航空工程英语基础

ESSENTIAL（基础） ENGLISH OF AERONAUTICAL ENGINEERING

航 空 工 程 英 语 基 础

LESSON 1 THE B737 FUSELAGE机体 一、生词 飞机 起落架 分为 玻璃纤维 铰链 进口 电子设备舱 货舱 空间 Airplane Landing gear Divide into Fiberglass Hinge Entry Electronic equipment bay Cargo Space unit 排出 伸长 增强 结构 Exhaust stretch Strengthen structure 设计 延伸 相对于 修改 逃逸 燃油箱 power 水平安定面 Escape Fule bank Horizontal stabilizer Design Extension Relaviate to revise 和?一样 脊鳍 滑轨 The same as Dorsal fin Skid 舱口 终止 桁架 半硬壳式 动力装置 包括 蜂窝状物 压力密封隔板 机上厨房 检修口 Galley Access door 登机梯 旅客舱 Semi-monocoque 机身 Power plant Contain Honeycomb Bulkhead 支柱 天线 整流罩 驾驶舱 Fuselage Strut Antenna Fairing flight compartment Airstair Passenger cabin Hatch Terminate Truss 辅助动力装置 Auxiliary 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 环境 发动机引气 接头 防冰 饮用水 在?之内 满足 图形 管道 管理、调整 Purpose Environment Engine bleed Connector Anti-icing Potable water Within Meet Figure Duct govern 压缩空气 阶段，相位 外部的 整流罩 也，此外 液压的 正常的 需要，要求 绝缘 结合、连接 适当的 compressure Air 压缩空气 Phase External Cowl Also Hydraulic Normal Need Isolation Join appropriate 得到 车 热的 提供 启动器 取代 上部、顶部 活门 交叉、跨接 pneumatic Obtain Cart Thermal provide Starter Substitute Top Valve crossover 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 加热 引出，放出 Air conditioning heat Bled 环境 冷却 总管道 Ambient Cool Manifold 机组 增压 分离 Crew pressurization Seprate 独立的 暖，热 涡轮冷却器 共同的 膨胀V 零下 indenpendent Worm Air cycle machine Common Expand Sub-zero 冷却组件 减少 整的 轴 膨胀N 分配 混合 头顶上 防护罩 再分配 Cooling pack Reduce Integral Shaft Expansion Distribute Mix Overhead Shroud Redistribute 调节，管理 期望 包括 离开 下降 此外 室、容器 竖管 过滤器 二等分 regulate Desire Consist of Leave Drop In addition Chamber Raise Filter halve 配平空气管道 Trim air line 加上，增加 收集器 排出口 Add Collector discharge 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 外流阀 目的地 曲线 巡航 爬升 环境 Pack Outflow valve destination Curve Curise Ascend ambient 控制 保持 安全的 对时间的 虚线 下降 减小 Control Maintain Safe Against time Dotted line Descent decrease \\座舱高度 Cabin altitude 尽可能的? As as possible 舒适的 起飞 实线 近 变化率 Comfortable Takeoff Solid line Near rate 确定、决定 Determine 磅/英寸 描绘 制度 相等的 向机舱外 Psi=pound square inch Depict Sytstem identical outbroud 大气 per 参照? Atmosphere By referring 例子 图表 称之为? 毫巴 排出 Example Chart Is referred to as Millibar exhaust 与?的关系曲线 versus 水银 施加 mercury exert 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 监控 部件 过热 发生 面板 机翼 厕所 可选的 Fire detection Monitor Component Overheat Occur Panel Wing Lavatory optional 在?周围 存在 警告 铃声 听觉 器件 灭火器 瓶 角落 Around Exist Alarm Bell Aural device Extinguish Bottle Corner 组件 泄漏 报警器 规定 在?之下 Pack Leak horn specify beneath 与?相对应 Respond to 盆 basin 擦手纸斜槽 Tower chute 特征 可用的 位置 元件 feature Available Location element 轮子 放出 完成 天花板 wheel discharge Accomplish 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 安装 稀释器 服务员 面罩 压强计 紧急情况 作动筒 自动地 Oxygen Install Diluter Attandent Mask Gage Emergence Actuator automatically 要求、命令 气态的 要求 气缸 切断 即使 锁定 机构 人工地 Acquire Gaseous Demand Cylinder Shut off In a event of Latch Mechanism manually 单独的 称为 化学上 旅客服务设备 数量 排出 释放 independent designate Chemically Passengers service unit Quantity Vent Release 开动，启动 activate 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 雨刷 卫生间 皮托静压 支柱管 强度 涂层 Protect Wiper Toilet Pitot static Mast Strengthen coating 帮助 防雨剂 排放 探头 堆积 雾 暴露 Aid Repellent Drain Probe Buildup Fog expose 为?而提供 Is provided for 叶片 视线 迎角叶片 碰撞 导电的 Vane Vision Alpha vane Impact conductive 气流 原因 槽 装置 Airstream Cause Sink fitting 形成 出故障的 嵌入 Formatting Faulty Embed with 结冰 损失 垫圈 Freeze Loss gasket 与?结合在一起 Are integrated

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 油箱 支架 园筒形的 外泄管道 簧片 磁铁 关联的 Potable water tank bracket Cylindrical Overflow line Reed Magnet associate 浪废 数量 3.785公升 覆盖层 水量传感器 二极管 包围 相应的 Waste Quantity U.S. gallon blanket Quantity transmitter Diode Surround corresponding 浮子 标明 空 Float Label emptiness 由?组成 制作 4.546公升 充注管道 容积 Be composed of Construct Imperial gallon Fill line Capacity 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 最佳的 主要的 总体的 遮光板 标记 亮度 AFDS Lighting Optimum Major Integral Glareshield Identify Brightness Autopilot 照明 效能 可变的 机长 发荧光的 顺时针方向的 白灼灯 flight 暗淡 Illumination Performance Available Captain Fluorescent Clockwise Incandescent Dim 舒适 操作 强度 副驾驶 泛光灯 增长 自动驾驶仪 试验 Test Comfort Handing Strength First office Floodlight Increase Autopilot director system 空间 Space quadrant 控制台 lever 电路跳开关 Control stand Circuit breaker 与?类似 Similar to 推力手柄盘 Thrust 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 排故 装配 大气数据 数字式 温度 飞行管理计算机 适配器 信号 综合飞行系Troubleshooting Assembly Air data Digital Temperature Flight management computer Adapter Signal 发动机 选择呼叫系统 到达 简化 支架 计算机 失速 控制器 惯性基准系统 reach Simplify Rack Computer Stall Controller Inertial reference system Engine Selective calling system Integrated flight 旅客广播 unit 遥控电子装置 空中交通管制 静变流机 整流器 缝翼 失火 继电器 Static inverter Rectifier Slat Fire relay Remote equipment unit Air traffic control 数字飞行数据采集装置 电瓶充电器 减速板 电门 探测器 甚高频 Very frequency Digital flight 测距机 Distance measuring equipment Battery charge Speed break Switch detector 变压器 襟翼 过热 导航 transformer Flap Overheat navigation data acquisition hight 通信 Communication Passenger address 统附件组件 system accessory 振动 偏航阻尼器 放大器 Amplifier Vibration Yaw damper 修改 可移动的 搁板 自动油门 警告 设置 模拟量 modification Removable Shelf Auto throttle Warning Location Analog 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 发电机 Electrical power Generator 不同的 地面保障设备 Various Ground support equipment 驱动 分布 额定容量 换向器 完整的 磁场 调节器 定子 关键的 备份的 Drive Distribute Is rated at Commutator Complete Field Regulator Stator critical backup 插座 产生 千伏安 电刷 整流器 转 子 引出 恒速传动装置 缺少 Receptacle Produce Kilovolt ampere Brush Rectifier Armature Develop Constant speed drive absence 变压器 励磁器 磁极 装有 送入 Exciter Pole Is supplied with Fed into gearbox transformer 转换 主要是 汇流条 Convertion Primarily Slip-ring 电瓶 交流 battery Alternating current 附件齿轮箱 Accessory 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 细分 油箱 暂时的 装配 紧固件 缓冲挡板 离开 部份的 入口 过满 利用 Fuel Subdivide Tank Temporary Fit Fastener Baffer Away off Partially port Overfill Utilize 存贮 贮藏 通气装置 燃油密封的 化合剂 接口 单向活门 加油站 完全地 转移 防止?做? 用泵抽 Store Storage Vent Fueling tight Compound Joint Check valve Fueling station Completely Transfer Prevent from doing Boost pump 供油 Feed 运送 加燃油 通气均压油箱 金属和金属 Metal to metal 密封剂 翼肋 增压泵 填充 另一方面 浮子 M 放油 Sealing compound Rib Boost pump Fill Alternately Float Defueling Deliver Fueling Vent surge tank

各自的 重量 芯片 电阻电流 错误 带 Weight Chip Resistive current Error tape 交输 容量 微电子计算机 泄漏 代码 高度 Crossfeed Capacitance 可使用的 杆 Usable Stick Liquid display crystal Microcomputer 液晶显示 Leakage Code Height 不能接受的 Unacceptable 刻度 Graduate 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 共享 有要求的 副翼 方向舵 动力转换装置 关闭 Hydraulic Share On demond aileron Rudder Driven unit Shutoff 截流阀 消除 返回 交替的 动力，电源 责任、负责 起落架 动力控制组件 飞行扰流板 transfer 发动机传动泵 Powr Landing gear Power control unit Flight spoiler Engine Shutoff valve 压力过滤器 Pressure filter 热交换器 前缘 龙骨 Exchanger Leading edge Keel beam Relief Return Alternate switch 润滑 后缘 单独地 节 Lubricate Trailing edge individually 电动马达传油箱 Electric Reservoir motor driven pump 动泵 driven pump 刹车 Brake 升降舵 反推装置 液压传动的 前轮转弯 Reverser Dydrallically Nose steering Elevator wheel

带保护罩的开关 Guarded 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 防滑的 解除预位 减压 相应的 充当 故障 碰撞 滑行 保证 Main gear Antiskid Disarm Depressurize Respective Serve as Malfunction Inpact Taxi Assure 前起落架 无效的 使动作 电磁线圈 移动，变换 形态 减震支柱 冲撞 整流罩 阻力杆 Nose gear Inoperative Actuate Solenoid Transit 梁 自动刹车 借助于? 限制 一致 Spar Autobrake By means of Restrict Agree Configuration 在?情况下 In case of Shock strut Shock Fairing Drag brace 缓冲 振动 机构 扭力臂 Absorb Vibration Mechanism Torsion link 圆筒 牵引 牵引杆 氮气 转弯力矩 Cylinder tow tow bar Nitrogen Turning moment 轴颈销钉 环 碰撞 折迭 手轮 Trunnion pin Lug Bump Fold Handwheel 稳定性 横向螺栓 注入 环 脚蹬 Stability crossbolt Charge collar 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 水平的 轴 起飞 地面 主要的 驾驶盘 导致 角度 建立 Flight Lateral Axes Takeoff Ground Primary Control wheel Cause Angular Establish 操纵 纵向的 增加 着陆 被分成 次要的 配平 转 动 量； 值 大小、尺寸 全部的 保持 角度 驾驶舱 反馈 转动鼓轮 Control longitudinal Increase Landing into Secondary Trim Rotate Amount Magnitude Total remain Angle Flight deck Feedback bus Drum 方法、手段 位置 姿.态 操纵面 达到 对?起作用 稳定的 降低 操纵台 信号 驾驶盘操纵 考虑 反向力 驾驶杆 扇形盘 Means Position Attitude Control surface Reach Act on Stable Lose Control stand Signal Control steering 换能器 升力中心 横滚 扭力管 transducer Center lift Roll Torque tube 副翼操纵力限制 Aileron force limiter 重心 俯仰（率） 调整片 Center gravity Pitch rate Tab Control column quadrant Counter force Consider wheel 机动动作 垂直的 升力 阻力 maneuver Vertical Lift Drag Group Are divided 集团 再成流线型 Refair 平衡 坡度 命令 传感器 Balance bank Command Sensor 自动驾驶仪 Autopilot 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: ? 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. ? 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. ? 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： ? 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。 ? 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。 ? 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

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