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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.交輸活門允許燃油從一
個油箱同時給兩臺發動機供油。為APU 供油主要是用1 號油箱，
但也可從任一油箱供油。
(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.
油量指示組件測量油箱中油的重量。一般使用兩種油量指示，一
個是容量指示，一種是人工用棒測量。
(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.
數字油量指示器顯示每個油箱中的油量。每個指示器包括一個單
芯片微型計算機系統和一個數字式液晶顯示器。微型電子計算機
測量油箱中的容量和電阻電流。它監控著泄漏電流，當泄漏達到
一定程度時，會指示一個0 到10 的代碼，以幫助進行系統排故。
(9) The measuring sticks are graduated tape which can be pulled down for
reading of fuel height.
測量棒是一個刻度尺，它能夠放進油箱來讀出燃油深度。
LESSON 13 HYDRAULIC POWER
一、單詞
液壓的Hydraulic 動力，電源Powr 反推裝置Reverser
共享Share 責任、負責液壓傳動的Dydrallically
有要求的On demond 起落架Landing
gear
前輪轉彎Nose wheel
steering
副翼aileron 動力控制組件Power
control unit
升降舵Elevator
方向舵Rudder 飛行擾流板Flight
spoiler
剎車Brake
動力轉換裝
置
Driven transfer
unit
發動機傳動泵Engine
driven pump
電動馬達傳
動泵
Electric motor
driven pump
關閉Shutoff 截流閥Shutoff
valve
油箱Reservoir
壓力過濾器Pressure filter 消除Relief 潤滑Lubricate
熱交換器Exchanger 返回Return 后緣Trailing edge
前緣Leading edge 交替的Alternate 單獨地individually
龍骨Keel beam 帶保護罩的開關Guarded
switch
節
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.
三個分隔獨立的液壓系統用以為飛行控制、起落架和反推裝置提供動
力。A 系統和B 系統在飛行中為全時操作系統，共同負責對所有受液
壓動力控制的組件進行控制。備用系統只在需要時工作。
(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 系統為下列系統提供動力：
起落架
前輪轉彎系統
左反推裝置
副翼—動力控制組件及自動駕駛作動筒
升降舵—動力控制組件及自動駕駛作動筒
升降舵FEEL
方向舵
內側飛行擾流板3#及6#
地面擾流板
備用剎車
動力傳輸組件
(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 系統壓力由一個發動機驅動泵和一個電動免馬達驅動泵提供。一個
28v 直流免達操作位于油箱及發動機驅動泵之間傳送管內的截流閥，
正常情況下，它是打開的。當火警手柄拉上時，閥門關閉并停止壓力
流向發動機。
(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.
系統正常構造是通過操作泵輸出3000PSI 的壓力，通過壓力組件給用
戶系統。壓力組件包括壓力油濾，低壓開關，單向活門和一個壓力釋
放活門。
(5) Hydraulic system B provides fluid under pressure of 3000 psi to portions
　
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