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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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航空工程英语

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 Flight Lateral Axes Takeoff 操纵 纵向的 增加 着陆 Control longitudinal Increase Landing 机动动作 垂直的 升力 阻力 maneuver Vertical Lift Drag 16