embody航空英语

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< /p>

，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

Fire detection

在?周围

Around

组件

Pack

4

专业资料

航空工程英语

Monitor

Component

Overheat

Occur

Panel

Wing

Lavatory

optional

feature

Available

Location

element

存在

警告

铃声

听觉

器件

灭火器

瓶

角落

轮子

放出

完成

天花板

Exist

Alarm

Bell

Aural

device

Extinguish

Bottle

Corner

wheel

discharge

Accomplish

Ceiling

泄漏

报警器

规定

在?之下

与?相对应

盆

擦手纸斜槽

Leak

horn

specify

beneath

Respond to

basin

Tower chute

监控

部件

过热

发生

面板

机翼

厕所

可选的

特征

可用的

位置

元件

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

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。

< br>

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

wheel well

and also in the flight deck. The APU fire bottle

is

located

behind the aft pressure bulkhead and is discharged either from the flight deck or P28 panel.

APU

探测器只感应火警信号。传感器的监控由

M279

完 成。指示出现在

P28

板在主轮舱和

F LIGHT DECK

。

APU

灭火 瓶后压力

隔板上，并通过

P28

板或< /p>

FLIGH DECK

释放。

4.

Wheel

well

fire

detection

is

provided

by

detector

elements

mounted

on

the

wheel

well

ceiling.

The

detectors

provide input to the M237 module located in the E/E bay. Indications occur on the P7 and P8 panels and an alarm

bell is provided by the M315 module.

轮舱火警探测由安装在轮舱天花板上的探测元件来提供。探测器提供信 号给安装在电子设备舱的

M237

组件。指示信号出现

在

P7

和

P8

板上，警告铃声由

M315

组件提供。

5.

The wing and body overheat detection system exists to monitor the pneumatic system for leaks . the

detection

system

is

divided

into

a

left

and

right

system.

The

detectors

provide

input

to

the

M237

module.

Overheat

indication occurs on the P5 and P7 panels.

机翼和机身过热探测系统监控增 压系统有无渗漏。探测系统分为左右两部分。探测器提供信号给

M237

组件。过热指示信号

出现在

P5

和

P7

板上。

6.

The lavatory smoke detector is located in each lavatory, the detector will provide a warning horn and

indication

at

a specified

smoke level

.located

in

each lavatory,

beneath the

wash

basin,

is

a fire extinguisher

bottle which responds to high temperature in the tower chute.

厕所 烟雾探测器安装在每个厕所里，探测器将在规定的烟雾层度发出警告信号。灭火瓶安装在每个厕所，洗手池下面， 可

以对擦手纸斜槽里的高温情况作出响应。

LESSON 6 OXYGEN SYSTEM

氧气系统

一、单词

氧气

Oxygen

要求、命令

Acquire

单独的

independent

5

专业资料

航空工程英语

Install

Diluter

Attandent

Mask

Gage

Emergence

Actuator

automatically

气态的

要求

气缸

切断

即使

锁定

机构

人工地

Gaseous

Demand

Cylinder

Shut off

称为

化学上

旅客服务设备

数量

designate

Chemically

Passengers service unit

Quantity

Vent

Release

activate

安装

稀释器

服务员

面罩

压强计

紧急情况

作动筒

自动地

In a event of

排出

Latch

Mechanism

manually

释放

开动，启动

二、

TEXT

1.

the purpose

of

the oxygen

system

is

to

provide oxygen

for the

flight

crew

and

passengers

when

required.

Two independent oxygen system are installed in B737. the flight crew oxygen system is a high pressure gaseous

system for flight crew use only, this type of system is designated a

“

diluter demand

”

system . The passenger

oxygen system is a chemically-generated oxygen system for use by passengers and cabin attendants. This type of

system is designated a

“

continuous flow

”

system.

氧气系 统用来为机组及旅客提供氧气。

B737

上安装有两套氧气系统 。机组氧气系统是一个仅供机组使用的高压气态系统，

这种系统被称为

< br>“稀释要求”

系统。

旅客氧气系统是一供旅客及乘务员使 用个化学制氧系统。

这种系统被称为

“

continuous

flow

”系统。

2.

The

flight

crew

oxygen

system

consists

of

an

oxygen

cylinder.

Valves,

indicating

components,

distribution

tubing

and

oxygen

mask/regulator.

The

crew

oxygen

system

components

are

located

in

the

forward

cargo

compartment

and in the flight compartment.

机组氧气系统包括一个氧气瓶，阀门，指示 组件，分配管道及氧气面罩

/

调节器。机组氧气系统组件安装在 前客舱和驾驶舱

内。

3.

Oxygen

flows

through

the

pressure

reducing

regulator

and

shut

off

valve

to

the

masks.

Quantity

(pressure)

indication is provided by a gage in the flight compartment. In the event of an overpressure, the cylinder is

vented to ambient through the overboard discharge. The cylinder is serviced after removal from the aircraft.

氧气通过减压调节器和关断活门流向氧气面罩。流量指示由驾驶 舱内的压强计指示。一旦过压，气瓶将通过顶部释放开关

进行释压。气瓶应从飞机上取下 进行勤务。

4.

The passenger oxygen system provides an emergency oxygen supply to the passengers and attendants, this

system

consists

of

passenger

sevice

units,

control

and

indication.

This

service

units

contain

the

mask

box,

door

latch release actuator, latching mechanism, chemical oxygen generator and oxygen mask.

旅客氧气系统为旅客及乘务员提供应急氧气，系统包括旅客服务设备，控制 及指示器。这个服务设备包括氧气面罩盒、门

锁释放作动筒，锁定机械装置、氧气发生器 及氧气面罩。

5.

The passenger oxygen system can be activated automatically by high cabin altitude (low cabin pressure)

or manually from the flight compartment.

旅客氧气系统能够被较高的客舱高 度自动启动，也能在驾驶舱人工启动。

LESSON 7 ICE AND RAIN PROTECTION

防冰、防雨

一、单词

雨

为?而提供

叶片

视线

迎角叶片

Rain

保护

Protect

Wiper

Toilet

Pitot static

Mast

Strengthen

coating

Formatting

Faulty

帮助

Aid

Repellent

Drain

Probe

Buildup

Fog

expose

Freeze

Loss

6

Is provided for

雨刷

Vane

Vision

Alpha vane

Impact

conductive

Airstream

Cause

卫生间

皮托静压

防雨剂

排放

探头

堆积

雾

暴露

结冰

损失

支柱管

强度

涂层

形成

出故障的

碰撞

导电的

气流

原因

专业资料

航空工程英语

Sink

fitting

嵌入

与?结合在一起

Embed

垫圈

gasket

槽

装置

Are integrated with

二、

TEXT

1.

the ice and rain protection system protects the airplane and aids the flight crew when operating under

ice and rain conditions. Ice and rain protection is provided for:

1.

wing leading edge slats outboard of each engine.

2.

Flight compartment windows (heat, wiper, rain repellent).

3.

Pitot static and temperature probes.

4.

Alpha vanes.

5.

Toilet drains.

防冰、防雨系统用于保护飞 机及帮助机组在雨雪天气下操作飞机。此系统为下列部件提供保护：

1.

发动机外前缘缝翼；

2.

驾驶舱玻璃窗（加热、雨刷、防雨剂）；

3.

皮托静压管及总温探头；

4.

迎角叶片；

5.

厕所排水。

2.

Wing leading slats use hot air from the pneumatic system. Flight compartment windows are electrically

heated.

The

wipers

and

rain

repellent

are

used

for

providing

clear

vision.

The

pitot

static

probes,

alpha

vanes,

drain masts, and toilet drains use electric heaters.

前缘缝翼用增压系统的热引气加温。驾驶舱窗口 用电加温。雨刷和防雨剂用来提供清晰视野。皮托静压探头、迎角叶片、

排水管及厕所排 水都是用电加温。

3.

The wing anti-ice system prevents ice buildup on the wing leading edge slats, this system consists of

air supply ducts, valves, terminal switches, controls and indications.

防冰系统可防止冰在缝翼前缘堆积，此系统包括供气管道、 活门、终端开关、控制及指示器。

4.

The window heat system improves the impact strength of the flight compartment windows and prevents fog

and

ice-buildup,

this

system

consists

of

conductive

coating

in

the

window

structure,

heat

control

units,

controls

and indications.

窗口加热系统提高了驾驶舱窗口的撞击强度并防止雾和冰的堆积，此系统包括窗口结构上的导 电涂层、加热控制组件、控

制及指示器。

5.

The pitot static probes, temperature probe and alpha vanes provide air data information to the various

using system, they are located on the left and right sides of the forward fuselage. Since all the probes and

vanes

are

exposed

to

the

airstream,

internal heating is

provided to

prevent

ice formation. Freezing

could

cause

faulty inputs or possible loss of all data.

皮托静压探头、总温探头和迎角叶片用来提供大气数据信息给不同的应用系 统，他们位于前机身在右侧。因为所有的探头

及叶片都暴露在气流里，需要加热以防止结 冰。结冰可以导致所有数据的丢失或输入错误信息。

6.

The

drain

anti-icing system

prevents ice buildup on the

drains from

the

toilets and

lavatory sinks.

The

aft toilet drain heater is embedded in gasket between the drain tube and the drain outlet fitting. The lavatory

sink

drain

heater

are

integrated

with

the

drain

mast.

The

power

supply

for

the

toilet

drain

heaters

is

115

volts

ac and for the lavatory sink drain is 115 volts ac or 28 volts ac.

排水防冰系统防止在卫生间及其水池的排水装置上积冰。后厕所加热器用垫片嵌 入在排水管道与外流排水装置之间。厕所

洗手池加热器与排水竖管连在一起。为厕所排水 管加热用的是

115V

直流电，为厕所洗手池加热用的是

115V

直流或

28V

直

流电。

LESSON 8 THE POTABLE WATER SYSTEM

饮用水系统

一、单词

饮用水

油箱

支架

园筒形的

外泄管道

簧片

磁铁

关联的

Potable water

tank

bracket

Cylindrical

Overflow line

Reed

Magnet

associate

浪废

数量

3.785

公升

覆盖层

水量传感器

二极管

包围

相应的

Waste

Quantity

U.S. gallon

blanket

由?组成

制作

4.546

公升

充注管道

Be composed of

Construct

Imperial gallon

Fill line

Capacity

Float

Label

emptiness

Quantity transmitter

容积

Diode

Surround

corresponding

浮子

标明

空

7

专业资料

航空工程英语

二、

TEXT

1.

the potable water system supplies potable water to the galleys and lavatories. The waste system is for

storing and removing waste from the toilets. The water and waste system is composed of independent but related

systems.

饮用水系统为机上厨房及卫生间提供饮用水。水系统是用于贮水及排放卫生间废水饮用水及废水系统是 由相互独立并相互

关联的系统。

2.

The potable water system consists of a water tank, quantity indication, pressurization components, and

distribution

tubing.

The

water

tank

and

pressurization

components

are

located

aft

of

the

aft

cargo

compartment.

The quantity indication is in the aft section of the passenger cabin.

饮用水系统由一个水箱、流量指示器、增压组件及分配管道组成。水箱及 增压组件位于后货舱的后面，流里指示器位于客

舱后部。

3.

The water tank stores potable water for use by the passengers and tank is constructed of

fiberglass and attached by struts and mounting brackets to the airplane structure. The 30 U.S. gallon tank is

cylindrical. It is protected from freezing by a 3-pieces fiberglass blanket. On the upper section of the tank

are connections for the air pressure line, fill line, overflow line, supply line, and a quantity transmitter,

the fill and overflow valve is used to fill the tank to the capacity determined by a standpipe, this valve is

operated a handle. A drain valve is located on the bottom of the tank.

水箱用以贮存供旅客及机组使用

的饮 用水。水箱由玻璃纤维制成，并固定在飞机桁架上。

30

加仑的 圆柱形水箱。用三个玻

璃纤维垫片防止结冰。水箱上部连结着一个空气连接管道，充注管 道，过流管道，供水管道及一个流量传感器，注水及过

流阀

此阀门被一个手柄控制。一个排放活门被安装在水箱底部。

4.

The quantity indication shows the amount of water in the tank. The quantity transmitter consists of 10

reed

switches

and

3

inside

a

tube.

A

float

with

3

magnets

surrounds

the

tube.

In

addition,

the

indicator

consists

of 5 lights the tank determines the position of the float. The magnets on the float close the associated reed

switches.

Using

the

push

button

on

the

quantity

indicator,

allows

the

corresponding

quantity

lights

to

illuminate

if the tank is emptiness, the E light is illuminated, if the tank is full, all lights are illuminated.

流量 指示器显示水箱水量。流量传感器包括

10

个簧片、

个管道。

1

个浮子和< /p>

3

个磁铁包围着管道。另外，指示器包括

5

个水位指示灯。浮子上的磁铁与弹簧开关相关联。按下水量指示器上的按钮，当水箱空 了时，相关的指示灯

E

灯就会亮，

若水 箱是满的，所有的灯都会亮。

LESSON 9 FLIGHT DECK LIGHTING

飞行面板照明

一、单词

照明

最佳的

主要的

总体的

遮光板

标记

亮度

AFDS

Lighting

Optimum

Major

Integral

Glareshield

Identify

Brightness

Autopilot flight director

system

Space

Thrust lever quadrant

照明

效能

可变的

机长

发荧光的

顺时针方向的

白灼灯

暗淡

Illumination

Performance

Available

Captain

Fluorescent

Clockwise

Incandescent

Dim

舒适

操作

强度

副驾驶

泛光灯

增长

自动驾驶仪

试验

Comfort

Handing

Strength

First office

Floodlight

Increase

Autopilot

Test

空间

推力手柄盘

控制台

电路跳开关

Control stand

与?类似

Similar to

Circuit breaker

二、

TEXT

1.

the

purpose

of

the

lighting

system

is

to

provide

the

necessary

illumination

for

passenger

comfort,

optimum

flight crew work performance, service and cargo handling, and provide for lighting undremergency conditions.

灯光系统的作用是为旅客舒适、极佳的机组工作效能、服务及货舱操作，及在应急条件下提供灯 光。

2.

The major systems are :flight compartment lights, passenger compartment lights, exterior lights and

emergency lights. In this lesson, we will introduce the flight deck lighting only.

主系统包括：驾驶舱灯光、客舱灯光、外部灯光及应急 灯光。本文中，我们将只讲驾驶舱灯光。

3.

Variable

intensity

controls

for

the

integral

instrument

and

main

instrument

panel

lights

are

identified

as

PANEL

and

located

on

the

lower

portion

of

the

captain’s

and

first

officer’s

panels.

The

captain’s

variable

intensity

PANEL

switch controls

these

lights on the captain’s main

panel, the

center

panel

and

the glareshied.

The first officer’s PANEL switch controls these lights on the first officer’s panel.

8

专业资料

航空工程英语

亮度调节面板作为调节亮度的整体及主要手，段位于机长及副驾面板的下方。机长的亮度调节面板开关控制着 机长面板、

中央面板及遮光板上的灯光。副驾驶面板开关控制副驾驶面板上的灯光。

4.

White fluorescent floodlights are positioned under the glareshield to direct background lighting onto

the main panels. One variable

–

intensity switch, which controls these lights, is on the lower portion of the

captain’s main panel and identified as ACKGROUND, movement of this switch in a clockwise direction increases

the brightness of the fluorescent lights.

白 色的荧光屏泛光灯位于遮光板下方。一个亮度调节开关控制着这些灯，它是位于机长主面板下方标识为