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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 11
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Subdivide Tank Temporary Fit Fastener 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 交输 容量 Storage Vent Fueling tight Compound Joint Check valve Fueling station Completely Transfer 加燃油 Fueling 细分 油箱 暂时的 装配 紧固件 通气均压油箱 Vent surge tank 金属和金属 密封剂 翼肋 增压泵 填充 另一方面 浮子 Metal to metal Sealing compound Rib Boost pump Fill Alternately Float Defueling Feed Usable Stick Liquid crystal display Unacceptable 缓冲挡板 Baffer 离开 部份的 入口 过满 利用 各自的 重量 芯片 Away off Partially port Overfill Utilize Weight Chip Prevent M from doing 放油 Boost pump Crossfeed Capacitance 供油 可使用的 杆 液晶显示 微电子计算机 Microcomputer 电阻电流 Resistive current 错误 带 Error tape 泄漏 Leakage 不能接受的 代码 高度 Code Height 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。
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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
1.
单词 液压的 共享 有要求的 副翼 Hydraulic Share On demond aileron 动力，电源 责任、负责 起落架 Powr Landing gear 反推装置 液压传动的 前轮转弯 升降舵 Reverser Dydrallically Nose wheel steering Elevator 动力控制组件 Power control unit 飞行扰流板 方向舵 动力转换装置 关闭 压力过滤器 热交换器 前缘 龙骨 Rudder Flight spoiler 刹车 电动马达传动泵 油箱 润滑 后缘 单独地 Brake Electric motor driven pump Reservoir Lubricate Trailing edge individually Driven transfer 发动机传动泵 Engine driven unit pump Shutoff 截流阀 Shutoff valve Relief Return Alternate Pressure filter 消除 Exchanger Leading edge Keel beam 返回 交替的 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
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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
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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 圆筒 牵引 牵引杆 氮气 转弯力矩 Main gear Antiskid Disarm Depressurize Respective Serve as Malfunction Inpact Taxi Assure Cylinder tow tow bar Nitrogen Turning moment 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 轴颈销钉 环 碰撞 折迭 手轮 Nose gear Inoperative Actuate Solenoid Transit Configuration Shock strut Shock Fairing Drag brace Trunnion pin Lug Bump Fold Handwheel 梁 自动刹车 借助于? 限制 一致 在?情况下 缓冲 振动 机构 扭力臂 稳定性 横向螺栓 注入 环 脚蹬 Spar Autobrake By means of Restrict Agree In case of Absorb Vibration Mechanism Torsion link 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
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