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
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
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
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
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
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
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
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
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
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 c enter 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 mo unted 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
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：
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。