英语翻译A.The outer wing consists of the structural units and associated components and members which support the airplane in flight.These include spars,skins,ribs,stringers,etc.,and integral fuel tank structures.B.The front and rear spars on the

英语翻译A.The outer wing consists of the structural units and associated components and members which support the airplane in flight.These include spars,skins,ribs,stringers,etc.,and integral fuel tank structures.B.The front and rear spars on the
英语翻译
A.The outer wing consists of the structural units and associated components and members which support the
airplane in flight.These include spars,skins,ribs,stringers,etc.,and integral fuel tank structures.
B.The front and rear spars on the left and right wing boxes are primary structural components of the main wing
frame.They extend from the wing root rib to the wingtip.The spars consist of vertical sheet metal webs tapering
down in depth towards the wingtips and provided with chords along the upper and lower edges.Vertical stiffeners
are attached to the vertical faces of the spare (Fig.1).
(1) The deployment of flight control surfaces exposes the spars to the ground and near ground air contaminants,
thrust reverser soot,runway dirt and debris and inclement weather elements all of which contribute to corrosion.
(2) The spar chords are found to be particularly susceptible to corrosion originating most likely at the fasteners
common to the chord and web.
(3) Stress corrosion cracks,have been reported on the front and rear spar upper chords (Fig.1,Section A-A).On
airplanes through line number 310 inspection requirements and repair instructions for cracked chords are described
in SB 57-1067 and SB 57-1081.Production changes at cum line number 311 include material change of the upper and
lower chords of the rear spar and the upper chord of the front spar from 7178-T6 to 7075-T73.There is no change
to the front spar lower chord.
NOTE:The preventive modification in SB 57-1081 R3 was changed for SB 57-1081 R4 due to recurrence of stress
corrosion cracking in airplanes modified by SB 57-1081 R3.This has been attributed to improper shimming and
fitting of the angles installed for preventive modification.Airplanes modified by SB 57-1081 prior to Revision 4
must be reinspected per Revision 4 (or later) and may incorporate preventive modifications of Revision 4 (or
later) to improve corrosion protection.An Airworthiness Directive has been issued on this subject.Revision 3 of
SB 737-57-1067 came out to add more recommended repair on wing spar chord for aging 737 airplanes.This service
bulletin supersedes SB 57-1046 and SB 57-1062.
(4) Stress corrosion cracks have been reported on the Krueger flap actuator support fittings mounted on the front
spars.Inspection procedures for checks in the fittings are outlined in SB 57-1129 for airplanes through line
number 813.Material changes were made to steel for airplanes line number 814 and on.

英语翻译A.The outer wing consists of the structural units and associated components and members which support the airplane in flight.These include spars,skins,ribs,stringers,etc.,and integral fuel tank structures.B.The front and rear spars on the
A．外段机翼由结构单元和相关的可以支持飞机飞行的部件构成.这些包括梁,蒙皮,肋,纵梁等,还有整体油箱结构.
B．前后的梁在左右机翼盒子上的是主要的机翼框架的初级结构原件,他们从机翼根部延展到翼尖,这个梁是有垂直的薄片金属腹板构成,一直延伸到翼尖,有上线边缘的弦所提供,垂直的加劲钢被系在梁的垂直的表面（图1）
（1）飞行面的控制将梁暴露在地面和近地空气污染物、反推力装置烟灰、跑道灰尘碎片和恶劣的气象因素等导致腐蚀.
（2）梁特别容易从扣件开始腐蚀以至于缘条和腹板.
（3）报告称,应力腐蚀裂纹会产生在前后梁上缘条（图1,A-A段）.行号到310的飞机,裂纹的检查和修复指南SB 57-1067和SB 57-1081叙述了.产品升级从行号为311的飞机开始,包括后梁的上下缘条和前梁的上缘条的材料从7178-T6变化到7075-T73.前梁的下缘条没有改变.
注：预防限制方案从SB 57-1081 R3变为SB 57-1081 R4以减少SB 57-1081 R3情况下的应力腐蚀裂纹.这归因于不适当的填隙法和设备的安装角度.飞机的改良从SB 57-1081到Revision 4必须重新考察通过Revision 4（或更晚的）并且要包含Revision 4（或更晚的）的预防和修改以太高防腐蚀能力.就这个问题已经颁布了一条适航性指令.SB 737-57-1067的Revision 3更多地被建议在737成熟的飞机中修复翼梁缘条.这项服务公告取代了SB 57-1046和SB 57-1062.
（4）有报告称,应力腐蚀裂纹发生在安装在前梁上的克鲁格襟翼驱动支承组件.组件上裂纹的检查程序列在SB 57-1129用于行号至813的飞机上.行号为814及以后的飞机已经做好材料升级的准备.

The wing structure composed of units and relevant parts and members of the support
Aircraft in flight. These measures include rod, skin, etc., whole ribs, longitudinal tank structure.
Second, ...

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The wing structure composed of units and relevant parts and members of the support
Aircraft in flight. These measures include rod, skin, etc., whole ribs, longitudinal tank structure.
Second, the front and rear of the left, right wing box bar is the main wing main structure
Frame. They put in the ribs with sharp. Including the vertical bar plank tapered nets
Fall on the wing tip depth and the lower edge of the chord, provide. Vertical stiffener
Adhering to the vertical facing spare (figure 1).
(1) the flight control surfaces exposed the bar to deploy and near the ground surface contaminants in the air,
FanTuiLi soot, dust and debris runway and bad weather helps factors corrosion.
(2) SPAR chord was found to be particularly vulnerable to corrosion fasteners originating in the most likely
Common chords and network.
(3) stress corrosion cracking, has reported the front and rear SPAR strings (figure 1, the aa). about
Through the inspection requirements, aircraft and cracked chord 310 repair introduced
In the event with SB 1067 57-57-1081. At the moment, and the production adjustment, including and physical changes
The rear SPAR and low chord on the T6-7178 summaried.especially, with the former string T73 7075 -. Any changes
Ahead of low SPAR.
Note: 57-1081 prevention in the modification of the event is for someone R3 57-1081 R4 due to the stress changes
Corrosion by SB revision of 57-1081 R3 plane craze. This is due to improper evenly and
Decorate the reconstruction is used to prevent the installation Angle. Modified by SB 57-1081 fourth revision before the plane
To inspect every fourth edition (or later versions), and may the fourth revision (or in preventing modification
Later) to improve the corrosion protection. It has been an airworthiness instructions. Edition three
Event 737-57-1067 out of aging aircraft increased more than the nickel-ferric suggest the 737 string repair. This service,
57-1046 bulletin replace event with SB 57-116.
The stress corrosion cracking (4) has been reported in Kruger flaps actuator support, front assemblies
Beam. For inspection procedures outlined in aircraft parts by line 57-1129. Event
Numbers 813. The change of material on the plane and steel line 3391.

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外翼由结构单元，相关部件及支持飞机飞行的其他“成员”组成，这些“成员”包括：圆材。（飞机）蒙皮，长调支承木材以及整体油箱结构等等。
B飞机左右翼盒的前后圆材是主要翼桢的主要结构部件。他们从翼根延伸到蒙皮到翼尖。圆材包括下降至翼尖的垂直金属板网，并在其上下两端附有翼弦。垂直机肋贴在备用零件的垂直面上。
（1）飞机控制地面的部署使圆材接触地面并靠近地面空调系统。
推力换向器烟尘...

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外翼由结构单元，相关部件及支持飞机飞行的其他“成员”组成，这些“成员”包括：圆材。（飞机）蒙皮，长调支承木材以及整体油箱结构等等。
B飞机左右翼盒的前后圆材是主要翼桢的主要结构部件。他们从翼根延伸到蒙皮到翼尖。圆材包括下降至翼尖的垂直金属板网，并在其上下两端附有翼弦。垂直机肋贴在备用零件的垂直面上。
（1）飞机控制地面的部署使圆材接触地面并靠近地面空调系统。
推力换向器烟尘，跑道灰尘废墟以及恶劣天气因素等等都将导致腐蚀的发生。
（2）圆材翼弦极易腐蚀，最有可能是由紧固件导致的。翼弦和网也有此现象。
(3)应裂腐蚀开裂现象大多发生在翼弦的前后圆木材上。在飞机上，通过对开裂翼弦进行行号310检查和维修，其记录将被载入SB57-1067和SB57-1081.对于这两者而言，生产量在兼行号311上下波动。包括后园材的上下翼弦以及前圆材的上翼弦的材料的变化。从7178-T6变换到7075T73，前圆材下翼弦没有什么变化。
注意：由于当前飞机上的应裂腐蚀开裂原定针对于SB57-1081R3的预防性更改更换至对SB57-1081R4做改进。这变化是由不合适的填隙和针对预防修改设备的安装角度不合宜造成的。由SB57-1081更改的飞机在第四次审核之前或之后都要进行复查，希望R4的不协调修改能够减少腐蚀。一个适航指标已安装再此之上。SB737-57-1067的R3系列已在737飞机翼圆材上增添更多的建议维修器材。这种服务远超过SB57-1046和SB57-1062.
(4）枝条腐蚀裂缝已报告了克鲁克机翼动作器支持装置安装在前圆材。进口检查程序通过了行线813在SB57-1129上表述出来，材料的变化更加坚固飞机，并在继续发展。

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