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