轮舱盖
supporting structure 支撑结构
friction 摩擦力
inertia 惯性
brake torque 刹车扭矩
air load 气动载荷
retraction 收回
extension 伸出，延伸
stalling speed 失速速度
approach position 进场着陆位置
cruising speed 巡航速度
load factor 载荷因数，过载，装载系数（有
效载荷与飞机起飞重量比）
yawing maneuver 偏航运动，方向动机
positive means 可靠的方法
safety switch 安全电门，保险开关
emergency system 应急系统
emergency means 应急方法
operational test 使用实验，工作实验
retracted position 收上位
extended position 放下位
landplane 陆上飞机
aural warning device 声响报警装置，声响
报警器
throttle 节流阀，节流油门，节气门
manual shutoff 手动关断
landing-gear control knob 起落架控制按钮
transport-airplane 运输机
tire 轮胎，轮箍
multiple landing gear 多轮起落架
compressed air chamber 压缩空气室
piston tube 活塞管
inner cylinder 内筒
outer cylinder 外筒
oil chamber 油室
power plant 动力装置，发动机
mount 支架座，安装，固定，装配
enclosed shelter 封闭的掩蔽所
multiengine airplane 多引擎飞机
National Aeronautics and Space Administration
(NSAS) 国家航空和宇航局
stream-lined structure 流线型结构
pod 吊舱，短舱，分离舱，可拆卸的货舱
pylon 外挂梁，吊架，挂架，支架
engine mount 发动机架
formed sheet metal 冷弯钣金件
welded steel tube 焊接钢管
forged steel 锻制钢
reciprocating (position) engine 活塞式发动
机
overhaul 大修
engine change 发动机更换
liquid line 液体管路
electric cable 电缆
control linkage 操纵线系
quick-disconnect joint 快速拆卸接头
quick engine change (QEC) 快速更换发动
机
package 组件，部件，成套设备
radial engine 星型发动机
opposed engine 对置式发动机
bushing 衬套，衬筒
vibration absorption 震动吸收
pad 沉淀，填料，垫片，底座台
cushion 垫子，软点，减震垫
restraining action 约束作用
manufacturer’s handbook 制造厂手册
mount bracket 固定托架，安装托架
dynamic suspension 非刚性支撑法，减震悬
挂，减震吊架
the center of gravity (CG) 重心
mount link 安装连杆
universal joint 万向接头
turbine engine 涡轮发动机
competent technician 胜任的技术人员，主
观的技术人员
fuel-burning heating 燃烧燃油的加热器
tail-pipe section 尾部排气管段，尾部喷管
段
fire wall 防火墙
shroud 外壳，保护罩
grommet 索环，眼圈，金属孔眼
closing rib 端部翼肋
strut mount fitting 吊架安装接头
engine rear mount support fitting 发动机后
部安装架支撑接头
disconnect point 分解点
universal block 万向接合件
cone bolt 锥体螺栓
support link 支撑连杆
thrust link 推力杆
atmosphere 大气，空气
lift 升力，举力
physical mixture 物理混合物
nitrogen 氮
oxygen 氧
weather-marking water vapor 造成气象现
象的水蒸气
constant 常数，恒定值
international civil Aeronautics organization
(ICAO) 国际民用航空组织
standard atmosphere 标准大气
pressure 压力，压强，大气压力
temperature 温度
density 密度

飞机常用单词英汉对照 6
flight test data 飞行试验数据
pounds per square inch (psi) 磅/平方英寸
Measurement 测量，度量
sea level 海平面
page pressure = psig 表压，计算压强，剩
余压强
tank 油箱
mercury 汞，水银
vacuum condition 真空状态
standard sea level condition 标准海平面状
态
absolute pressure 绝对压力，绝对压强
induction system 进气系统
piston engine 活塞式发动机
fuel-air charge 油-气进料，油-气填料
cylinder 气缸
manifold pressure gage 进气压力表
altimeter 高度表
scale 刻度盘，刻度表
barometric scale 气压表
millibar 毫巴
meteorologist 气象学家
weather map 天气图
constant pressure line 等压线
Fahrenheit scale 华氏温标
Celsius 摄氏温标
absolute temperature 绝对温度
centigrade scale 百分温标，摄氏温度
division 分刻度，间隔
increment 增量
degree 度
heat energy 热能
true reference 真实的基准
molecular activity 分子运动
Kelvin scale 绝对温标
freezing point of pure water 纯水冰点
boiling point of pure water 纯水沸点
state 状态
rankine scale 兰金温标
mass 质量
volume 体积，容积
gravity 重力
effect 作用，影响，效果，引起，实现，
达到
gravitational pull 万有引力
weightless 失重的
slug 斯勒格（质量单位）
cubic foot 立方英寸
acceleration 加速度
aerodynamic lift 气动升力
aerodynamic drag 气动阻力
determining factor 决定性因素
pressure altitude 压力高度
density altitude 密度高度
ambient air 周围大气，外界大气
the law of conservation of energy 能量守恒
定律
disposal 处理，收拾，整理
latitude 纬度，纵坐标，活动余地，范围
chemical energy 化学能
petroleum 石油产品
mechanical energy 机械能
relationship 关系
Newton’s laws of motion 牛顿运动定律
velocity 速度
reaction 反作用
autogiro 旋翼机，直升飞机，自动陀螺仪
Bemoulli’s principle 伯努力原理
kinetic energy 动能
potential energy 势能
position 位置
noncompressible fluid 不可压缩流体
restricted tube 截流管
flow rate 流量，流率
specific static pressure 单位静压比，比静压
restriction 限制，约束，限流
reference pressure 参考压强，基准压强
chart 图表
metric a. 公制（公斤，米，秒制）
mean sea level 平均海平面
specific weight 比重
speed of sound 音速
knot 节（测航速的单位）=1海里小时
Km = kilometer 千米，公里
Cm = centimeter 厘米
mile 英里
Lb = pound 磅
Hg = mercury 汞
venture tube 文氏管
subsonic aerodynamics 亚音速空气动力学
subsonic airfoil 亚音速翼型
supersonic airfoil 超音速翼型
transonic airfoil 跨音速翼型
realim 领域范围
leading edge 前缘
maximum thickness 最大厚度
trailing edge 后缘
asymmetrical airfoil 非对称翼型
symmetrical airfoil 对称翼型
obstruction 障碍物，障碍
chord line 弦线
streamline 流线，气流，流线的，流线形的，
把——制成流线型的
stagnation point 驻点，滞点
stall 失速，气流分离
deflection 偏转，偏折
downwash 下洗流，下洗
upwash 上洗流，上洗
impending stall 临近失速，即将时速
deflection 偏转，偏折
lift coefficient 升力系数
dynamic pressure 动压，速压
factor 系数，因数，要素
square feet 平方英寸
dimensionless number 无量纲数值
formula 公式，方程式
variable 变量
angle of attack 迎角，攻角，冲角
wind tunnel 风洞
curve 曲线，弧线
relative wind 相对来流
critical angle of attack 临界迎角
product 产品，生产，制造，乘积
feet per second 英尺/秒
airspeed 空速，气流速度
boundary layer 附面层
viscosity 粘性，粘滞度
friction drag 摩擦阻力
roughness 不平坦度，粗糙度
dirt 污物，弄脏，弄污
frost 霜，霜冻，下霜，粗糙的，无光泽的
local turbulence 尾部旋涡，尾部涡流
random flow pattern 紊乱的流线谱
laminar flow 层流
turbulent flow 紊流，湍流
mile per hour 英里/小时
kilometer per hour 公里/小时
component 部件，组件，分量，分力，成
份，部分
complex nature 复杂的性质，综合的性质
induced drag 诱导阻力
parasite drag 废阻力
characteristic curve 特性曲线
drag coefficient 阻力系数
lift/drag ratio (lift over drag ratio) 升阻比
separation 分离，分开
pressure center 压力中心
pitch force 俯仰力
aerodynamic center 空气动力中心，焦点
axis 轴，坐标轴
controls 操纵系统，操纵机构，舵面
longitudinal axis 纵轴
lateral axis 横轴，侧轴
vertical axis 立轴，竖轴，垂直轴
roll axis 滚转轴，纵轴
pitch axis 俯仰轴，横轴
yaw axis 偏航轴，立轴
aerodynamic stability 空气动力安定性
mechanical stability 机械安定性
stable aircraft 安定的飞机，具有安定性的
飞机
horizon 地平，地平线，地平仪
static stability 静安定性
dynamic stability 动安定性
equilibrium 平衡，平衡状态
steady flight 稳定飞行，定常飞行
nose-up attitude 抬头姿势，仰角
nose-down attitude 低头姿势，俯角
restorative force 恢复力，复原力
positive stability 正安定性
original position 原始位置，初始位置
valley 谷，凹地
opposite side 对边，相反的一边
negative stability 负安定性
oscillation 振动，摆动
neutral stability 中性安定面，无安定裕度
amplitude 振幅，幅度
longitudinal stability 纵向安定性
lateral stability 侧向安定面
directional stability 方向安定性，航向安定
性
pitch stability 俯仰安定性
hands-off flight 松杆飞行
straight and level flight 直线水平飞行
nose-down moment 低头力矩
balance 平衡，配重，衡量，比较
rotational force 旋转力，转动力
horizontal tail surface 水平尾翼
nose-up moment 抬头力矩
tendency 倾向，趋势
approach 接近，探讨，进近，进场，进场
着陆
control wheel 驾驶盘，操纵轮
control pressure 操纵杆（盘）上的力，操
纵系统的力
trim control 配平操纵
downdraft 下向通风，下洗流，下降气流
roll stability 滚转安全性
dihedral 两面角的，上反角
acute angle 锐角

brashman

十分感谢了

flyuanyuan

不管怎样，下载先

weiaiya

好东西看看

F6 ~9 @6 C# u+ w$ d2 u7 j: G

 

zhuce0553

好东西，down下来学习学习！

kevingi

我所在的学院就是航空工程学院啊

hotnikke

看看学习学习

leo

感谢帅哥！

adrlil

学习一下咯

zhongli_wei

多谢~~刚入门~~