曝光台 注意防骗
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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Hydraulic 动力，电源Powr 反推装置Reverser
共享Share 责任、负责液压传动的Dydrallically
有要求的On demond 起落架Landing
gear
前轮转弯Nose wheel
steering
副翼aileron 动力控制组件Power
control unit
升降舵Elevator
方向舵Rudder 飞行扰流板Flight
spoiler
刹车Brake
动力转换装
置
Driven transfer
unit
发动机传动泵Engine
driven pump
电动马达传
动泵
Electric motor
driven pump
关闭Shutoff 截流阀Shutoff
valve
油箱Reservoir
压力过滤器Pressure filter 消除Relief 润滑Lubricate
热交换器Exchanger 返回Return 后缘Trailing edge
前缘Leading edge 交替的Alternate 单独地individually
龙骨Keel beam 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. SystemA 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) SystemA 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) SystemA 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
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航空工程英语基础（中英文对照）(89)
